МЕТАЛЛИЧЕСКОЕ ПОКРЫТИЕ (ВАРИАНТЫ) И СПОСОБ ЕГО НАНЕСЕНИЯ

Изобретения относятся к металлическим покрытиям и способам их нанесения и могут быть использованы при изготовлении газотурбинных двигателей, работающих в условиях высоких температур. Металлическое покрытие содержит до 18 мас.% кобальта, от 3,0 до 18 мас.% хрома, от 5,0 до 15 мас.% алюминия, от 0,1 до 1,0 мас.% иттрия, до 0,6 мас.% гафния, до 0,3 мас.% кремния, от 3,0 до 10 мас.% тантала, до 9,0 мас.% вольфрама, от 1,0 до 6,0 мас.% рения, до 10 мас.% молибдена, а остальное составляет никель. Способ его нанесения характеризуется тем, что сначала создают подложку из по крайней мере одного из металлических материалов на основе никеля, кобальта или железа, а затем наносят покрывочный слой. Изобретения позволяют получать покрытия с высокой стойкостью к окислению и усталостной прочностью. 8 с. и 25 з.п. ф-лы, 1 табл.

СУПЕРСПЛАВ НА ОСНОВЕ НИКЕЛЯ, МОНОКРИСТАЛЛИЧЕСКАЯ ЛОПАТКА И ГАЗОТУРБИННЫЙ ДВИГАТЕЛЬ

Изобретение относится к металлургии, а именно к суперсплавам на основе никеля, и может быть использовано в авиационной промышленности, в частности, для изготовления монокристаллических лопаток газотурбинного двигателя. Суперсплав на основе никеля содержит, в мас.%: 4,0-6,0 хрома, 0,4-0,8 молибдена, 2,5-3,5 рения, 6,2-6,6 вольфрама, 5,2-5,7 алюминия, 0,0-1,6 титана, 6,0-9,9 тантала, 0,3-0,7 гафния, 0,0-0,3 кремния, остальное – никель и возможные примеси. Монокристаллическая лопатка (20А, 20В) для газотурбинного двигателя, изготовленная с использованием суперсплава и имеющая защитное покрытие, содержащее металлический подслой, нанесённый на суперсплав, и керамический тепловой барьер, нанесённый на металлический подслой. Сплав характеризуется высокими значениями жаростойкости и стойкости к термической усталости, повышается стойкость теплового барьера к отслоению. 3 н. и 7 з.п. ф-лы, 1 ил., 3 табл., 5 пр.

ЖАРОПРОЧНЫЙ СПЛАВ НА ОСНОВЕ НИКЕЛЯ

Изобретение относится к жаропрочному сплаву на основе никеля. Сплав содержит, мас. %: 7,7 - 8,3 Cr, 5,0 - 5,25 Co, 2,0 - 2,1 Mo, 7,8 - 8,3 W, 5,8 - 6,1 Та, 4,9 - 5,1 Аl, 1,0 - 1,5 Ti, 1,0 - 2,0 Re, 0 - 0,5 Nb, 0,11 - 0,15 Si, 0,1 - 0,7 Hf, 0,02 - 0,17 C, 50 - 400 частей на миллион В, остальное - никель и неизбежные примеси. Сплав характеризуется высокой стойкостью к окислению, коррозионной стойкостью и положительными свойствами ползучести при высоких температурах.18 з.п. ф-лы, 3 ил., 1 табл.

СПЛАВ НА ОСНОВЕ НИКЕЛЯ, СОДЕРЖАЩИЙ КРЕМНИЙ, АЛЮМИНИЙ И ХРОМ

Изобретение относится к области металлургии, а именно к сплавам на основе никеля, которые могут быть использованы в качестве материала для изготовления элементов зажигания двигателей внутреннего сгорания. Сплав на основе никеля содержит, мас.%: Si 1,5-3,0, Al 1,5-3,0, Cr >0,1-3,0, Fe 0,005-0,20, Y 0,01-0,20, один или несколько из элементов: Hf, Zr, La, Ce, Ti <0,001-0,20, C 0,001-0,10, N 0,0005-0,10, Mn 0,001-0,20, Mg 0,0001-0,08, O 0,0001-0,010, S не более 0,015, Cu не более 0,80, Ni и обычные технологически обусловленные примеси - остальное. Сплав характеризуется высокими значениями стойкости к искровой эрозии и стойкости к коррозии при одновременно достаточных значениях деформируемости и свариваемости. 2 н. и 18 з.п. ф-лы.

Способ получения электродов из сплавов на основе алюминида никеля

Изобретение относится к области специальной металлургии, в частности к получению литых шихтовых заготовок электродов из высоколегированных сплавов на основе алюминидов никеля, и может быть использовано для центробежной атомизации материала электродов и получения гранул для применения в аддитивных 3D-технологиях с целью получения сложнопрофильных изделий из жаропрочных металлических материалов. Способ получения электродов из сплава на основе алюминида никеля включает получение полуфабриката методом центробежного СВС-литья при центробежном ускорении 60±10g с использованием реакционной смеси, содержащей, вес.%: оксид никеля 47,0-49,1, алюминий 28,6-32,4, смесь CrO, Hf, B и CoOв качестве легирующей добавки 13,1-17,9, смесь AlOи NaAlFв качестве функциональной добавки 6,5-7,0, и последующий двухстадийный переплав полуфабриката с получением на первой стадии рафинированого дегазированного слитка, а на второй стадии - электрода, при этом на второй стадии за 2-3 мин до разливки в расплав вводят лигатуру ...

Жаропрочный никелевый сплав с равноосной структурой

Изобретение относится к области металлургии, а именно к производству никелевых жаропрочных сплавов, и может быть использовано при изготовлении деталей и узлов для авиационных газотурбинных двигателей и газоперекачивающих, энергетических и морских газотурбинных установок, применяемых в авиации, судостроении, энергетике, ракетостроении и других отраслях промышленности, в том числе для высокотемпературных штампов. Никелевый жаропрочный сплав с равноосной структурой содержит, мас.%: С 0,08-0,18; Сr 3,0-8,0; Со 5,0-10,0; W 4,0-10,0; Мо 0,5-2,0; Аl 4,5-6,5; Ti 0,5-3,5; Nb 0,5-2,5; Та 5,0-10,0; Hf 0,05-1,0; Re 3,0-5,0; V 0,1-1,0; В 0,01-0,1; Zr 0,005-0,05; Се 0,005-0,1; La 0,005-0,1; Y 0,005-0,1; Mg 0,005-0,3; Mn 0,05-0,5; Si 0,05-0,5; Ca 0,02-0,2; Fe 0,1-0,5; Ni - остальное. Сплав характеризуется высоким уровнем жаропрочности. 2 табл.

МОНОКРИСТАЛЛИЧЕСКИЙ СУПЕРСПЛАВ НА ОСНОВЕ Ni

... 1. Монокристаллический суперсплав на основе Ni, имеющий состав, включающий: от 5,0 до 7,0 мас.% Al, от 4,0 до 10,0 мас.% Та, от 1,1 до 4,5 мас.% Мо, от 4,0 до 10,0 мас.% W, от 3,1 до 8,0 мас.% Re, от 0,0 до 2,0 мас.% Hf, от 2,5 до 8,5 мас.% Cr, от 0,0 до 9,9 мас.% Со, от 0,0 до 4,0 мас.% Nb и от 1,0 до 14,0 мас.% Ru в расчете на массовую долю; а остальное включает Ni и случайные примеси. ! 2. Монокристаллический суперсплав на основе Ni по п.1, в котором Hf составляет в интервале от 0,0 до 0,5 мас.%, а Cr составляет в интервале от 5,1 до 8,5 мас.%. ! 3. Монокристаллический суперсплав на основе Ni по п.1, в котором Hf составляет в интервале от 0,0 до 0,5 мас.%, Cr составляет в интервале от 5,1 до 8,5 мас.%, Мо составляет в интервале от 2,1 до 4,5 мас.%, а Та составляет в интервале от 4,0 до 6,0 мас.%. ! 4. Монокристаллический суперсплав на основе Ni, имеющий состав, включающий: от 5,0 до 6,5 мас.% Al, от 4,0 до 6,5 мас.% Та, от 2,1 до 4,0 мас.% Мо, от 4,0 до 6,0 мас.% W, от 4,5 до 7,5 мас ...

ЗАГОТОВКА ИЗ КОВОЧНОГО СПЛАВА НА ОСНОВЕ NI И ВЫСОКОТЕМПЕРАТУРНЫЙ ЭЛЕМЕНТ КОНСТРУКЦИИ ТУРБИНЫ С ИСПОЛЬЗОВАНИЕМ ЭТОЙ ЗАГОТОВКИ

Изобретение относится к области металлургии, а именно к получению заготовок из ковочного сплава на основе никеля, которые могут быть использованы при изготовлении высокотемпературных элементов конструкции турбины. Заготовка из ковочного сплава на основе Ni содержит кристаллические зерна γ-фазы и выпадающие частицы γ'-фазы и имеет химический состав, при котором в матричную γ-фазу при 700°С выпадает 50-70 об.% γ'-фазы. Фаза γ' содержит: частицы γ'-фазы старения, выпадающие в кристаллические зерна γ-фазы, и частицы γ'-фазы эвтектической реакции, выпадающие между этими кристаллическими зернами γ-фазы, причем в частицах γ'-фазы эвтектической реакции содержание Ni и Аl превышает содержание этих элементов в частицах γ'-фазы старения, а средний размер частиц γ'-фазы эвтектической реакции составляет 2-40 мкм. Заготовка характеризуется высокими значениями механических свойств. 3 н. и 4 з.п. ф-лы, 7 ил., 4 табл., 5 пр.

ТЕПЛОЗАЩИТНОЕ ПОКРЫТИЕ, НАНОСИМОЕ НЕПОСРЕДСТВЕННО НА МОНОКРИСТАЛЛИЧЕСКИЕ ЖАРОПРОЧНЫЕ СПЛАВЫ

... 1. Способ нанесения теплозащитного покрытия на монокристаллический жаропрочный сплав (10), отличающийся тем, что упомянутый жаропрочный сплав (10) имеет состав по массе: 3,5-7,5% Cr, 0-1,5% Mo, 1,5-5,5% Re, 2,5-5,5% Ru, 3,5-8,5% W, 5-6,5% Al, 0-2,5% Ti, 4,5-9% Ta, 0,08-0,12% Hf, 0,08-0,12% Si, остальное до 100% составляют Ni и случайные примеси, и тем, что непосредственно на этот жаропрочный сплав наносят диоксид циркония (20), стабилизированный по меньшей мере одним оксидом элемента, выбранного из группы, состоящей из редкоземельных металлов, или сочетанием оксида тантала и по меньшей мере одного оксида редкоземельного металла, или сочетанием оксида ниобия и по меньшей мере одного оксида редкоземельного металла. ! 2. Способ по п.1, отличающийся тем, что упомянутый жаропрочный сплав (10) имеет состав по массе: 3,5-5,5% Cr, 0-1,5% Mo, 4,5-5,5% Re, 2,5-5,5% Ru, 4,5-6,5% W, 5-6,5% Al, 0-1,5% Ti, 5-6,2% Ta, 0,08-0,12% Hf, 0,08-0,12% Si, остальное до 100% составляют Ni и случайные примеси. !

БАРЬЕРНЫЕ СЛОИ, ВКЛЮЧАЮЩИЕ Ni-СОДЕРЖАЩИЕ ТРОЙНЫЕ СПЛАВЫ, ПОКРЫТЫЕ ИЗДЕЛИЯ, ВКЛЮЧАЮЩИЕ БАРЬЕРНЫЕ СЛОИ, И СПОСОБЫ ИХ ИЗГОТОВЛЕНИЯ

... 1. Покрытое изделие с поддерживающей низкоизлучательное покрытие подложкой, причем покрытие включает в порядке удаления от подложки:первый диэлектрический слой;первый барьерный слой;первый отражающий ИК излучение слой, содержащий серебро, предусмотренный над и в контакте с первым барьерным слоем;второй барьерный слой, предусмотренный над и в контакте с отражающим ИК излучение слоем; ивторой диэлектрический слой, предусмотренный над вторым барьерным слоем,при этом первый и второй барьерные слои окислены и по массе металла содержат 54-58 мас.% Ni, 20-22,5 мас.% Cr и 12,5-14,5 мас.% Мо.2. Покрытое изделие по п. 1, при этом изделие включает только один отражающий ИК излучение слой.3. Покрытое изделие по п. 1, дополнительно включающее верхний слой, содержащий оксид Zr, над вторым барьерным слоем.4. Покрытое изделие по п. 3, при этом слой, содержащий оксид Zr, дополнительно содержит по меньшей мере один из Ti, Al и Мо.5. Покрытое изделие с поддерживающей низкоизлучательное покрытие стеклянной ...

OXIDATIONSUND FATIGUE-STEADY METALLIC COATING

NICKEL ALLOY COMPOSITIONS CORROSION RESISTANT WITH MORE INCREASE CASTINGBARNESS AND EXTENDED MECHANICAL CHARACTERISTICS

SUPERALLOY ON NICKEL BASIS AND MANUFACTURING PROCESS FOR IT

PROCEDURE FOR THE PRODUCTION THERMAL EXPANSION ARMS OF A SUPERALLOY ON NI-BASIS

ON NICKEL BASED SUPERALLOY, ASSOCIATED PROCEDURE FOR THE UNIDIRECTIONAL SOLIDIFICATION AND FROM IT FORMED CAST PIECES

OXIDE-DISPERSION-HARDENED ALLOY WITH GOOD FIRMNESS IN THE MIDDLE TEMPERATURE RANGE.

NICKEL BASIS ALLOY FOR THE CASTINGTECHNICAL PRODUCTION SINGLE-CRYSTAL OF RIGID CONSTRUCTION UNITS

Ni-base single crystal superalloy

Nickel base superalloys and turbine components fabricated therefrom

Single crystal nickel-based superalloy

OXIDATION AND FATIGUE RESISTANT METALLIC COATING

The present invention relates to a metallic coating to be deposited on gas turbine engine components. The metallic coating comprises up to 18 wt% cobalt, 3.0 to 18 wt% chromium, 5.0 to 15 wt% aluminum, 0.1 to 1.0 wt% yttrium, up to 0.6 wt% hafnium, up to 0.3 wt% silicon, 3.0 to 10 wt% tantalum, up to 9.0 wt% tungsten, 1.0 to 6.0 wt% rhenium, up to 10 wt% molybdenum, and the balance nickel.

CORROSION-RESISTING AND WEAR-RESISTING ALLOY AND DEVICE USING THE SAME

To provide a corrosion-resisting and wear resisting alloy including cobalt, nickel or iron as a base used for a sliding part or a valve seat for a machine, and restraining erosion and corrosion caused by eutectic carbide constituting the alloy in an atmosphere with dissolved oxygen. A material is selected from a cobalt base added with Cr and/or W, a nickel base added with Fe and/or Cr, and an iron vase added with Cr and/or Ni. The material is cast into an ingot or a slab to produce an intermediate material. The intermediate material comprises mesh-like eutectic carbide and a base material surrounded by the eutectic carbide. A heat plastic forming is applied to the intermediate material at a temperature 650.degree.C or more and the solidus temperature or less. The eutectic carbide is formed into multiple grains or clusters as a discontinuous distribution. A resulting corrosion-resisting and wear-resisting alloy has 0.1 to 0.5 of coefficient of friction, and 300 to 600 Hv of Vickers hardness ...

NI-BASED SINGLE CRYSTAL SUPERALLOY AND TURBINE BLADE

The present invention provides a Ni-based single crystal superalloy which has the following composition by weight: 0.1 wt% or more and 9.9 wt% or less of Co, 5.1 wt% or more and 10.0 wt% or less of Cr, 1.0 wt% or more and 4.0 wt% or less of Mo, 8.1 wt% or more and 11.0 wt% or less of W, 4.0 wt% or more and 9.0 wt% or less of Ta, 5.2 wt% or more and 7.0 wt% or less of Al, 0.1 wt% or more and 2.0 wt% or less of Ti, 0.05 wt% or more and 0.3 wt% or less of Hf, 1.0 wt% or less of Nb and less than 3.0 wt% of Re with the remainder including Ni and unavoidable impurities. This Ni-based single crystal superalloy has a low Re content and also has excellent high-temperature strength, mainly creep strength.

NICKEL-BASE SUPERALLOY CAST ARTICLE

A nickel-base superalloy cast article is provided with improved stress rupture and creep properties as a result of providing its microstructure with aligned cellular dendrites in combination with the substantial absence of NiAl, carbon, carbides, and Ti. The superalloy consists, in atomic percent, essentially of 4-11 Cr. 5-16 Al, at least 0.5 R?, up to about 10V, up to about 15 Co, up to about 5 Ta, up to about 5W, up to about 1 Mo, up to about 2.5 Mn, up to about 2.5 Rh, with the balance nickel and incidental impurities. The alloy is suited for use in gas turbines.

BRAZE ALLOY COMPOSITIONS

A nickel-based high-temperature braze alloy composition includes Cr, Hf, and B. Furthermore, a cobalt-based high-temperature braze alloy composition includes Cr, Hf, and B. The braze alloys can be used, for example, as a single homogenous braze. The braze alloys can also be used, for example, as a component in a wide gap braze mixture where higher or lower melting point superalloy and/or brazing powder is used. The braze alloys may permit joining/repairing of superalloy articles with complex shape and may be used in high temperature applications.

HIGH STRENGTH NICKEL BASE ALLOY

NICKEL-BASED SUPERALLOY, SINGLE-CRYSTAL BLADE AND TURBOMACHINE

L'invention concerne un superalliage à base de nickel comprenant, en pourcentages massiques, 4,0 à 5,5 % de rhénium, 1,0 à 3,0 de ruthénium, 2,0 à 14,0 % de cobalt, 0,3 à 1,0 % de molybdène, 3,0 à 5,0 % de chrome, 2,5 à 4,0 % de tungstène, 4,5 à 6,5 % d'aluminium, 0,50 à 1,50 % de titane, 8,0 à 9,0 % de tantale, 0,15 à 0,30 % de hafnium, 0,05 à 0,15 % de silicium, le complément étant constitué par du nickel et des impuretés inévitables. L'invention concerne également une aube (20A, 20B) monocristalline comprenant un tel alliage et une turbomachine (10) comprenant une telle aube (20A, 20B).

NICKEL BASED MONOCRYSTALLINE SUPERALLOY, METHOD OF HEAT TREATING SAID ALLOY, AND PARTS MADE THEREFROM

THERMAL BARRIER PLACED DIRECTLY ON SINGLE-CRYSTAL SUPERALLOYS

L'invention concerne le domaine des superalliages revêtus d'une barrière thermique. Sur un superalliage (10) monocristallin de composition en masse de 3,5 à 7,5% Cr, 0 à 1,5% Mo, 1,5 à 5,5% Re, 2,5 à 5,5% Ru, 3,5 à 8,5%W,5 à 6,5% Al, 0 à 2,5% Ti,4,5 à 9% Ta,0,08 à 0,12% Hf, 0,08 à 0,12% Si, le complément à 100% étant constitué par Ni et les impuretés éventuelles, on dépose directement une zircone (20) stabilisée avec au moins un oxyde d'un élément choisi dans le groupe constitué des terres rares, ou avec une combinaison d'un oxyde de tantale et d'au moins un oxyde de terre rare, ou avec une combinaison d'un oxyde de niobium et d'au moins un oxyde de terre rare.

LAYERED ASSEMBLIES FOR SUPERALLOY ARTICLE REPAIR

Methods of superalloy article repair are provided. In some embodiments, a method for repairing a nickel-based superalloy article comprises providing a layered assembly over a damaged region of the nickel-based superalloy article, the layered assembly comprising a nickel-based superalloy preform, an infiltration alloy preform and a melting point depressant component. The layered assembly is heated to form a nickel-based filler alloy metallurgically bonded to the damaged region, wherein primary carbide and secondary carbide phases are present in the nickel-based filler alloy in a combined amount of 0.5 to 10 vol.%.

ADVANCED BOND COAT

In some examples, an alloy may include less than 55 atomic percent aluminum; between about 10 and about 25 atomic percent of a platinum group metal; and a balance of nickel; at least one of chromium, silicon, tantalum, or cobalt; a reactive element; and diffusion impurities; where the alloy has a discrete gamma-prime Ni3A1 region and a discrete beta NiA1 region. In some examples, a coating system may include a substrate; a first layer including gamma-prime Ni3A1; and a second layer including beta NiA1, where the first region and the second region are discrete dual region.

NI-BASED SINGLE CRYSTAL SUPERALLOY

The Ni-based single crystal alloy disclosed here is a single crystal and has a chemical composition containing, as % by mass, Co: 8 to 12%, Cr: 5 to 7.5%, Mo: 0.2 to 1.2%, W: 5 to 7%, Al: 5 to 6.5%, Ta: 8 to 12%. Hf: 0.01 to 0.2%, Re: 2 to 4%, Si: 0.005 to 0.1%, with the balance of Ni and inevitable impurities.

NICKEL ALLOY

A nickel alloy with high-temperature oxidation resistance and excellent creep strength is provided. The nickel alloy comprises 11.5%-11.9% by mass Cr, 25%-29% by mass Co, 3.4%-3.7% by mass Mo, 1.9%-2.1% by mass W, 3.9%-4.4% by mass Ti, 2.9%-3.2% by mass Al, 0.02%-0.03% by mass C, 0.01%-0.03% by mass B, 0.04%-0.06% by mass Zr, 2.1%-2.2% by mass Ta, 0.3%-0.4% by mass Hf, 0.5%-0.8% by mass Nb, with the remainder comprising Ni and unavoidable impurities; and includes carbide and boride precipitated in the crystal grains and in the crystal grain boundaries.

TURBINE BLADES MADE FROM MULTIPLE SINGLE CRYSTAL CAST SUPERALLOY SEGMENTS

Large gas turbine blades (10) made from separate cast segments (12, 14. 16, 18) of superalloys are disclosed. The turbine blade is designed such that bond lines between adjacent segments are placed in low stress regions of the blade. The cast superalloy segments of the blades are aligned and fitted together with specified tolerances. The turbine blade segments are then joined by transient liquid phase bonding, followed by a controlled heat treatment which produces the desired microstructure in the bond region. The method allows for the production of large, high quality turbine blades (10) by joining small, high quality cast superalloy sections (12, 14, 16, 18), in comparison with prior attempts to cast large turbine blades as single pieces which have produced very low yields and high individual component costs.

Thermokompensierende Feder

Elektronenröhre

Alliage de nickel et utilisation de cet alliage

Alliage de nickel

SUPERALLOY ON NICKEL BASIS.

Casting method and A molded article as.

Es sind ein Giessverfahren und ein Gussartikel offenbart. Das Giessverfahren enthält ein Bereitstellen eines Basismaterials (101) in einer Form (110), Einleiten eines Fluidmaterials (103) in die Form (110) und Erstarrenlassen des Basismaterials (101) und des Fluidmaterials (103), um einen Gussartikel (109) zu bilden. Das Basismaterial (101) weist eine erste Dichte und eine Zusammensetzung auf. Das Fluidmaterial (103) weist eine zweite Dichte und eine zweite Zusammensetzung auf. Die erste Dichte unterscheidet sich von der zweiten Dichte, oder die erste Zusammensetzung unterscheidet sich von der zweiten Zusammensetzung, oder die erste Dichte unterscheidet sich von der zweiten Dichte und die erste Zusammensetzung unterscheidet sich von der zweiten Zusammensetzung. Der Gussartikel (109) enthält ein erstes erstarrtes Material aus dem Basismaterial und ein zweites erstarrtes Material aus dem Fluidmaterial. Durch das Verfahren wird die Kernstruktur des Gussartikels (109) kontrolliert.

Nickel basis superalloy.

Nickel basis superalloy with improved degradation behavior.

Die Erfindung betrifft eine Nickel-Basis-Superlegierung. Die erfindungsgemässe Legierung ist gekennzeichnet durch folgende chemische Zusammensetzung (Angaben in Gew.-%): 7.78.3 Cr, 5.05.25 Co, 2.02.1 Mo, 7.88.3 W, 5.86.1 Ta, 4.95.1 Al, 1.31.4 Ti, 0.10.6 Pt, 0.10.5 Nb, 0.110.15 Si, 0.110.15 Hf, 200750, vorzugsweise 200300 ppm C, 50400, vorzugsweise 50100 ppm B, Rest Ni und herstellungsbedingte Verunreinigungen. Sie zeichnet sich durch ein verbessertes Degradationsverhalten aus.

Protective pipes for thermocouples.

Die Erfindung betrifft Schutzrohre (1) für Thermoelemente, welche bei Temperaturen im Bereich von ca. 1100 °C oxidierenden Atmosphären ausgesetzt sind. Sie ist dadurch gekennzeichnet, dass diese Schutzrohre (1) aus einer Einkristall-Nickelbasis-Superlegierung, bevorzugt aus einer Legierung mit folgender chemische Zusammensetzung (Angaben in Gew.- %): 7.78.3 Cr, 5.05.25 Co, 2.02.1 Mo, 7.88.3 W, 5.86.1 Ta, 4.95.1 Al, 1.31.4 Ti, 0.110.15 Si, 0.11-0.15 Hf, 200750 ppm C, 50400 ppm B, Rest Nickel und herstellungsbedingte Verunreinigungen hergestellt sind. Derartige Schutzrohre erfüllen die hohen Beanspruchungsbedingungen hinsichtlich Festigkeit und Oxidationsbeständigkeit.

Hysteresis-poor sensor.

Ein Sensor (1) umfasst eine Magnetfeldquelle (3), zumindest ein flussführendes weichmagnetisches Element (2), der zumindest einen Luftspalt (4) aufweist, und zumindest einen Magnetfeldsensor (5), das im Luftspalt (5) angeordnet ist und eine Änderung des Magnetfelds der Magnetfeldquelle (3) misst. Das flussführende weichmagnetische Element (2) besteht aus einer Legierung, die aus 35 Gew.-% Ni 50 Gew.-%, 0 Gew.-% Co 2 Gew.-%, 0 Gew.-% Mn 1,0 Gew.-% 0 Gew.-% Si 0,5 Gew.-% sowie 0,5 Gew.-% Cr 8 Gew.-% und/oder 0,5 Gew.-% Mo 8 Gew.-%, wobei (Mo+Cr) 8 ist, Rest Eisen sowie unvermeidbaren Verunreinigungen besteht.

hysteresis-poorer Sensor.

Ein Sensor (1) umfasst eine Magnetfeldquelle (3), zumindest ein flussführendes weichmagnetisches Element (2), der zumindest einen Luftspalt (4) aufweist, und zumindest einen Magnetfeldsensor (5), das im Luftspalt (5) angeordnet ist und eine Änderung des Magnetfelds der Magnetfeldquelle (3) misst. Das flussführende weichmagnetische Element (2) besteht aus einer Legierung, die aus 35 Gew.% Ni 50 Gew.%, 0 Gew.% Co 2 Gew.%, 0 Gew.% Mn 1,0 Gew.% 0 Gew.% Si 0,5 Gew.% sowie 0,5 Gew.% Cr 8 Gew.% und/oder 0,5 Gew.% Mo 8 Gew.%, wobei (Mo+Cr) 8 ist, Rest Eisen sowie unvermeidbaren Verunreinigungen besteht.

Nickel basis superalloy.

Die Erfindung betrifft eine Nickel-Basis-Superlegierung. Die erfindungsgemässe Legierung ist gekennzeichnet durch folgende chemische Zusammensetzung (Angaben in Gew.-%): 7.78.3 Cr, 5.05.25 Co, 2.02.1 Mo, 7.88.3 W, 5.86.1 Ta, 4.95.1 Al, 1.01.5 Ti, 1.02.0 Re, 0.110.15 Si, 0.10.7 Hf, 00.5 Nb, 0.020.17 C, 50400 ppm B, Rest Ni und herstellungsbedingte Verunreinigungen. Sie zeichnet sich durch eine sehr hohe Oxidationsbeständigkeit, Korrosionsbeständigkeit und gute Kriecheigenschaften bei hohen Temperaturen aus.

From such alloys nickel basis superalloys and A molded article as, in particular for components of gas turbine engines.

Geschaffen sind Nickelbasissuperlegierungen, die aufweisen: etwa 7,0 Gewichtsprozent (Gew.-%) bis 12,0 Gew.-% Chrom, etwa 0,1 Gew.-% bis 5 Gew.-% Molybdän, etwa 0,2 Gew.-% bis 4,5 Gew.-% Titan, etwa 4 Gew.-% bis 6 Gew.-% Aluminium, etwa 3 Gew.-% bis 4,9 Gew.-% Kobalt, etwa 6,0 Gew.-% bis 9,0 Gew.-% Wolfram, etwa 4,0 Gew.-% bis 6,5 Gew.-% Tantal, etwa 0,05 Gew.-% bis 0,6 Gew.-% Hafnium, bis etwa 1,0 Gew.-% Niob, bis etwa 0,02 Gew.-% Bor, und bis etwa 0,1 Gew.-% Kohlenstoff, wobei Nickel und zufällige Verunreinigungen die Differenz zu 100% bilden. Die Legierungen können gegossen, direktional erstarrt und wärmebehandelt werden, um Artikel mit einem γ´-Anteil von mehr als etwa 50% zu erzeugen.

Nickel basis superalloys and articles.

Geschaffen sind Nickelbasissuperlegierungen, die aufweisen: etwa 7,0 Gewichtsprozent (Gew.-%) bis ungefähr 12,0 Gew.-% Chrom, etwa 0,1 Gew.-% bis ungefähr 5 Gew.-% Molybdän, etwa 0,2 Gew.-% bis ungefähr 4,5 Gew.-% Titan, etwa 4 Gew.-% bis ungefähr 6 Gew.-% Aluminium, etwa 3 Gew.-% bis ungefähr 4,9 Gew.-% Kobalt, etwa 6,0 Gew.-% bis ungefähr 9,0 Gew.-% Wolfram, etwa 4,0 Gew.-% bis ungefähr 6,5 Gew.-% Tantal, etwa 0,05 Gew.-% bis ungefähr 0,6 Gew.-% Hafnium, bis etwa 1,0 Gew.-% Niob, bis etwa 0,02 Gew.-% Bor, und bis etwa 0,1 Gew.-% Kohlenstoff, wobei Nickel und zufällige Verunreinigungen die Differenz zu 100% bilden. Die Legierungen können gegossen, direktional erstarrt und wärmebehandelt werden, um Artikel mit einem ´-Anteil von mehr als etwa 50% zu erzeugen.

Article and method of making an article.

Es sind ein Gegenstand und ein Verfahren zur Herstellung formgestalteter Kühllöcher in einem Gegenstand geschaffen. Das Verfahren enthält die Schritte des Auftragens eines Metalllegierungspulvers, um eine Anfangsschicht zu bilden, die wenigstens eine Öffnung enthält, des Schmelzens des Metalllegierungspulvers mit einer fokussierten Energiequelle, um die Pulverschicht in eine Metalllegierungsbahn umzuwandeln, des darauffolgenden Auftrags einer zusätzlichen Schicht des Metalllegierungspulvers, um eine Schicht zu bilden, die wenigstens eine Öffnung enthält, die der wenigstens einen Öffnung in der Anfangsschicht entspricht, des Schmelzens der zusätzlichen Schicht des Metalllegierungspulvers mit der fokussierten Energiequelle zur Erhöhung der Bahndicke und des Wiederholens der Schritte des aufeinanderfolgenden Auftrags und Aufschmelzens der zusätzlichen Schichten des Metalllegierungspulvers, bis eine Struktur, die wenigstens eine Öffnung mit einem vorbestimmten Profil enthält, erhalten wird.

Nickel base superalloy article and method of making an article.

Es werden ein Gegenstand und ein Verfahren zur Herstellung eines Einkristallgussstücks offenbart. Der Gegenstand enthält eine Einkristall-Superlegierung auf Nickelbasis mit einer Zusammensetzung, die mehr als etwa 80 ppm Bor (B) und eine im Wesentlichen einkristalline Mikrostruktur mit mindestens einer Korngrenze aufweist. Eine Dauerstandfestigkeit des Gegenstands wird bis zu einer Korngrenzenfehlpassung von etwa 40 Grad weitgehend bewahrt. Das Verfahren zur Herstellung eines Einkristallgussstücks enthält ein Positionieren einer Form auf einer Kühlplatte, wobei die Form einen Einkristallselektor aufweist, Bereitstellen einer geschmolzenen Superlegierungszusammensetzung auf Nickelbasis in der Form, wobei die geschmolzene Zusammensetzung mehr als etwa 80 ppm Bor (B) enthält, Abkühlen der geschmolzenen Zusammensetzung mit der Kühlplatte und Ausbilden eines unidirektionalen Temperaturgradienten durch Herausholen der Form aus dem Inneren einer Wärmequelle, um das Einkristallgussstück herzustellen ...

Article and method of making an article.

Es sind ein Gegenstand und ein Verfahren zur Herstellung formgestalteter Kühllöcher in einem Gegenstand geschaffen. Das Verfahren enthält die Schritte des Auftragens eines Metalllegierungspulvers, um eine Anfangsschicht zu bilden, die wenigstens eine Öffnung enthält, des Schmelzens des Metalllegierungspulvers mit einer fokussierten Energiequelle, um die Pulverschicht in eine Metalllegierungsbahn umzuwandeln, des darauffolgenden Auftrags einer zusätzlichen Schicht des Metalllegierungspulvers, um eine Schicht zu bilden, die wenigstens eine Öffnung enthält, die der wenigstens einen Öffnung in der Anfangsschicht entspricht, des Schmelzens der zusätzlichen Schicht des Metalllegierungspulvers mit der fokussierten Energiequelle zur Erhöhung der Bahndicke und des Wiederholens der Schritte des aufeinanderfolgenden Auftrags und Aufschmelzens der zusätzlichen Schichten des Metalllegierungspulvers, bis eine Struktur, die wenigstens eine Öffnung mit einem vorbestimmten Profil enthält, erhalten wird.

Nickel base superalloy article and method of manufacturing the superalloy article.

Es werden ein Gegenstand und ein Verfahren zur Herstellung eines Einkristallgussstücks offenbart. Der Gegenstand enthält eine Einkristall-Superlegierung auf Nickelbasis mit einer Zusammensetzung, die mehr als etwa 80 ppm Bor (B) und eine im Wesentlichen einkristalline Mikrostruktur mit mindestens einer Korngrenze aufweist. Eine Zeitstandfestigkeit des Gegenstands wird bis zu einer Korngrenzenfehlpassung von etwa 40 Grad weitgehend bewahrt. Das Verfahren zur Herstellung eines Einkristallgussstücks enthält ein Positionieren einer Form auf einer Kühlplatte, wobei die Form einen Einkristallselektor aufweist, Bereitstellen einer geschmolzenen Superlegierungszusammensetzung auf Nickelbasis in der Form, wobei die geschmolzene Zusammensetzung mehr als etwa 80 ppm Bor (B) enthält, Abkühlen der geschmolzenen Zusammensetzung mit der Kühlplatte und Ausbilden eines unidirektionalen Temperaturgradienten durch Herausholen der Form aus dem Inneren einer Wärmequelle, um das Einkristallgussstück herzustellen ...

METHOD OF PRODUCING ELECTRODES FROM ALLOYS BASED ON NICKEL ALUMINIDE

METALLIC COATING AND METHOD OF ITS APPLICATION

HIGH TEMPERATURE LOW THERMAL EXPANSION Ni-Mo-Cr ALLOY

A METAL COATING AND A METHOD FOR THE APPLICATION THEREOF

HEAT RESISTANT ALLOY

SUPERALLOY POWDERS

Nickel alloys

HIGH CREEP-STRENGTH NICKEL ALLOYS

New single crystal nickel superalloy, e.g. for aircraft turbine blades, has a specified composition providing low density, high creep resistance and good micro structural stability

Superalliage monocristallin à matrice à base de nickel, de densité ne dépassant pas 8, 7, de composition pondérale suivante : Cr 4, 5 à 6 % - Co 0 à 10 % - Mo 1 à 3 % - W 4, 5 à 7, 5 % - Ta 3, 5 à 7 % - Ti 0, 5 à 2 % - Nb 0 à 0, 2 % - Al 5 à 5, 6 % - Ru 0 à 3 % - Hf 0 à 0, 7 % - Si 0 à 0, 2 % - Re 2 à 3, 5 % - Y 0 à 0, 05 % - S 0 à 10 ppm et Ni complément à 100. De plus, la somme atomique Al+Ti+Ta+Nb est comprise entre 15 et 16 % et la somme atomique Mo+W+Re+Ru est comprise entre 4, 2 et 4,8 %. Ce superalliage est particulièrement adapté à la coulée monocristalline d'aubes de turbine présentant une haute résistance au fluage et il présente une bonne stabilité microstructurale.

NICKEL-BASE TANTALUM CARBIDE EUTECTIC ALLOYS

Nickel-base superalloy with high mechanical and environmental strength at high temperature and low density

SUPERALLOY CONTAINING NICKEL AND CASTINGS IN MONOCRYSTAL

Ce superalliage (A ou B) comprend comprend essentiellement, en % en poids, environ 9,5 % à environ 14,0 % de Cr, 7,0 à environ 11,0 % de Co, environ 3,0 à environ 5,0 % de Ti, environ 3,0 à environ 4,0 0 % de Al, environ 3,0 à environ 4,0 % de W, environ 1,0 à environ 2,5 % de Mo, environ 1,0 à environ 4,0 % de Ta, environ 1,0 à environ 6,0 % de Re, jusqu'à environ 0,25 % de C, jusqu'à environ 0,015 % de B, jusqu'à environ 1,0 % de Nb, jusqu'à environ 0,15 % de Hf, jusqu'à environ 0,003 % de Zr, et le reste formé de Ni et d'éventuelles impuretés. Application notamment aux aubes de turbines.

니켈 베이스 초합금 컴포넌트들의 레이저 첨가제 수리

... 비교적 다량의 Al 및 Ti를 포함하는 Ni 베이스 초합금 컴포넌트들은, 균열 없이 용접 빌드 업 프로세스에 의해 빌드 업 하기가 어렵다고 알려져 있다. 강도를 개선시키기 위해 초합금의 Al 및 Ti 함량이 증가되기 때문에, 균열에 대한 민감성이 증가된다. 본원에서는, 첨가제 빌드 업 재료에서 γ' 페이즈를 감소시키는 것이 균열에 대비한 강건성을 개선시킴이 나타난다. 존재하는 γ'을 감소시키고 그렇게 함으로써 균열을 감소시키기 위해, 첨가제 빌드 업 프로세스와 협력하여 사용될 단계적인 제어된 가열 및 냉각 프로세스가 설명된다.

금속 호일의 제조 방법

... 본 발명은 다음 방법 단계들을 포함하는, 50% 초과의 니켈을 갖는 합금으로으로부터의 금속 필름의 제조 방법에 관한 것이다: (a) 상기 합금은 진공 유도로(vacuum induction furnace) 내에서, 또는 개방된 유도로 또는 아크로 내에서 1 메트릭톤 초과의 용량으로 용융되고, 이후 VOD 또는 VLF 시스템에서 처리되는 단계, (b) 이후 상기 합금은 예비 생성물을 형성하기 위해 블록 또는 전극으로 주조되거나, 또는 연속 주조법으로 주조되며, 이후 필요한 경우 VAR 및/또는 ESU에 의해 단일 또는 다중 재용융(remelting)되는 단계, (c) 이후 상기 1차 생성물은 필요한 경우 공기 또는 보호 가스 하에 800℃ 내지 1350℃의 온도에서 1 시간 내지 300 시간 동안 어닐링되는 단계, (d) 이후 상기 예비 생성물은 600℃ 내지 1300℃의 온도에서 열간 성형, 특히 열간 압연되어 출발 재료의 두께가 1.5 내지 200 배 감소됨으로써, 상기 예비 생성물은 상기 성형 후 1 내지 100 mm의 두께를 가지며, 재결정화 및/또는 어닐링되지 않았거나, 및/또는 300 mm 미만의 그레인 크기로 (동력학적으로) 재결정화되는 단계, (e) 이후 상기 예비 생성물은 산세정되는 단계, (f) 이후 상기 예비 생성물은 10 내지 600 mm, 특히 40 내지 150 mm의 최종 두께를 갖는 필름을 제조하기 위해 90% 초과의 변형도로 냉간 가공되는 단계, (g) 이후 상기 냉간 성형 후에, 상기 필름은 5 내지 300 mm의 스트립들로 절단되는 단계, (h) 이후 상기 호일 스트립들은 연속로에서 보호 가스 하에 600℃ 내지 1200℃의 온도에서 1 초 내지 5 시간 동안 어닐링되는 단계, (i) 이 어닐링 후 상기 어닐링된 필름 형상 재료는 재결정화되어 있고, 고 비율의 입방 조직(cubic texture) 을 나타내는 단계.

BARRIER LAYERS COMPRISING NI-INCLUSIVE ALLOYS AND/OR OTHER METALLIC ALLOYS,DOUBLE BARRIER LAYERS, COATED ARTICLES INCLUDING DOUBLE BARRIER LAYERS, AND METHODS OF MAKING THE SAME

Ni-BASE ALLOY-HIGH CHROMIUM STEEL STRUCTURE AND PROCESS FOR PRODUCING THE NI-BASE ALLOY-HIGH CHROMIUM STEEL STRUCTURE

Disclosed is a process for producing a Ni-base alloy-high chromium steel structure. In the process, in order to maintain the strength of a joint formed by welding between a Ni-base alloy and a high chromium steel, at least two first members formed of a Ni-base alloy are joined to each other by welding to form a first assembly. The first assembly is subjected to first aging treatment. A second member formed of a high chromium steel is joined by welding to the first assembly comprising the first members connected to each other. Thereafter, the first assembly comprising the first members connected to each other is subjected to second aging treatment, and the welded part between the first member and the second member is subjected to post-welding heat treatment. COPYRIGHT KIPO & WIPO 2010 ...

SINGLE CRYSTAL NICKEL-BASED SUPERALLOY

ALLOY, PROTECTIVE LAYER AND COMPONENT

Known protective layers having a high Cr-content and a silicone in addition, form brittle phases that embrittle further under the influence of carbon during use. The protective layer according to the invention is composed of 22% to 26% cobalt (Co), 10.5% to 12% aluminum (AI), 0.2% to 0.4% Yttrium (Y) and/or at least one equivalent metal from the group comprising Scandium and the rare earth elements, 15% to 16% chrome (Cr), optionally 0.3% to 1.5% tantal, the remainder nickel (Ni).

METHOD AND DEVICE FOR GENERATIVELY PRODUCING AT LEAST ONE COMPONENT AREA

The invention relates to a method for generatively producing or for repairing at least one area of a component, wherein a zone arranged downstream of a molten bath is post-heated to a post-heating temperature and the component is set to a base temperature. The invention further relates to a device for carrying out such a method.

NICKEL-BASED BRAZING ALLOY AND METHOD FOR BRAZING

Nickel-based brazing alloy and method for brazing Brazing alloy with a composition consisting essentially of FeaNiRestCrbMocCudSi eBfPg, wherein 0 atomic % <= a <= 50 atomic %; 5 atomic % <= b <= 18 atomic %; 0.2 atomic % < c <= 3 atomic %; 4 atomic % <= e <= 15 atomic %; 4 atomic % <= f <= 15 atomic %; 0 atomic % <= g <= 6 atomic %; rest Ni, and wherein if 0 atomic % < a <= 50 atomic %; then 0.5 atomic % <= d < 3 atomic % and if a=0, then 0.5 atomic % <= d <= 5 atomic %.

Nickel base superalloys and turbine components fabricated therefrom

A nickel base superalloy suitable for the production of a large, crack-free nickel-base superalloy gas turbine bucket suitable for use in a large land-based utility gas turbine engine, comprising, by weight percents: Chromium 7.0 to 12.0 Carbon 0.06 to 0.10 Cobalt 5.0 to 15.0 Titanium 3.0 to 5.0 Aluminum 3.0 to 5.0 Tungsten 3.0 to 12.0 Molybdenum 1.0 to 5.0 Boron 0.0080 to 0.01 Rhenium 0 to 10.0 Tantalum 2.0 to 6.0 Columbium 0 to 2.0 Vanadium 0 to 3.0 Hafnium 0 to 2.0 and remainder nickel and incidental impurities.

Material having a high magnetic permeability

A material having a high magnetic permeability made by a basic composition consisting of 75-82 weight percent of nickel, 2-6 weight percent of molybdenum, 1 or less weight percent of manganese, 1 or less weight percent of silicon and the remainder iron, and by an additive consisting of at least two different types of elements, one of which types of elements being an element selected from a first group of elements consisting of zirconium, vanadium, tantalum, chromium and tungsten, and the other being at least one element selected from a second group of elements consisting of titanium, zirconium, vanadium, niobium, tantalum, chromium and tungsten but different from said an element of the first group, said additive being contained in said material in an amount within the range of 1-8 weight percent. This material exhibits a high mechanical strength, and a high resistance to wear due to friction and a high magnetic permeability.

Method for isothermal brazing of single crystal components

A process of brazing cracks and gaps in a single crystal article which takes places isothermally under the following conditions: the temperature of the isothermal solidification is between TLiqidus, Braze+5*(wt-%BBraze) and (Tsolidus, base material-70*(wt-%BBraze)), while (wt-%B*wt-%Cr) is between 15 and 40 and (Tsolv.gamma', base material-TLiqidus, Braze) is above 140° C. This results in an homogeneous gamma/gamma'-microstructure of the isothermal solidified, brazed joint with mechanical properties similar to those of the base material.

BARRIER LAYERS COMPRISING NI-INCLUSIVE ALLOYS AND/OR OTHER METALLIC ALLOYS, DOUBLE BARRIER LAYERS, COATED ARTICLES INCLUDING DOUBLE BARRIER LAYERS, AND METHODS OF MAKING THE SAME

Certain example embodiments relate to Ni-inclusive ternary alloy being provided as a barrier layer for protecting an IR reflecting layer comprising silver or the like. The provision of a barrier layer comprising nickel, chromium, and/or molybdenum and/or oxides thereof may improve corrosion resistance, as well as chemical and mechanical durability. In certain examples, more than one barrier layer may be used on at least one side of the layer comprising silver. In still further examples, a NixCryMoz-based layer may be used as the functional layer, rather than or in addition to as a barrier layer, in a coating.

Inertia friction weld of superalloy with enhanced post weld heat treatment

A method of inertia friction welding a superalloy substrate, the method including: rotating and forcing a deposit material (110) against the superalloy substrate (100); plastically deforming at least one of the deposit material (110) and the superalloy substrate (100) to form a weld joining the deposit material (110) to the superalloy substrate (100), thereby forming an assembly; and heat-treating the assembly. Heat-treating includes: a post-weld intermediate stress-relief (ISR) treatment; a solutionizing treatment; and a precipitation hardening heat treatment.

Casting method and cast article

A casting method and cast article are provided. The casting method includes providing a casting furnace, the casting furnace including a withdrawal region in a lower end, positioning a mold within the casting furnace, positioning a molten material in the mold, partially withdrawing the mold a withdrawal distance through the withdrawal region in the casting furnace, the withdrawal distance providing a partially withdrawn portion, then reinserting at least a portion of the partially withdrawn portion into the casting furnace through the withdrawal region, and then completely withdrawing the mold from the casting furnace. The reinserting at least partially re-melts a solidified portion within the partially withdrawn portion to reduce or eliminate freckle grains. The cast article includes a microstructure and occurrence of freckle grains corresponding to being formed by a process comprising partially withdrawing, reinserting, and completely withdrawing of a mold from a casting furnace to form ...

Ni-Base Superalloy and Gas Turbine Component Using the Same

A Ni-base superalloy of the present invention essentially includes, by weight %, Co: 9 to 11%, Cr: 9 to 12%, Mo: up to 1%, W: 6 to 9%, Al: 4 to 5%, Ti: 4 to 5%, Nb: up to 1%, Ta: up to 3%, Hf: 0.5 to 2.5%, Re: up to 3%, C: 0.05 to 0.15%, B: 0.005 to 0.015%, Zr: up to 0.05%, and the balance of Ni and inevitable impurities. This alloy, as a component material of an industrial gas turbine, has an excellent resistance to corrosion at high temperatures to deal with low-quality fuel and a resistance to oxidation at high temperatures and high-temperature strength to deal with improvement in thermal efficiency due to high-temperature demands and can ensure a high yield at a casting process.

Solder material for soldering components

The invention relates to a method for repairing components that consist of superalloys, in particular for repairing components that consist of a superalloy with an aligned microstructure in such a way that the repaired site likewise has an aligned microstructure. The method comprises the following steps: a solder material is applied to the repair site; the repair site with the applied solder material is heated until the latter melts; and the melted solder material is left to solidify. The solder material is an alloy with the same alloy components as the component alloy. At least the fraction of one alloy component in the solder material composition is modified in relation to the fraction of that alloy component in the component alloy composition, in such a way that the melting temperature of the solder material is reduced in relation to the melting temperature of the component alloy.

Additively manufacturing components containing nickel alloys, and feedstocks for producing the same

Some variations provide an additively manufactured metal-containing component comprising (i) nickel, (ii) aluminum and/or titanium, and (iii) nanoparticles, wherein the sum of aluminum weight percentage and one-half of titanium weight percentage is at least 3 on a nanoparticle-free basis, and wherein the additively manufactured metal-containing component has a microstructure that is substantially crack-free with equiaxed grains. A feedstock composition is also provided, comprising metal-containing microparticles and nanoparticles, wherein the nanoparticles are chemically and/or physically disposed on surfaces of the microparticles, wherein the microparticles comprise (i) nickel and (ii) aluminum and/or titanium, and wherein the sum of aluminum weight percentage and one-half of titanium weight percentage is at least 3 on a nanoparticle-free basis. The nanoparticles may be selected from metals; ceramics; cermets; intermetallic alloys; oxides, carbides, nitrides, borides, or hydrides thereof ...

METALLIC BONDCOAT OR ALLOY WITH A HIGH y/y' TRANSITION TEMPERATURE AND A COMPONENT

WELD FILLER FOR WELDING DISSIMILAR ALLOY STEELS AND METHOD OF USING SAME

Low rhenium single crystal superalloy for turbine blades and vane applications

A low rhenium nickel-base superalloy for single crystal casting that exhibits excellent high temperature creep resistance, while also exhibiting other desirable properties for such alloys, comprises 5.60% to 5.80% aluminum by weight, 9.4% to 9.9% cobalt by weight, 4.9% to 5.5% chromium by weight, 0.08% to 0.35% hafnium by weight, 0.50% to 0.70% molybdenum by weight, 1.4% to 1.6% rhenium by weight, 8.1% to 8.5% tantalum by weight, 0.60% to 0.80 titanium by weight, 7.6 to 8.0% tungsten by weight the balance comprising nickel and minor amounts of incidental impurity elements.

Nickle-based superalloys and articles

Rhenium-free nickel based alloys are provided. More particularly, the alloys comprise preferred levels and ratios of elements so as to achieve good high temperature strength of both gamma matrix phase and gamma prime precipitates, as well as good environmental resistance, without using rhenium. When cast and directionally solidified into single crystal form, the alloys exhibit creep resistance substantially equivalent to rhenium-bearing single-crystal alloys. Further, the alloys can be processed by directional solidification into articles in single crystal form or columnar structure comprising fine dendrite arm spacing, e.g., less than 400 µm, if need be, so that further improvements in mechanical properties in the articles can be seen.

High-strength and high-ductility ni-base superalloys, parts using them, and method of producing the same

Ni-BASE DIRECTIONALLY SOLIDIFIED SUPERALLOY AND Ni-BASE SINGLE CRYSTAL SUPERALLOY

Nickel base superalloy articles with improved resistance to crack propagation

METHOD FOR REPAIRING SUBSTRATES

SUPERALLOY FOR SINGLE CRYSTAL TURBINE VANE

PROBLEM TO BE SOLVED: To provide a superalloy which has excellent high temperature mechanical properties, and is useful for casting a single crystal turbine vane. SOLUTION: The nickel based superalloy that is useful for making single crystal castings exhibiting outstanding stress-rupture properties, creep-rupture properties, and an increased tolerance for grain defects comprises, by weight, about 4.7 to about 4.9% chromium (Cr), about 9 to about 10% cobalt (Co), about 0.6 to about 0.8% molybdenum (Mo), about 8.4 to about 8.8% tungsten (W), about 4.3 to about 4.8% tantalum (Ta), about 0.6 to about 0.8% titanium (Ti), and about 5.6 to about 5.8% aluminum (Al). The superalloy further comprises about 2.8 to about 3.1% rhenium (Re), about 1.1 to about 1.5% hafnium (Hf), about 0.06 to about 0.08% carbon (C), about 0.012 to about 0.020% boron (B), and about 0.004 to about 0.010% zirconium (Zr), and the balance being nickel with inevitable impurities. COPYRIGHT: (C)2004,JPO ...

ВЫСОКОТЕМПЕРАТУРНЫЙ Ni-Mo-Cr СПЛАВ С НИЗКИМ ТЕПЛОВЫМ РАСШИРЕНИЕМ

Изобретение относится к области металлургии, а именно к сплавам на основе никель-молибден-хром-вольфрам, работающим при повышенных температурах и пригодным для применения в газотурбинных двигателях. Сплав на основе никеля-молибдена-хрома-вольфрама содержит, вес.%: от 7 до 9 хрома, от 21 до 24 молибдена, более 5 вольфрама, до 3 железа, никель и примеси: алюминий, кобальт, медь, марганец, ниобий, кремний, тантал, титан и ванадий - остальное. Сплав после термической обработки при температуре 760°С (1400°F) имеет твердость по Роквеллу по меньшей мере 23. Сплав характеризуется низким коэффициентом теплового расширения, высокими характеристиками устойчивости к окислению и прочности вплоть до 760°С. 4 н. и 11 з.п. ф-лы, 3 ил., 10 табл.

БАРЬЕРНЫЕ СЛОИ, ВКЛЮЧАЮЩИЕ Ni-СОДЕРЖАЩИЕ ТРОЙНЫЕ СПЛАВЫ, ПОКРЫТЫЕ ИЗДЕЛИЯ, ВКЛЮЧАЮЩИЕ БАРЬЕРНЫЕ СЛОИ, И СПОСОБЫ ИХ ИЗГОТОВЛЕНИЯ

Изобретение относится к изделию с низкоизлучательным покрытием. Технический результат изобретения заключается в повышении долговечности низкоизлучательного покрытия. На стекло наносят слои в следующей последовательности: первый диэлектрический слой, первый барьерный слой, слой, отражающий ИК-излучение и содержащий серебро, второй барьерный слой, второй диэлектрический слой. Барьерные слои содержат, мас.%: Ni 54-58, Cr 20-22.5, Mo 12.5-14.5. 2 н. и 7 з.п. ф-лы, 16 ил., 3 табл.

Сплав с высокой стойкостью к окислению и применения для газовых турбин с использованием этого сплава

Изобретение относится к области металлургии, а именно к сплавам на основе никеля с высокой стойкостью к окислению и может быть использовано для изготовления компонентов газовой турбины с использованием аддитивных технологий. Сплав с высокой стойкостью к окислению содержит, в мас.%: Co 9,00-9,50; W 9,30-9,70; Cr 8,00-8,70; Al от более 7,00 до 15,50; Ti 0,60-0,90; Ta 2,80-3,30; Mo 0,40-0,60; Hf вплоть до 1,20; Mn вплоть до 0,05; Si вплоть до 0,02; C вплоть до 0,065; Re 0,00-4,00; Mg, B, Zr, Fe, O, N, S или их смеси вплоть до 0,287; Ni остальное. Сплав характеризуется высокой стойкостью к окислению. 3 н. и 12 з.п. ф-лы, 2 пр., 3 ил.

Жаропрочный никелевый сплав для дисков газотурбинных двигателей

Изобретение относится к металлургии, а именно к жаропрочным никелевым сплавам, предназначенным для изготовления высоконагруженных роторных деталей, в частности дисков газотурбинных двигателей, работающих в условиях активного воздействия статических и динамических нагрузок при температурах до 800-850°С. Жаропрочный никелевый сплав содержит, мас.%: углерод 0,05-0,1, хром 6,0-10,0, кобальт 16,0-20,0, вольфрам 4,0-7,0, молибден 3,0-5,0, титан 3,0-5,0, алюминий 3,0-5,0, ниобий 2,0-3,5, тантал 3,0-6,0, гафний 0,05-0,5, ванадий 0,5-1,5, марганец 0,05-0,3, бор 0,005-0,05, цирконий 0,001-0,05, скандий 0,01-0,1, магний 0,001-0,05, церий 0,01-0,05, лантан 0,01-0,05, иттрий 0,01-0,05, никель - остальное. Сплав характеризуется высокой устойчивостью к деформации. 3 з.п. ф-лы, 2 табл.

Литейный жаропрочный никелевый сплав с монокристаллической структурой

Изобретение относится к области металлургии - к производству литейных жаропрочных никелевых сплавов, предназначенных для литья лопаток и других ответственных деталей газовых турбин, имеющих монокристальную структуру. Литейный жаропрочный никелевый сплав с монокристаллической структурой содержит углерод, хром, кобальт, вольфрам, молибден, алюминий, тантал, рений, бор, церий, лантан, иттрий, магний, отличается тем, что он дополнительно содержит гафний, марганец, кремний, скандий, титан, ниобий, цирконий при следующем соотношении компонентов, мас.%: углерод 0,002-0,1, хром 2,8-6,0, кобальт 3,0-6,5, вольфрам 2,0-5,0, молибден 1,5-3,5, алюминий 5,4-6,3, титан 0,1-1,2, ниобий 0,1-1,0, тантал 7,2-9,0, гафний 0,1-0,3 рений 4,3-7,0, бор 0,005-0,01, цирконий 0,005-0,03, церий 0,001-0,1, лантан 0,001-0,1, иттрий 0,001-0,1, магний 0,01-0,03, марганец 0,01-0,2, кремний 0,01-0,2, скандий 0,005-0,03, никель - остальное, при соблюдении следующих условий: 44,2≥3,0CMo+1,6CW+2,3CTa+1,3CRe+10,0CHf, где СМо ...

Barrier layers comprising Ni-inclusive ternary alloys, coated articles including barrier layers, and methods of making the same

Certain example embodiments relate to Ni-inclusive ternary alloy being provided as a barrier layer for protecting an IR reflecting layer comprising silver or the like. The provision of a barrier layer comprising nickel, chromium, and/or molybdenum and/or oxides thereof may improve corrosion resistance, as well as chemical and mechanical durability. In certain examples, more than one barrier layer may be used on at least one side of the layer comprising silver. In still further examples, a Ni x Cr y Mo z -based layer may be used as the functional layer, rather than or in addition to as a barrier layer, in a coating.

Alumina-Forming Cobalt-Nickel Base Alloy and Method of Making an Article Therefrom

A cobalt-nickel base alloy is disclosed. The alloy includes, in weight percent: greater than about 4% of Al, about 10 to about 20% of W, about 10 to about 40% Ni, about 5 to 20% Cr and the balance Co and incidental impurities. The alloy has a microstructure that is substantially free of a CoAl phase having a B2 crystal structure and configured to form a continuous, adherent aluminum oxide layer on an alloy surface upon exposure to a high-temperature oxidizing environment. A method of making an article of the alloy includes: selecting the alloy; forming an article from the alloy; solution-treating the alloy; and aging the alloy to form an alloy microstructure that is substantially free of a CoAl phase having a B2 crystal structure, wherein the alloy is configured to form a continuous, adherent aluminum oxide layer on an alloy surface upon exposure to a high-temperature oxidizing environment.

Method for limiting surface recrystallization

A method to limit surface zone recrystallization in a superalloy article includes limiting recrystallization in a surface zone of a superalloy article by treating the superalloy article in an oxygen-containing environment to introduce oxygen into the surface zone in an amount sufficient to pin any new grain boundaries in the surface zone.

NICKEL-BASED ALLOY

Nickel-based alloy consisting of (in % by mass) Si 0.8-2.0%, Al 0.001-0.1%, Fe 0.01-0.2%, C 0.001-0.10%, N 0.0005-0.10%, Mg 0.0001-0.08%, O 0.0001-0.010%, Mn max. 0.10%, Cr max. 0.10%, Cu max. 0.50%, S max. 0.008%, balance Ni and the usual production-related impurities. 1. Nickel-based alloy , consisting of (in % by mass)Si 0.8-2.0%Al 0.001 to 0.1%Fe 0.01 to 0.2%C 0.001-0.10%N 0.0005-0.10%Mg 0.0001-0.08%O 0.0001 to 0.010%Mn max. 0.10%Cr max. 0.10%Cu max. 0.50%S max. 0.008%Ni remainder, and the usual production-related contaminants.2. Alloy according to claim 1 , with a Si content (in % by mass) of 0.8 to 1.5%.3. Alloy according to claim 1 , with a Si content (in % by mass) of 0.8 to 1.2%.4. Alloy according to claim 1 , with an Al content (in % by mass) of 0.001 to 0.05%.5. Alloy according to claim 1 , with an Fe content (in % by mass) of 0.01 to 0.10%.6. Alloy according to claim 1 , with an Fe content (in % by mass) of 0.01 to 0.05%.7. Alloy according to claim 1 , with a C content (in % by mass) of 0.001 to 0.05% and an N content (in % by mass) of 0.001 to 0.05%.8. Alloy according to claim 1 , with a Mg content (in % by mass) of 0.005 to 0.08%.9. Alloy according to claim 1 , with a Ca content (in % by mass) of 0.0002 to 0.06%.10. Alloy according to claim 1 , with an O content (in % by mass) of 0.0001 to 0.008%.11. Alloy according to claim 1 , with a Mn content (in % by mass) of max. 0.05% and with a Cr content (in % by mass) of max. 0.05%.12. Alloy according to claim 1 , with an Y content (in % by mass) of 0.03 to 0.20%.13. Alloy according to claim 1 , with an Y content (in % by mass) of 0.05 to 0.15%.14. Alloy according to claim 1 , with a Hf content (in % by mass) of 0.03 to 0.25%.15. Alloy according to claim 1 , with a Hf content (in % by mass) of 0.03 to 0.15%.16. Alloy according to claim 1 , with a Zr content (in % by mass) of 0.03 to 0.15%.17. Alloy according to claim 1 , with a Ce content (in % by mass) of 0.03 to 0.15%.18. Alloy according to claim 1 , with a ...

METAL-BASE ALLOY PRODUCT AND METHODS FOR PRODUCING THE SAME

A metal base alloy and methods for producing the alloy. The metal base alloy product includes the formula MeTSiCrMnj VCf, wherein—Meis a metal base selected from the group having Fe, Co and Ni, in an amount ranging from about 45-75 w %. The metal base alloy product contains a substantially homogenous dispersion of separate precipitated carbide particles in an amount ranging from 10-65 percentages by volume and the precipitate carbide particles have an average diameter of 0.01-5 micrometers. 2. Metal base alloy product according to wherein said precipitated carbide particles are substantially spherical carbides having an average diameter of 0.1-5 micrometer.3. Metal base alloy according to claim 1 , wherein said precipitated carbide particles are a mixture of substantially spherical carbides having an average diameter of 0.5-5 micrometer and of nano-crystalline carbides having an average size of 0.01-0.5 micrometer.4. Metal base alloy according to claim 1 , wherein said precipitated carbide particles are surrounded by a matrix of ferrite and/or austenite.5. Metal base alloy according to claim 1 , wherein said alloy has a tensile strength of at least about 800 MPa.6. A metal base alloy according to claim 1 , wherein the Meis Fe present in an amount from about 45-75 w %.7. A metal base alloy according to claim 1 , wherein the Tis Mo present in an amount from about 5-10 w %.8. A method to produce a metal base alloy product consisting of the formula MeTSiCrMnVC claim 1 , wherein{'sub': 'base', 'Meis a metal base selected from the group consisting of Fe, Co and NI, in an amount ranging from about 45-75 w %,'}{'sub': 'a', 'Tis an alloying material selected from the group consisting of Mo, Nb and Ta in an amount a ranging from about 5-10 w %,'}{'sub': 'b', 'Siis a further alloying member in an amount b ranging from about 4-10 w %,'}{'sub': 'c', 'Cris a further alloying member in an amount c ranging from about 8-30 w %,'}{'sub': 'd', 'Mnis a further alloying member in an ...

CO-BASED ALLOY

A Co-based alloy containing not less than 0.001 mass % and less than 0.100 mass % of C, not less than 9.0 mass % and less than 20.0 mass % of Cr, not less than 2.0 mass % and less than 5.0 mass % of Al, not less than 13.0 mass % and less than 20.0 mass % of W, and not less than 39.0 mass % and less than 55.0 mass % of Ni, with the remainder being made up by Co and unavoidable impurities, wherein the contents of Mo, Nb, Ti and Ta which are included in the unavoidable impurities are as follows: Mo<0.010 mass %, Nb<0.010 mass %, Ti<0.010 mass %, and Ta<0.010 mass %. 1. A Co-based alloy comprising:not less than 0.001 and less than 0.100 mass % of C;not less than 9.0 and less than 20.0 mass % of Cr;not less than 2.0 and less than 5.0 mass % of Al;not less than 13.0 and less than 20.0 mass % of W;not less than 39.0 and less than 55.0 mass % of Ni; andthe balance being Co and inevitable impurities, wherein the impurities includeless than 0.010 mass % of Mo,less than 0.010 mass % of Nb,less than 0.010 mass % of Ti, andless than 0.010 mass % of Ta.2. The Co-based alloy according to claim 1 , further comprising at least one ofnot less than 0.0001 and less than 0.020 mass % of B andnot less than 0.0001 and less than 0.10 mass % of Zr.3. The Co-based alloy according to claim 1 , further comprising at least one ofnot less than 0.0001 and less than 0.10 mass % of Mg andnot less than 0.0001 and less than 0.20 mass % of Ca.4. The Co-based alloy according to claim 1 , produced through hot working claim 1 , solution treatment and aging treatment claim 1 , the alloy{'sub': '2', 'comprising a γ phase matrix, carbide precipitated in the matrix, and a γ′ phase composed of an L1-type intermetallic compound.'} The present invention relates to a Co-based alloy suitable for various components required to have a high strength in a high-temperature environment, such as for a gas turbine, an aircraft engine, a chemical plant, a vehicle engine and a high-temperature furnace. In particular, it ...

NICKEL BASE SUPERALLOY COMPOSITIONS BEING SUBSTANTIALLY FREE OF RHENIUM AND SUPERALLOY ARTICLES

A nickel base superalloy composition substantially free of rhenium includes, in percentages by weight: about 5-8 Cr; about 7-8 Co; about 1.3-2.2 Mo; about 4.75-6.75 W; about 6.0-7.0 Ta; if present, up to about 0.5 Ti; about 6.0-6.4 Al; about 0.15-0.6 Hf; if present, from about 0.03-0.06 C; if present, up to about 0.004 B; if present, one or more rare earths selected from Y, La, and Ce up to about 0.03 total, the balance including nickel and incidental impurities. The superalloy composition is able to provide sustained-peak low cycle fatigue and/or oxidation resistance properties comparable to second generation superalloy compositions including at least about 3 wt % rhenium. Superalloy articles incorporating the compositions include nozzles, shrouds, and splash plates for gas turbine engines. 1. A nickel base superalloy composition consisting of , in percentages by weight:about 5-6 Cr;about 7-8 Co;about 1.5 Mo;about 6 W;about 6.0-7.0 Ta;if present, up to about 0.5 Ti;about 6.0-6.4 Al;about 0.15-0.6 Hf;if present, from about 0.03-0.06 C;if present, up to about 0.004 B;if present, one or more rare earths selected from Y, La, and Ce up to about 0.03 total;wherein the superalloy composition is substantially free of Re and exhibits a sustained-peak low cycle fatigue resistance exceeding 10,500 cycles to failure at 2000° F./18 ksi APS;the balance of the superalloy composition being nickel and incidental impurities.2. The nickel base superalloy composition according to being characterized by a P-value of less than 3360 claim 1 , wherein the P-value is defined as: P=−200 Cr+80 Mo−20 Mo−250 Ti−50 (Ti×Ta)+15 Cb+200 W−14 W+30 Ta−1.5 Ta+2.5 Co+1200 Al −100 Al+100 Re+1000 Hf−2000 Hf+700 Hf−2000 V−500 C−15000 B−500 Zr.3. The nickel base superalloy composition according to being characterized by a P-value of less than 3050.4. The nickel base superalloy composition according to wherein the superalloy composition is in the form of a single crystal article.5. The nickel base ...

METALLIC BONDCOAT OR ALLOY WITH A HIGH GAMMA/GAMMA' TRANSITION TEMPERATURE AND A COMPONENT

A metallic coating or alloy is provided, which is nickel based, and includes at least γ and γ′ phases. The metallic coating or the alloy further includes tantalum (Ta) in the range of between 4 wt % to 7.5 wt %. The metallic coating or the alloy also includes cobalt (Co) in the range between 11 wt %-14.5 wt %. 115-. (canceled)16. A metallic coating or alloy ,wherein the metallic coating or alloy is nickel based,wherein the metallic coating or alloy comprises at least γ and γ′ phases,wherein the metallic coating or the alloy further comprises tantalum (Ta) in the range of between 4 wt % to 7.5 wt %,wherein the metallic coating or the alloy further comprises cobalt (Co) in the range between 11 wt %-14.5 wt %.17. The metallic coating or alloy according to claim 16 , wherein the amount of tantalum (Ta) is in the range between 5 wt % and 6.8 wt %.18. The metallic coating or alloy according to claim 17 , wherein the amount of tantalum (Ta) is 6 wt %.19. The metallic coating or alloy according to claim 16 , wherein the amount of cobalt (Co) is in the range between 12 wt %-14 wt %.20. The metallic coating or alloy according to claim 19 , wherein the amount of cobalt (Co) is 13 wt %.21. The metallic coating or alloy according to claim 16 , wherein the metallic coating or alloy contains no Yttrium (Y) and/or no platinum (Pt) and/or no melting depressant.22. The metallic coating or alloy according to claim 16 , further comprising chromium (Cr) claim 16 , wherein the amount of chromium (Cr) is between 14 t %-16 wt %.23. The metallic coating or alloy according to claim 16 , further comprising aluminum claim 16 , wherein the amount of aluminum (Al) is between 9 wt %-13 wt %.24. The metallic coating or alloy according to claim 16 , further comprising yttrium claim 16 , wherein the amount of yttrium (Y) is between 0 claim 16 ,1 wt %-0 claim 16 ,7 wt %.25. The metallic coating or alloy according to claim 16 , wherein the metallic coating or the alloy contains no rhenium (Re).26. The ...

Layer system comprising an nicocraly double protective layer with differing chromium content and alloy

A two-layered NiCoCrAlY layer is provided. The layer includes a bottom and a top layer. Through the use of a two-layered NiCoCrAlY layer, it is possible to reduce the formation of cracks in the thermally grown oxide layer as forms on account of the protective action of the NiCoCrAlY layers.

Oxidation-Resistant Coated Superalloy

A coating-substrate combination includes: a Ni-based superalloy substrate comprising, by weight percent: 2.0-5.1 Cr; 0.9-3.3 Mo; 3.9-9.8 W; 2.2-6.8 Ta; 5.4-6.5 Al; 1.8-12.8 Co; 2.8-5.8 Re; 2.8-7.2 Ru; and a coating comprising, exclusive of Pt group elements, by weight percent: Ni as a largest content; 5.8-9.3 Al; 4.4-25 Cr; 3.0-13.5 Co; up to 6.0 Ta, if any; up to 6.2 W, if any; up to 2.4 Mo, if any; 0.3-0.6 Hf; 0.1-0.4 Si; up to 0.6 Y, if any; up to 0.4 Zr, if any; up to 1.0 Re, if any. 1. An article comprising:a Ni-based superalloy substrate comprising, by weight percent: 2.0-5.1 Cr; 0.9-3.3 Mo; 3.9-9.8 W; 2.2-6.8 Ta; 5.4-6.5 Al; 1.8-12.8 Co; 2.8-5.8 Re; 2.8-7.2 Ru; anda coating comprising, exclusive of Pt group elements, by weight percent: Ni as a largest content; 5.8-9.3 Al; 4.4-25 Cr;3. 0-13.5 Co; up to 6.0 Ta , if any; up to 6.2 W , if any; up to 2.4 Mo , if any; 0.3-0.6 Hf; 0.1-0.4 Si; up to 0.6 Y , if any; up to 0.4 Zr , if any; up to 1.0 Re , if any.2. The article of wherein:the substrate comprises 0.05-0.7 weight percent Hf.3. The article of wherein:the substrate has a 1800° F. & 45 ksi (982° C. & 310 MPa) rupture life of at least 120 hours.4. The article of wherein:the coating comprises exclusive of Pt group elements, by weight percent: 0.4-0.6 said Hf; 0.2-0.4 said Si.5. The article of wherein:the coating has less than 1.0 weight percent overall said Pt group elements combined.6. The article of wherein:in weight percent exclusive of Pt group elements, the coating has less than 1.0 weight percent individually elements other than said Ni, Al, Cr, Co, Ta, W, Mo, Hf, Si, Y, Zr, Re, and Pt group elements, if any.7. The article of wherein:the substrate also falls within one of the broader ranges of Table VI; andthe coating also falls within the associated broader range of Table VII.8. The article of wherein:the coating and substrate fall within the narrower associated ranges.9. The article of wherein:in weight percent the coating has 6.0≤W+Ta≤13.0 or Ta+W≤0.05 ...

Abrasive Coating and Manufacture and Use Methods

A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; an abrasive; and a matrix in which the abrasive is at least partially embedded; and heating to cause the self-braze material to braze to the substrate. The heating leaves at least a portion of the self-braze material with a composition comprising, in weight percent: cobalt 2.5-13.5; chromium 12-27; aluminum 5-7; yttrium 0.0-1.0; hafnium 0.0-1.0; silicon 1.0-3.0; tantalum 0.0-4.5; tungsten 0.0-6.5; rhenium 0.0-2.0; molybdenum 0.1-1.0; and the balance nickel. 1. A method for applying an abrasive , the method comprising: a self-braze material;', 'an abrasive; and', 'a matrix in which the abrasive is at least partially embedded; and, 'applying, to a substrate, the integral combination of cobalt 2.5-13.5;', 'chromium 12-27;', 'aluminum 5-7;', 'yttrium 0.0-1.0;', 'hafnium 0.0-1.0;', 'silicon 1.0-3.0;', 'tantalum 0.0-4.5;', 'tungsten 0.0-6.5;', 'rhenium 0.0-2.0;', 'molybdenum 0.1-1.0; and', 'the balance nickel., 'heating to cause the self-braze material to braze to the substrate, the heating leaving at least a portion of the self-braze material with a composition comprising, in weight percent2. The method of wherein: cobalt 2.5-13.5;', 'chromium 12-27;', 'aluminum 5-7;', 'yttrium 0.0-1.0;', 'hafnium 0.0-1.0;', 'silicon 1.0-3.0;', 'tantalum 2.0-4.5;', 'tungsten 2.0-6.5;', 'rhenium 0.0-2.0;', 'molybdenum 0.1-1.0; and', 'the balance nickel., 'said portion of the self-braze material has said composition comprising, in weight percent3. The method of wherein:said composition has no more than 1.0 weight percent of any other individual element.4. The method of wherein:said composition has no more than 3.0 weight percent of all other individual elements combined.5. The method of wherein:the matrix comprises an MCrAlY; andthe abrasive comprises cubic boron nitride.6. The method of wherein the self-braze material comprises a sintered sheet of:at least one first ...

Abrasive Coating and Manufacture and Use Methods

A method for applying an abrasive comprises: applying, to a substrate, the integral combination of a self-braze material, an abrasive, a matrix in which the abrasive is at least partially embedded, and an intermediate layer between the self-braze material and the matrix; and heating to cause the self-braze material to braze to the substrate. 1. A method for applying an abrasive , the method comprising:applying, to a substrate, the integral combination of:a self-braze material;an abrasive;a matrix in which the abrasive is at least partially embedded; andan intermediate layer between the self-braze material and the matrix; andheating to cause the self-braze material to braze to the substrate.2. The method of wherein the intermediate layer is a cast layer.3. The method of wherein the heating leaves at least a portion of the self-braze material with a composition comprising claim 1 , in weight percent:cobalt 2.5-13.5;chromium 12-27;aluminum 5-7;yttrium 0.0-1.0;hafnium 0.0-1.0;silicon 1.0-3.0;tantalum 0.0-4.5;tungsten 0.0-6.5;rhenium 0.0-2.0;molybdenum 0.1-1.0; andthe balance nickel.4. The method of wherein:said portion of the self-braze material has said composition comprising, in weight percent:cobalt 2.5-13.5;chromium 12-27;aluminum 5-7;yttrium 0.0-1.0;hafnium 0.0-1.0;silicon 1.0-3.0;tantalum 2.0-4.5;tungsten 2.0-6.5;rhenium 0.0-2.0;molybdenum 0.1-1.0; andthe balance nickel.5. The method of wherein:said composition has no more than 1.0 weight percent of any other individual element.6. The method of wherein:said composition has no more than 3.0 weight percent of all other individual elements combined.7. The method of wherein:the matrix comprises an MCrAlY; andthe abrasive comprises cubic boron nitride.8. The method of wherein the self-braze material comprises a sintered sheet of:at least one first alloy of low melting point relative to the substrate; andat least one second alloy of high melting point relative to the first alloy.9. The method of wherein:the at least one ...

Abrasive Preforms and Manufacture and Use Methods

A method for applying an abrasive comprises: applying, to a substrate, the integral combination of: a self-braze material; and an abrasive embedded in the self-braze material; and securing the combination to the substrate. 1. A method for applying an abrasive , the method comprising: a self-braze material; and', 'an abrasive embedded in the self-braze material; and, 'applying, to a substrate, the integral combination ofsecuring the combination to the substrate.2. The method of wherein:the securing comprises heating to cause the self-braze material to braze to the substrate or an intervening component.3. The method of wherein the applying comprises applying an assembly of the combination and at least one additional braze material layer claim 1 , said additional braze material layer lacking abrasive.4. The method of wherein the assembly further comprises a cast intermediate layer.5. The method of wherein the self-braze material and the at least one additional braze material layer each comprise a mixture of alloys of different melting points.6. The method of wherein: cobalt 2.5-13.5;', 'chromium 12-27;', 'aluminum 5-7;', 'yttrium 0.0-1.0;', 'hafnium 0.0-1.0;', 'silicon 1.0-3.0;', 'tantalum 0.0-4.5;', 'tungsten 0.0-6.5;', 'rhenium 0.0-2.0;', 'molybdenum 0.1-1.0; and', 'the balance nickel., 'the securing comprises heating and leaves at least a portion of the self-braze material with a composition comprising, in weight percent7. The method of wherein: cobalt 2.5-13.5;', 'chromium 12-27;', 'aluminum 5-7;', 'yttrium 0.0-1.0;', 'hafnium 0.0-1.0;', 'silicon 1.0-3.0;', 'tantalum 2.0-4.5;', 'tungsten 2.0-6.5;', 'rhenium 0.0-2.0;', 'molybdenum 0.1-1.0; and', 'the balance nickel., 'said portion of the self-braze material has said composition comprising, in weight percent8. The method of wherein:said composition has no more than 1.0 weight percent of any other individual element.9. The method of wherein:said composition has no more than 3.0 weight percent of all other individual ...

ARTICLE AND ADDITIVE MANUFACTURING METHOD FOR MAKING

Additive manufacturing methods, and articles made using additive manufacturing methods, are described herein. One embodiment is an article that comprises a hafnium-bearing superalloy. The superalloy includes at least about 50 weight percent nickel, from about 0.015 weight percent to about 0.06 weight percent carbon, and up to about 0.8 weight percent hafnium. The article further includes a plurality of primary carbide phase particulates disposed within the superalloy; the plurality has a median size less than about 1 micrometer. A method includes melting and solidifying particulates of a metal powder feedstock to build an intermediate article comprising a series of layers of solidified material. The feedstock includes the above-described superalloy composition. The method further includes heating the intermediate article to a temperature of at least about 950 degrees Celsius to form a processed article. The processed article further includes a plurality of primary carbide phase particulates disposed within the solidified material, the plurality of particulates having a median size less than about 1 micrometer. 1. An article , comprising:a hafnium-bearing superalloy comprising at least about 50 weight percent nickel, from about 0.015 weight percent to about 0.06 weight percent carbon, and up to about 0.8 weight percent hafnium;wherein the article further comprises a plurality of primary carbide phase particulates disposed within the superalloy, the plurality of particulates having a median size less than about 1 micrometer.2. The article of claim 1 , wherein the superalloy further comprises a gamma prime phase that claim 1 , at a temperature in a range from about 700 degrees Celsius to about 800 degrees Celsius claim 1 , is present at a concentration of at least about 50 percent by volume of the superalloy.3. The article of claim 2 , wherein the concentration is at least about 60 percent by volume of the superalloy.4. The article of claim 1 , wherein the median size ...

MOLDING MACHINE CYLINDER AND ITS PRODUCTION METHOD

A molding machine cylinder comprising a lining layer having a structure comprising 20-50% by area of tungsten carbide particles and 1-10% by area of tungsten-based metal carboboride particles in a nickel-based alloy matrix, and containing 1-7.5% by mass of Fe, can be produced by a centrifugal casting method comprising a first step of heating at higher than 1140° C. and lower than 1200° C., and a second step of heating at 1080-1140° C. after melting the raw material powder. 1. A molding machine cylinder comprising a lining layer formed on an inner surface of a steel cylinder by a centrifugal casting method;said lining layer having a structure comprising 20-50% by area of tungsten carbide particles and 1-10% by area of tungsten-based metal carboboride particles in a nickel-based alloy matrix; andsaid lining layer containing 1-7.5% by mass of Fe.2. The molding machine cylinder according to claim 1 , wherein said metal carboboride particles contain 0.5-4% by mass of C claim 1 , 0.5-6% by mass of B claim 1 , 65-85% by mass of W claim 1 , and 1-20% by mass of Ni.3. The molding machine cylinder according to claim 1 , wherein said metal carboboride particles have an average particle size of 0.5-5 μm.4. The molding machine cylinder according to claim 1 , wherein said tungsten carbide particles have an average particle size of 1.5-15 μm.5. The molding machine cylinder according to claim 1 , wherein said lining layer comprises 1.5-4% by mass of C claim 1 , 0.5-3.5% by mass of B claim 1 , 25-60% by mass of W claim 1 , 1-10% by mass of Cr claim 1 , 1-15% by mass of Co claim 1 , 0.1-3% by mass of Si claim 1 , 0.1-2% by mass of Mn claim 1 , and 0-5% by mass of Cu claim 1 , the balance being nickel and inevitable impurities.6. The molding machine cylinder according to claim 5 , wherein a matrix of said lining layer comprises 0.05-1% by mass of C claim 5 , 0.5-3% by mass of B claim 5 , 1-5% by mass of W claim 5 , 2-20% by mass of Cr claim 5 , 2-30% by mass of Co claim 5 , 0.2-5% by ...

CASTING METHODS AND MOLDED ARTICLES PRODUCED THEREFROM

A method comprising introducing a first casting material into a casting mold; applying directional solidification to the first casting material in the casting mold; introducing a second casting material into the casting mold, the second casting material having a different chemical composition than the first casting material; applying directional solidification to the second casting material in the casting mold; and forming a molded article, wherein the molded article comprises a first region 120.-. (canceled)21. A molded article comprising:a first region formed by a first casting material; anda second region formed by mixing a molten or liquid portion of the first casting material and a second casting material,wherein the first casting material has a different chemical composition than the second casting material,wherein the first region and the second region are cast as one integral casting using directional solidification, andwherein the molded article has a lower concentration of impurities than were present in the first casting material and the second casting material.22. The molded article of claim 21 , wherein the molded article is a component in a gas turbine engine.231. The molded article of claim 21 , wherein the molded article is a stage bucket in a gas turbine engine.24. The molded article of claim 21 , wherein the molded article is a latter stage bucket in a gas turbine engine.25. The molded article of claim 24 , wherein the second region is a squealer tip.26. The molded article of claim 25 , wherein the second region is a tip shroud.27. The molded article of claim 21 , wherein the first region and the second region are each single crystal claim 21 , columnar claim 21 , equiaxed claim 21 , or a combination thereof.28. The molded article of claim 21 , wherein the interface between the first region and the second region is devoid of an oxidation layer.29. The molded article of claim 21 , wherein the molded article further comprises a third region formed by ...

Advanced bond coat

In some examples, an alloy may include less than 55 atomic percent aluminum; between about 10 and about 25 atomic percent of a platinum group metal; and a balance of nickel; at least one of chromium, silicon, tantalum, or cobalt; a reactive element; and diffusion impurities; where the alloy has a discrete gamma-prime Ni 3 Al region and a discrete beta NiAl region. In some examples, a coating system may include a substrate; a first layer including gamma-prime Ni 3 Al; and a second layer including beta NiAl, where the first region and the second region are discrete dual region.

METHOD OF MAKING A Ni-BASED SINGLE CRYSTAL SUPERALLOY AND TURBINE BLADE INCORPORATING SAME

The present invention provides a Ni-based single crystal superalloy which has the following composition by weight: 0.1 wt % or more and 9.9 wt % or less of Co, 5.1 wt % or more and 10.0 wt % or less of Cr, 1.0 wt % or more and 4.0 wt % or less of Mo, 8.1 wt % or more and 11.0 wt % or less of W, 4.0 wt % or more and 9.0 wt % or less of Ta, 5.2 wt % or more and 7.0 wt % or less of Al, 0.1 wt % or more and 2.0 wt % or less of Ti, 0.05 wt % or more and 0.3 wt % or less of Hf, 1.0 wt % or less of Nb and less than 3.0 wt % of Re with the remainder including Ni and unavoidable impurities. This Ni-based single crystal superalloy has a low Re content and also has excellent high-temperature strength, mainly creep strength.

Iambda/4 TYPE RADIO WAVE ABSORBER

The present invention aims to provide a λ/4 type radio wave absorber having excellent durability. Provided is a λ/4 type radio wave absorber including: a resistive film containing molybdenum; a resistive film; a dielectric layer; and a reflective layer, in the stated order. 1. A λ/4 type radio wave absorber comprising:a resistive film containing molybdenum;a dielectric layer; anda reflective layer, in the stated order.2. The λ/4 type radio wave absorber according to claim 1 ,wherein the resistive film comprises a barrier layer on at least one surface.3. The λ/4 type radio wave absorber according to claim 2 ,wherein the barrier layer has a thickness of 9 nm or less.4. The λ/4 type radio wave absorber according to claim 2 ,wherein the barrier layer contains an oxide or nitride of silicon, titanium, and copper.5. The λ/4 type radio wave absorber according to claim 1 ,wherein the resistive film further contains nickel and chromium.6. The λ/4 type radio wave absorber according to claim 5 ,wherein the resistive film contains molybdenum in an amount of 5% by weight or more, nickel in an amount of 40% by weight or more, and chromium in an amount of 1% by weight or more.7. The λ/4 type radio wave absorber according to claim 3 ,wherein the barrier layer contains an oxide or nitride of silicon, titanium, and copper.8. The λ/4 type radio wave absorber according to claim 2 ,wherein the resistive film further contains nickel and chromium.9. The λ/4 type radio wave absorber according to claim 3 ,wherein the resistive film further contains nickel and chromium.10. The λ/4 type radio wave absorber according to claim 7 ,wherein the resistive film further contains nickel and chromium.11. The λ/4 type radio wave absorber according to claim 4 ,wherein the resistive film further contains nickel and chromium.12. The λ/4 type radio wave absorber according to claim 8 ,wherein the resistive film contains molybdenum in an amount of 5% by weight or more, nickel in an amount of 40% by weight or ...

Highly processable single crystal nickel alloys

Alloys, processes for preparing the alloys, and articles including the alloys are provided. The alloys can include, by weight, about 4% to about 7% aluminum, 0% to about 0.2% carbon, about 7% to about 11% cobalt, about 5% to about 9% chromium, about 0.01% to about 0.2% hafnium, about 0.5% to about 2% molybdenum, 0% to about 1.5% rhenium, about 8% to about 10.5% tantalum, about 0.01% to about 0.5% titanium, and about 6% to about 10% tungsten, the balance essentially nickel and incidental elements and impurities.

HOT-DIE NI-BASED ALLOY, HOT-FORGING DIE EMPLOYING SAME, AND FORGED-PRODUCT MANUFACTURING METHOD

Provided are a Ni-based alloy for hot die having a high high-temperature compressive strength and a good oxidation resistance and being capable of suppressing the deterioration in the working environment and the shape deterioration, a hot forging die using the Ni-based alloy for hot die, and a method for manufacturing a forged product using the hot forging die. The present invention provides a hot forging die comprising a Ni-based alloy for hot die comprising, in mass %, W: 7.0 to 15.0%, Mo: 2.5 to 11.0%, Al: 5.0 to 7.5%, Cr: 0.5 to 7.5%, and the balance of Ni with inevitable impurities, wherein at least 80% of a surface area of the Ni-based alloy for hot die is covered with an aluminum oxide layer. In addition to the composition, the Ni-based alloy for hot die may further comprise 7.0% or less of Ta and may further comprise one or two or more elements selected from Zr: 0.5% or less, Hf: 0.5% or less, rare-earth elements: 0.2% or less, Y: 0.2% or less, and Mg: 0.03% or less. 1. A hot forging die comprising a Ni-based alloy for hot die comprising , in mass % , W: 7.0 to 15.0% , Mo: 2.5 to 11.0% , Al: 5.0 to 7.5% , Cr: 0.5 to 7.5% , and the balance of Ni with inevitable impurities , wherein at least 80% of a surface area of the Ni-based alloy for hot die is covered with an aluminum oxide layer.2. The hot forging die according to claim 1 , wherein the Ni-based alloy for hot die further comprises claim 1 , in mass % claim 1 , one or two or more elements selected from Zr: 0.5% or less claim 1 , Hf: 0.5% or less claim 1 , rare-earth elements: 0.2% or less claim 1 , Y: 0.2% or less claim 1 , and Mg: 0.03% or less.3. The hot forging die according to claim 1 , wherein the Ni-based alloy for hot die further comprises claim 1 , in mass % claim 1 , Ta: 7.0% or less.4. The hot forging die according to claim 2 , wherein the Ni-based alloy for hot die further comprises claim 2 , in mass % claim 2 , one or two elements selected from Ti and Nb in a total amount of 3.5% or less claim ...

Age-Hardening Process Featuring Anomalous Aging Time

This document describes a process/strategy for age hardening nickel based alloys to create desirable properties with reduced energy expenditure. The inventive process introduces isolated atom nucleation sites to accelerate the nucleation rate by approximately 36 times, thereby permitting age hardening to occur in significantly less time and with significantly less energy expenditure. 1. A method for achieving accelerated age hardening in a metal alloy while minimizing the risk of over-aging , comprising:a. providing a metal alloy containing nickel, molybdenum, chromium, and rhenium;b. wherein said rhenium comprises 3% to 10% of the total weight of said metal alloy;c. wherein nickel comprises the majority of said metal alloy by weight; and{'sub': '2', 'd. subjecting said metal alloy to an age hardening process that forms long-range-ordered precipitates of the form NiRe.'}2. A method for achieving accelerated age hardening in a metal alloy as recited in claim 1 , further comprising annealing said metal alloy before subjecting said metal alloy to said age hardening process.3. A method for achieving accelerated age hardening in a metal alloy as recited in claim 1 , wherein said molybdenum comprises at least 20% to 30% of the total weight.4. A method for achieving accelerated age hardening in a metal alloy as recited in claim 1 , wherein said age hardening is conducted at a temperature in excess of 800 K.5. A method for achieving accelerated age hardening in a metal alloy as recited in claim 1 , further comprising work hardening said metal alloy before subjecting said metal alloy to said age hardening process.6. A method for achieving accelerated age hardening in a metal alloy as recited in claim 2 , further comprising work hardening said metal alloy before subjecting said metal alloy to said age hardening process.7. A method for achieving accelerated age hardening in a metal alloy as recited in claim 3 , further comprising work hardening said metal alloy before ...

NICKEL-BASED ALLOY WITH SILICON, ALUMINUM, AND CHROMIUM

A nickel-based alloy, consisting of (in mass %) 1.5-3.0% Si, 1.5-3.0% Al, and >0.1-3.0% Cr, where Al+Si+Cr is ≧4.0 and ≦8.0 for the contents of Si, Al, and Cr in %; 0.005-0.20% Fe, 0.01-0.20% Y, and <0.001-0.20% of one or more the elements Hf, Zr, La, Ce, Ti, where Y+0.5*Hf+Zr+1.8*Ti 0.6*(La+Ce) is ≧0.02 and ≦0.30 for the contents of Y, Hf, Zr, La, Ce, and Ti in %; 0.001-0.10% C; 0.0005-0.10% N; 0.001-0.20% Mn; 0.0001-0.08% Mg; 0.0001-0.010% O; max. 0.015% S; max. 0.80% Cu; Ni remainder; and the usual production-related impurities. 1: Nickel-based alloy , consisting of (in mass %)Si 1.5-3.0%Al 1.5-3.0%Cr >0.1-3.0%, wherein 4.0≦Al+Si+Cr≦8.0 is satisfied for the contents of Si, Al and Cr in %,0.005 to 0.20%,Y 0.01-0.20%, 0.001 to 0.20% of one or more of the elements Hf, Zr, La, Ce, Ti, wherein 0.02≦Y+0.5*Hf +Zr+1.8*Ti+0.6*(La+Ce)≦0.30 is satisfied for the contents of Y, Hf, Zr, La, Ce, Ti in %,C 0.001-0.10%N 0.0005-0.10%Mn 0.001-0.20%Mg 0.0001-0.08%O 0.0001 to 0.010%S max. 0.015%Cu max. 0.80%Ni rest and the usual manufacturing-related impurities.2: Alloy according to with an Si content (in mass %) of 1.8 to 3.0%.3: Alloy according to with an Si content (in mass %) of 1.9 to 2.5%.4: Alloy according to with an Al content (in mass %) of 1.5 to 2.5%.5: Alloy according to with an Al content (in mass %) of 1.6 to 2.5%.6: Alloy according to with an Al content (in mass %) of 1.6 to 2.2% claim 1 , especially 1.6 to 2.0%.7: Alloy according to with a Cr content (in mass %) of 0.8 to 3.0%.8: Alloy according to with a Cr content (in mass %) of 1.2 to 3.0%.9. Alloy according to with a Cr content (in mass %) of 1.9 to 3.0% claim 1 , preferably 1.9 to 2.5%.10: Alloy according to wherein the formula 4.5≦Al+Si+Cr≦7.5 is satisfied for the contents of Si claim 1 , Al and Cr in %.11: Alloy according to with an Fe content (in mass %) of 0.005 to 0.10%.12: Alloy according to with a Y content (in mass %) of 0.01 to 0.15%.13: Alloy according to with a Y content (in mass %) of 0.01 to 0.15% ...

HOT EXTRUSION-MOLDING METHOD FOR Ni-BASED SUPER HEAT-RESISTANT ALLOY AND PRODUCTION METHOD FOR Ni-BASED SUPER HEAT-RESISTANT ALLOY EXTRUSION MATERIAL

A hot extrusion-molding method is for a Ni-based super heat-resistant alloy, wherein: a billet has a component composition for a precipitation strengthened-type Ni-based super heat-resistant alloy having a gamma prime phase equilibrium precipitation amount of 40 mol % or more at 700° C.; a lubrication glass pad is installed between a die and the billet; and adjustment is made so the relationship between the outer diameter DB (mm) of the billet at the time of insertion in a container and the inner diameter DC (mm) of the container satisfies (DC-DB): 2-8 mm, or adjustment is made so the relationship between the outer diameter DB′ (mm) of the billet prior to being heated to a hot processing temperature and the inner diameter DC′ (mm) of the container prior to being heated to a preheating temperature satisfies (DC′−DB′): 3-9 mm. A production method is performed using the hot extrusion-molding method mentioned above.

Creep-Resistant, Cobalt-Containing Alloys for High Temperature, Liquid-Salt Heat Exchanger Systems

An essentially Fe-free alloy consists essentially of, in terms of weight percent: 4 to 11 Co, 6.5 to 7.5 Cr, 0 to 0.15 Al, 0.5 to 0.85 Mn, 11 to 20 Mo, 1 to 3.5 Ta, 0.05 to 9 W, 0.03 to 0.08 C, 0 to 0.001 B, 0.0005 to 0.005 N, balance Ni, the alloy being characterized by, at 850° C., a yield strength of at least 25 Ksi, a tensile strength of at least 45 Ksi, a creep rupture life at 12 Ksi of at least 10 hours, and a corrosion rate, expressed in weight loss [g(cm 2 sec)]10 −11 during a 1000 hour immersion in liquid FLiNaK at 850° C., in the range of 5 to 20.

CREEP-RESISTANT, RHENIUM-FREE NICKEL BASE SUPERALLOY

Disclosed is a nickel base alloy which is substantially free of rhenium and has a solidus temperature of more than 1320° C. Precipitates of a γ′-phase are present in a γ-matrix with a fraction of 40 to 50 vol % at 1050° C. to 1100° C., and a γ/γ′ mismatch at 1050° C. to 1100° C. is from −0.15% to −0.25%. The alloy comprises 11 to 13 at % aluminum, 4 to 14 at % cobalt, 6 to 12 at % chromium, 0.1 to 2 at % molybdenum, 0.1 to 3.5 at % tantalum, 0.1 to 3.5 at % titanium, 0.1 to 3 at % tungsten. The tungsten content of the γ-matrix is greater than that in the precipitated γ′-phases. 1. A nickel base alloy , wherein the alloy is substantially free of rhenium and has a solidus temperature of more than 1320° C. , wherein precipitates of a γ′-phase are present in a γ-matrix with a fraction of from 40 to 50 vol % at temperatures of from 1050° C. to 1100° C. , and a γ/γ′ mismatch at temperatures of from 1050° C. to 1100° C. is from −0.15% to −0.25% , and wherein the alloy comprises:aluminum from 11 to 13 at %,cobalt from 4 to 14 at %,chromium from 6 to 12 at %,molybdenum from 0.1 to 2 at %,tantalum from 0.1 to 3.5 at %,titanium from 0.1 to 3.5 at %,tungsten from 0.1 to 3 at %,optionally, hafnium from 0.05 to 0.3 wt %, andnickel and unavoidable impurities as remainder,a tungsten content of the γ-matrix being greater than a tungsten content of the precipitates of the γ′-phase.2. The nickel base alloy of claim 1 , wherein the tungsten content of the γ-matrix at a temperature of 1100° C. is greater than 3.5 at %.3. The nickel base alloy of claim 1 , wherein the tungsten content of the γ-matrix is at a maximum when taking into account remaining constituents of the alloy.4. The nickel base alloy of claim 1 , wherein tungsten content and molybdenum content of the γ-matrix together are more than 5 at %.5. The nickel base alloy of claim 1 , wherein for a minimum aluminum content a maximum tantalum content and a medium titanium content are present.6. The nickel base alloy of claim 1 , ...

Ni-based superalloy with excellent unsusceptibility to segregation

A subject for the invention is to diminish the occurrence of streak-type segregation in producing a material comprising a Ni-based superalloy. The invention relates to a Ni-based superalloy having excellent unsusceptibility to segregation, characterized by comprising: 0.005 to 0.15 mass % of C; 8 to 22 mass % of Cr; 5 to 30 mass % of Co; equal or greater than 1 and less than 9 mass % of Mo; 5 to 21 mass % of W; 0.1 to 2.0 mass % of Al; 0.3 to 2.5 mass % of Ti; up to 0.015 mass % of B; and up to 0.01 mass % of Mg, with the remainder comprising Ni and unavoidable impurities.

HYBRID PRE-SINTERED PREFORM, GREEN PREFORM, AND PROCESS

A process includes agitating at least one core of a core alloy together with a braze binder to form at least one coated core comprising the at least one core coated with a first layer of the braze binder. The process also includes agitating the at least one coated core together with a powder composition comprising a first metal powder of a first alloy and a second metal powder of a second alloy to form a green preform having a first powder composition layer of the first alloy and the second alloy. The process further includes sintering the green preform to form at least one hybrid pre-sintered preform. A green preform includes a core, a first layer of a braze binder coated on the core, and a powder composition coated on the first layer. A hybrid pre-sintered preform includes a core and a first layer sintered to the core. 1. A process comprising:agitating at least one core of a core alloy together with a braze binder to form at least one coated core comprising the at least one core coated with a first layer of the braze binder;agitating the at least one coated core together with a powder composition comprising a first metal powder of a first alloy and a second metal powder of a second alloy to form a green preform having a first powder composition layer of the first alloy and the second alloy; andsintering the green preform to form at least one hybrid pre-sintered preform (PSP).2. The process of claim 1 , wherein the first alloy has a first melting point of at least about 2400° F. and the second alloy has a second melting point of below about 2350° F.3. The process of claim 1 , wherein the braze binder is a braze binder gel.4. The process of further comprising agitating the green preform together with the braze binder to form a braze binder-coated green preform and agitating the braze binder-coated green preform together with the first metal powder and the second metal powder to form a powder-coated green preform claim 1 , wherein the sintering is of the powder- ...

Creep-Resistant, Cobalt-Free Alloys for High Temperature, Liquid-Salt Heat Exchanger Systems

An essentially Fe- and Co-free alloy is composed essentially of, in terms of weight percent: 6.0 to 7.5 Cr, 0 to 0.15 Al, 0.5 to 0.85 Mn, 11 to 19.5 Mo, 0.03 to 4.5 Ta, 0.01 to 9 W, 0.03 to 0.08 C, 0 to 1 Re, 0 to 1 Ru, 0 to 0.001 B, 0.0005 to 0.005 N, balance Ni, the alloy being characterized by, at 850° C., a yield strength of at least 25 Ksi, a tensile strength of at least 38 Ksi, a creep rupture life at 12 Ksi of at least 25 hours, and a corrosion rate, expressed in weight loss [g/(cmsec)]10during a 1000 hour immersion in liquid FLiNaK at 850° C., in the range of 3 to 10. 1. An essentially Fe- and Co-free alloy consisting essentially of , in terms of weight percent:Cr 6.0 to 7.5Al 0 to 0.15Mn 0.5 to 0.85Mo 11 to 19.5Ta 0.3 to 4.5W 0.01 to 9C 0.03 to 0.08Re 0 to 1Ru 0 to 1B 0 to 0.001N 0.0005 to 0.005Ni balance{'sup': 2', '−11, 'said alloy being characterized by, at 850° C., a yield strength of at least 25 Ksi, a tensile strength of at least 38 Ksi, a creep rupture life at 12 Ksi of at least 25 hours, and a corrosion rate, expressed in weight loss [g/(cmsec)]10during a 1000 hour immersion in liquid FLiNaK at 850° C., in the range of 3 to 10.'}2. An alloy in accordance with wherein the range of Cr is 6.7 to 7.1 weight percent.3. An alloy in accordance with wherein the range of Al is 0.05 to 0.12 weight percent.4. An alloy in accordance with wherein the range of Mn is 0.7 to 0.8 weight percent.5. An alloy in accordance with wherein the range of Mo is 11.5 to 19 weight percent.6. An alloy in accordance with wherein the range of Ta is 0.4 to 4.1 weight percent.7. An alloy in accordance with wherein the range of C is 0.04 to 0.06 weight percent.8. An alloy in accordance with wherein said yield strength is at least 27 Ksi.9. An alloy in accordance with wherein said tensile strength is at least 40 Ksi.10. An alloy in accordance with wherein said creep rupture life is at least 28 hours.11. An alloy in accordance with wherein said corrosion rate is no more than 9.3.12. An ...

ADHESION PROMOTER LAYER FOR JOINING A HIGH-TEMPERATURE PROTECTION LAYER TO A SUBSTRATE, AND METHOD FOR PRODUCING SAME

An adhesion promoter layer for joining a high-temperature protection layer to a substrate includes a first layer of a first adhesion promoter material, provided for application to the substrate, and a second layer, arranged on the first layer and including a second adhesion promoter material having additionally introduced oxide dispersions, which is provided for joining a high-temperature protection layer. 1. An adhesion promoter layer for joining a high-temperature protection layer to a substrate , the adhesion promoter layer comprising:a first layer of a first adhesion promoter material, provided for application to the substrate, anda second layer, arranged on the first layer and comprising a second adhesion promoter material comprising additionally introduced oxide dispersions, which is provided for joining a high-temperature protection layer.2. The adhesion promoter layer according to claim 1 , wherein the second layer comprises oxide dispersions in a proportion of 0.01 to 50% by weight.3. The adhesion promoter layer according to claim 1 , wherein the first and/or second adhesion promoter material comprises MCrAIY claim 1 , where M=Co claim 1 , Ni claim 1 , and/or Fe.4. The adhesion promoter layer according to claim 1 , wherein the first and/or second adhesion promoter material comprises Si or an Si alloy.5. The adhesion promoter layer according to claim 1 , wherein the first and second adhesion promoter materials are identical.6. The adhesion promoter layer according to claim 1 , wherein the second layer comprises yttrium oxide claim 1 , aluminum oxide claim 1 , zirconium oxide claim 1 , hafnium oxide or else rare earth oxide dispersions.7. The adhesion promoter layer according to claim 1 , wherein the first layer is thicker than the second layer.8. The adhesion promoter layer according to claim 1 , having a total layer thickness of between 50 and 300 μm claim 1 , wherein the second layer has a layer thickness of at least 50 μm.9. A high-temperature protection ...

HIGH OXIDATION-RESISTANT ALLOY AND GAS TURBINE APPLICATIONS USING THE SAME

An alloy is disclosed, encompassing reduced amounts of Hafnium and Carbon so as to achieve an excellent oxidation resistance, as well as gas turbine applications using the same. 2. The high oxidation-resistant alloy of claim 1 , wherein Al is present in an amount of 4.00-10.50 wt %.3. The high oxidation-resistant alloy of claim 1 , wherein Hf is present in an amount of 1.00-1.20 wt %.4. The high oxidation-resistant alloy of claim 1 , wherein Re is present in an amount of 0.0-3.0 wt %.5. The high oxidation-resistant alloy of claim 1 , wherein Mg is present in an amount of up to 0.008 wt % claim 1 , and Mo claim 1 , B claim 1 , Zr claim 1 , Fe claim 1 , O claim 1 , N claim 1 , S claim 1 , or a mixture thereof in an amount of up to 0.879 wt %.6. The high oxidation-resistant alloy of claim 1 , wherein Mo is present in an amount of up to 0.60 wt % claim 1 , and Mg claim 1 , B claim 1 , Zr claim 1 , Fe claim 1 , O claim 1 , N claim 1 , S claim 1 , or a mixture thereof in an amount of up to 0.287 wt %.7. The high oxidation-resistant alloy of claim 1 , wherein B is present in an amount of up to 0.015 wt % claim 1 , and Mg claim 1 , Mo claim 1 , Zr claim 1 , Fe claim 1 , O claim 1 , N claim 1 , S claim 1 , or a mixture thereof in an amount of up to 0.872 wt %.8. The high oxidation-resistant alloy of claim 1 , wherein Zr is present in an amount of up to 0.015 wt % claim 1 , and Mg claim 1 , Mo claim 1 , B claim 1 , Fe claim 1 , O claim 1 , N claim 1 , S claim 1 , or a mixture thereof in an amount of up to 0.872 wt %.9. The high oxidation-resistant alloy of claim 1 , wherein Fe is present in an amount of up to 0.20 wt % claim 1 , and Mg claim 1 , Mo claim 1 , B claim 1 , Zr claim 1 , O claim 1 , N claim 1 , S claim 1 , or a mixture thereof in an amount of up to 0.687 wt %.10. The high oxidation-resistant alloy of claim 1 , wherein 0 is present in an amount of up to 0.02 wt % claim 1 , and Mg claim 1 , Mo claim 1 , B claim 1 , Zr claim 1 , Fe claim 1 , N claim 1 , S claim 1 , ...

HIGHLY PROCESSABLE SINGLE CRYSTAL NICKEL ALLOYS

Alloys, processes for preparing the alloys, and articles including the alloys are provided. The alloys can include, by weight, about 4% to about 7% aluminum, 0% to about 0.2% carbon, about 7% to about 11% cobalt, about 5% to about 9% chromium, about 0.01% to about 0.2% hafnium, about 0.5% to about 2% molybdenum, 0% to about 1.5% rhenium, about 8% to about 10.5% tantalum, about 0.01% to about 0.5% titanium, and about 6% to about 10% tungsten, the balance essentially nickel and incidental elements and impurities. 1. An alloy comprising , by weight , 4% to 7% aluminum , 0% to 0.2% carbon , 7% to 11% cobalt , 5% to 9% chromium , 0.01% to 0.2% hafnium , 0.5% to 2% molybdenum , 0% to 1.5% rhenium , 8% to 10.5% tantalum , 0.01% to 0.5% titanium , 6% to 10% tungsten , 0% to 0.5% lanthanum , 0% to 0.5% yttrium , and 0% to 0.5% boron the balance nickel and incidental impurity elements.2. (canceled)3. The alloy of claim 1 , wherein the alloy comprises claim 1 , by weight claim 1 , 5.5% to 6.5% aluminum claim 1 , 0% to 0.2% carbon claim 1 , 8.5% to 9.5% cobalt claim 1 , 6.5% to 7.5% chromium claim 1 , 0.05% to 0.15% hafnium claim 1 , 0.6% to 1.2% molybdenum claim 1 , 0.8% to 1.2% rhenium claim 1 , 9% to 10% tantalum claim 1 , 0.05% to 0.15% titanium claim 1 , and 7.5% to 8.5% tungsten claim 1 , the balance nickel and incidental impurity elements.4. The alloy of claim 1 , wherein the alloy is a single crystal.5. The alloy of claim 1 , wherein the alloy is essentially free of freckles.6. The alloy of claim 4 , wherein the alloy has a reduction in liquid density of less than 0.015 g/cmat 20% solidification of the alloy.7. The alloy of claim 4 , wherein the alloy has a reduction in liquid density of less than 0.025 g/cmat 40% solidification of the alloy.8. The alloy of claim 1 , wherein the alloy is essentially free of topologically close-packed phases.9. The alloy of claim 1 , wherein the alloy has a γ′ phase fraction of greater than 59% at 1000° C.10. The alloy of claim 1 , ...

OPTIMIZED NICKEL-BASED SUPERALLOY

A nickel-based alloy for high-temperature applications, in particular for use in turbomachines, which has a chemical composition as set forth in the claims, wherein the ratio of the fractions of Ta to Al in percent by weight is greater than or equal to 1 and less than or equal to 2, and wherein the ratio of the fractions of Co to W in percent by weight is greater than or equal to 2 and less than or equal to 5. 1. A nickel-based alloy for high-temperature applications , wherein the alloy has a chemical composition which comprises , in % by weight:Al from 3.7 to 7.0Co from 10 to 20Cr from 2.1 to 7.2Mo from 1.1 to 3.0Re from 5.7 to 9.2Ru from 3.1 to 8.5Ta from 4.1 to 11.9Ti from 0 to 3.3from 2.1 to 4.9from 0 to 0.05Si from 0 to 0.1Mn from 0 to 0.05from 0 to 0.015S from 0 to 0.001from 0 to 0.003Cu from 0 to 0.05Fe from 0 to 0.15from 0 to 0.15Zr from 0 to 0.015from 0 to 0.001remainder nickel and unavoidable impurities, and wherein a ratio of fractions of Ta to Al in percent by weight is greater than or equal to 1 and less than or equal to 2, and a ratio of fractions of Co to W in percent by weight is greater than or equal to 2 and less than or equal to 5.2. The nickel-based alloy of claim 1 , wherein the ratio of the fractions of Co to W in percent by weight is less than or equal to 4.3. The nickel-based alloy of claim 1 , wherein a ratio of fractions of W to Mo in percent by weight is greater than or equal to 1 and less than or equal to 4.4. The nickel-based alloy of claim 1 , wherein a ratio of fractions of Co to Re in percent by weight is greater than or equal to 1 and less than or equal to 2.5. The nickel-based alloy of claim 1 , wherein the alloy comprises claim 1 , in percent by weight:from 5.0 to 7.0% Al and/orfrom 10.5 to 15.0% Co and/orfrom 4.0 to 6.0% Cr and/orfrom 1.1 to 2.5% Mo and/orfrom 5.5 to 7.0% Re and/orfrom 3.1 to 5.5% Ru and/orfrom 5.0 to 9.0% Ta and/orfrom 0 to 2.0% Ti and/orfrom 3.0 to 4.5% W.6. The nickel-based alloy of claim 1 , wherein the alloy ...

RHENIUM-FREE NICKEL BASE SUPERALLOY OF LOW DENSITY

The invention relates to a substantially rhenium-free nickel base alloy showing a high creep resistance and relatively low density which comprises in % by weight: aluminum from 3.0 to 7.7, cobalt from 0 to 16.8, chromium from 3 to 11.8, molybendum from 3.1 to 11.3, tantalum from 0 to 3.9. In addition to nickel and unavoidable impurities this alloy may further comprise one or more of titanium, tungsten, carbon, phosphorus, copper, zirconium, silicon, hafnium, yttrium, niobium, and germanium. 1. A nickel base alloy exhibiting high creep resistance and being substantially free of rhenium , wherein the alloy comprises the following elements in % by weight relative to the total weight of the alloy:aluminum from 3.0 to 7.7cobalt from 0 to 16.8chromium from 3 to 11.8molybendum from 3.1 to 11.3tantalum from 0 to 3.9.2. The alloy of claim 1 , wherein the alloy comprises:aluminum from 3.4 to 7.7cobalt from 0 to 16.8chromium from 4 to 11.8molybendum from 3.3 to 11.3tantalum from 0 to 3.9.3. The alloy of claim 1 , wherein the alloy comprises:aluminum from 3.8 to 7.7cobalt from 0 to 16.8chromium from 5 to 11.8molybendum from 3.4 to 11.3tantalum from 0 to 3.9.4. The alloy of claim 1 , wherein the alloy comprises:aluminum from 4.1 to 7.7cobalt from 0 to 16.8chromium from 6 to 11.8molybendum from 3.6 to 11.3tantalum from 0 to 3.9.5. The alloy of claim 1 , wherein the alloy comprises:aluminum from 4.7 to 7.7cobalt from 2.6 to 13.6chromium from 6.3 to 7.3molybendum from 3.7 to 4.7tantalum from 0 to 0.5titanium from 2.8 to 3.6tungsten from 7.4 to 8.4.6. The alloy of claim 1 , wherein the alloy comprises:aluminum from 5.0 to 5.4cobalt from 2.9 to 13.3chromium from 6.6 to 7molybendum from 4 to 4.4tantalum from 0 to 0.2titanium from 3.1 to 3.5tungsten from 7.7 to 8.1.7. The alloy of claim 1 , wherein the alloy further comprises:titanium from 0 to 6.0tungsten from 0 to 11.3carbon from 0 to 0.05phosphorus from 0 to 0.015copper from 0 to 0.05zirconium from 0 to 0.015silicon from 0 to 6. ...

NOVEL MASK FORMULATION TO PREVENT ALUMINIZING ONTO THE PRE-EXISTING CHROMIDE COATING

A novel dual layer mask formulation is provided. In particular, the mask has a unique composition that protects the integrity of an underlying chromide coating, prevents chromium depletion from the chromide coating and prevents a subsequent aluminide coating from being deposited thereon. 1. A mask composition having a dual layer that prevents aluminizing of the selected regions of a turbine component having a pre-existing and underlying chromide coating , said dual layer comprising:an inner buffer layer consisting essentially of a slurry of mixed chromium-based powder and an inner inert ceramic powder in a binder solution; said chromium-based powder having a chromium activity equal to or higher than a chromium activity in the pre-existing and underlying chromide coating; andan outer getter layer overlying said inner buffer layer consisting essentially of nickel-based powder and an outer inert ceramic powder;wherein said mask composition substantially prevents aluminide coating deposition onto said pre-existing and underlying chromide coating, and prevents chromium depletion from said pre-existing and underlying chromide coating, thereby maintaining the structural integrity of the pre-existing and underlying chromide coating.2. The mask composition of claim 1 , wherein each of said inner inert ceramic material and said outer inert ceramic material is selected from the group consisting of alumina claim 1 , kaolinite and zirconia.3. The mask composition as in claim 1 , wherein the inner buffer layer comprises from about 25 to about 65 weight percent of metallic chromium based on the total weight of the inner buffer layer.4. The mask composition as in claim 1 , wherein the inner buffer layer comprises no greater than about 5 weight percent of metallic aluminum based on the total weight of the inner buffer layer.5. The mask composition as in claim 1 , wherein the inner buffer layer is characterized by the absence of metallic aluminum.6. The mask composition of claim 1 , ...

LOW DENSITY NICKEL-BASED SUPERALLOY HAVING HIGH MECHANICAL STRENGTH AND ENVIRONMENTAL ROBUSTNESS AT A HIGH TEMPERATURES

A nickel-based superalloy includes, in weight percent, 6 to 8% aluminum, 12 to 15% cobalt, 4 to 8% chromium, 0 to 0.2% hafnium, 0.5 to 4% molybdenum, 3.5 to 6% rhenium, 4 to 6% tantalum, 1 to 3% titanium, 0 to 2% tungsten, 0 to 0.1% silicon, the balance being nickel and unavoidable impurities. 1. A nickel-based superalloy comprising , in weight percent , 6 to 8% aluminum , 12 to 15% cobalt , 4 to 8% chromium , 0 to 0.2% hafnium , 0.5 to 4% molybdenum , 3.5 to 6% rhenium , 4 to 6% tantalum , 1 to 3% titanium , 0 to 2% tungsten , 0 to 0.1% silicon , the balance consisting of nickel and unavoidable impurities.2. The superalloy as claimed in claim 1 , wherein said superalloy comprises claim 1 , in weight percent claim 1 , 6 to 8% aluminum claim 1 , 12 to 15% cobalt claim 1 , 4 to 8% chromium claim 1 , 0 to 0.2% hafnium claim 1 , 0.5 to 4% molybdenum claim 1 , 3.5 to 6% rhenium claim 1 , 4 to 6% tantalum claim 1 , 1 to 3% titanium claim 1 , 0 to 2% tungsten claim 1 , 0 to 0.05% silicon claim 1 , the balance consisting of nickel and unavoidable impurities.3. The superalloy as claimed in claim 1 , wherein said superalloy comprises claim 1 , in weight percent claim 1 , 6 to 8% aluminum claim 1 , 12 to 15% cobalt claim 1 , 4 to 8% chromium claim 1 , 0 to 0.15% hafnium claim 1 , 0.5 to 4% molybdenum claim 1 , 3.5 to 6% rhenium claim 1 , 4 to 6% tantalum claim 1 , 1 to 3% titanium claim 1 , 0 to 2% tungsten claim 1 , 0 to 0.1% silicon claim 1 , the balance consisting of nickel and unavoidable impurities.4. The superalloy as claimed in claim 1 , wherein said superalloy comprises claim 1 , in weight percent claim 1 , 6.5 to 7.5% aluminum claim 1 , 12 to 15% cobalt claim 1 , 4.5 to 7.5% chromium claim 1 , 0 to 0.2% hafnium claim 1 , 0.5 to 3.5% molybdenum claim 1 , 3.5 to 5.5% rhenium claim 1 , 4.5 to 5.5% tantalum claim 1 , 1.5 to 2.5% titanium claim 1 , 0 to 1.5% tungsten claim 1 , 0 to 0.1% silicon claim 1 , the balance consisting of nickel and unavoidable impurities.5. The ...

A NICKEL-BASED ALLOY

A nickel-based alloy composition consisting, in weight percent, of: between 7.0 and 1.0% chromium, between 4.0 and 14.0% cobalt, between 1.0 and 2.0% rhenium, between 0.5 and 11.0% tungsten, between 0.0 and 0.5% molybdenum, between 4.0 and 6.5% aluminium, between 8.0 and 12.0 tantalum, between 0.0 and up to 0.5% hafnium, between 0.0 and 0.5% niobium, between 0.0 and 0.5% titanium, between 0.0 and 0.5% vanadium, between 0.0 and 0.1% silicon, between 0.0 and 0.1% yttrium, between 0.0 and 0.1% lanthanum, between 0.0 and 0.1% cerium, between 0.0 and 0.003% sulphur, between 0.0 and 0.05% manganese, between 0.0 and 0.05% zirconium, between 0.0 and 0.005% boron, between 0.0 and 0.01% carbon, the balance being nickel and incidental impurities. 1. A nickel-based alloy composition consisting , in weight percent , of: between 7.0 and 11.0% chromium , between 4.0 and 14.0% cobalt , between 1.0 and 2.0% rhenium , between 5.5 and 11.0% tungsten , between 0.0 and 0.5% molybdenum , between 4.0 and 6.5% aluminium , between 8.0 and 12.0% tantalum , between 0.0 and up to 0.5% hafnium , between 0.0 and 0.5% niobium , between 0.0 and 0.5% titanium , between 0.0 and 0.5% vanadium , between 0.0 and 0.1% silicon , between 0.0 and 0.1% yttrium , between 0.0 and 0.1% lanthanum , between 0.0 and 0.1% cerium , between 0.0 and 0.003% sulphur , between 0.0 and 0.05% manganese , between 0.0 and 0.05% zirconium , between 0.0 and 0.005% boron , between 0.0 and 0.01% carbon , the balance being nickel and incidental impurities.2. The nickel-based alloy composition according to claim 1 , consisting claim 1 , in weight percent claim 1 , of between 7.0 and 8.5% chromium.3. The nickel-based alloy composition according to claim 1 , consisting claim 1 , in weight percent claim 1 , of between 4.0 and 12.0% cobalt claim 1 , preferably between 7.0 and 11.0% cobalt claim 1 , more preferably between 9.0 and 11.0% cobalt.4. The nickel-based alloy composition according to claim 1 , consisting claim 1 , in weight ...

METHOD FOR PRODUCING A METAL FILM

A method for producing a metal film from an alloy having more than 50% nickel includes the following steps: (a) the alloy is melted in volumes of more than one ton in a vacuum induction furnace, or open in an induction or arc furnace, followed by treatment in a VOD or VLF system, (b) the alloy is then poured off in blocks, electrodes or as continuous casting to form a pre-product, followed by single or multiple re-melting by VAR and/or ESU (c) the pre-product is then annealed between 800 and 1350° C. for 1-300 hours under air or protection gas, (d) the pre-product is then hot-formed between 1300 and 600° C. to reduce the thickness of the input material by the factor 1.5-200, such that the pre-product has a thickness of 1-100 mm after the forming and is not recrystallized, recovered, and/or (dynamically) recrystallized having a grain size of smaller than 300 μm, (e) the pre-product is then pickled, (f) the pre-product is then cold-formed to produce a film having an end thickness of 10-600 μm, having a deformation ratio of greater than 90%, (g) the film is then cut into strips of 5-300 mm following the cold-forming, (h) the film strips are then annealed under protection gas between 600 and 1200° C. for 1 second to 5 hours in a continuous furnace, (i) wherein the annealed, film-like material is recrystallized after the annealing and has a high proportion of cubic texture. 1. Method for the production of a metal foil from an alloy with more than 50% nickel , containing the following method steps:(a) the alloy is melted in amounts of more than one metric ton in a vacuum induction furnace or openly in an induction or arc furnace, followed by a treatment in a VOD or VLF system,(b) then the alloy is cast into ingots, electrodes or as continuous casting for the formation of a primary product, if necessary followed by a single or multiple remelting by means of VAR and/or ESU(c) thereafter the primary product is annealed as needed at temperatures between 800 and 1350° C. for 1 ...

Oxidation-Resistant Coated Superalloy

A coating-substrate combination includes: a Ni-based superalloy substrate comprising, by weight percent: 2.0-5.1 Cr; 0.9-3.3 Mo; 3.9-9.8 W; 2.2-6.8 Ta; 5.4-6.5 Al; 1.8-12.8 Co; 2.8-5.8 Re; 2.8-7.2 Ru; and a coating comprising, exclusive of Pt group elements, by weight percent: Ni as a largest content; 5.8-9.3 Al; 4.4-25 Cr; 3.0-13.5 Co; up to 6.0 Ta, if any; up to 6.2 W, if any; up to 2.4 Mo, if any; 0.3-0.6 Hf; 0.1-0.4 Si; up to 0.6 Y, if any; up to 0.4 Zr, if any; up to 1.0 Re, if any. 1. An article comprising:a Ni-based superalloy substrate comprising, by weight percent: 2.0-5.1 Cr; 0.9-3.3 Mo; 3.9-9.8 W; 2.2-6.8 Ta; 5.4-6.5 Al; 1.8-12.8 Co; 2.8-5.8 Re; 2.8-7.2 Ru; anda coating comprising, exclusive of Pt group elements, by weight percent: Ni as a largest content; 5.8-9.3 Al; 4.4-25 Cr; 3.0-13.5 Co; up to 6.0 Ta, if any; up to 6.2 W, if any; up to 2.4 Mo, if any; 0.3-0.6 Hf; 0.1-0.4 Si; up to 0.6 Y, if any; up to 0.4 Zr, if any; up to 1.0 Re, if any.2. The article of wherein:the substrate comprises 0.05-0.7 weight percent Hf.3. The article of wherein:the substrate has a 1800° F. & 45 ksi (982° C. & 310 MPa) rupture life of at least 120 hours.4. The article of wherein:the coating comprises exclusive of Pt group elements, by weight percent: 0.4-0.6 said Hf; 0.2-0.4 said Si.5. The article of wherein:the coating has less than 1.0 weight percent overall said Pt group elements combined.6. The article of wherein:in weight percent exclusive of Pt group elements, the coating has less than 1.0 weight percent individually elements other than said Ni, Al, Cr, Ta, W, Mo, Hf, Si, Y, Zr, and Pt group elements, if any.7. The article of wherein:the substrate also falls within one of the broader ranges of Table VI; andthe coating also falls within the associated broader range of Table VII.8. The article of wherein:the coating and substrate fall within the narrower associated ranges.9. The article of wherein:in weight percent the coating has 6.0≤W+Ta≤13.0 or Ta+W≤0.05.10. The ...

NICKEL-BASE SUPERALLOY AND USE THEREOF

The novel nickel-base superalloy useful in an additive manufacturing process or a powder-based manufacturing process includes the following composition in wt %: Cr 8.0-8.5; Co 9.0-9.5; Mo 0.4-0.6; W 9.3-9.7; Ta 2.9-3.6; Al 4.9-5.6; Ti 0.2-1.0; Hf 0-0.05; C 0.005-0.03; B 0.005-0.02; Zr 0.005-0.1; Nb 0.2-1; Mn 0-0.6; and S 0-0.002 (≦20 ppm); the balance nickel and incidental elements and unavoidable impurities. 7. A nickel-base superalloy as claimed in claim 1 , in a physical form which is suitable for use in an additive manufacturing process.8. A nickel-base superalloy as claimed in claim 1 , in the form of a wire claim 1 , rod or powder suitable for use in an additive manufacturing process.9. A nickel-base superalloy as claimed in claim 1 , in the form of a wire claim 1 , rod or powder suitable for use in a directed energy deposition (DED) additive manufacturing process.10. A nickel-base superalloy as claimed in claim 7 , wherein the physical form is suitable for use in a manufacturing process selected from laser-based additive manufacturing (LBAM) claim 7 , direct laser deposition (DLD) claim 7 , electron beam additive manufacturing (EBAM) claim 7 , laser engineered net shaping (LENS) claim 7 , selective laser melting (SLM) claim 7 , SLM three-dimensional printing (SLM 3D printing) claim 7 , direct metal laser sintering (DMLS) claim 7 , direct metal laser sintering three-dimensional printing (DML 3D printing) claim 7 , electron beam melting (EBM) claim 7 , direct metal deposition (DMD) claim 7 , direct metal tooling (DMT) claim 7 , direct metal tooling three-dimensional printing (DMT 3D printing) claim 7 , construction laser additive direct (CLAD) and ion fusion formation (IFF).11. A nickel-base superalloy as claimed in claim 1 , in a physical form which is suitable for use in a powder-based manufacturing process.12. A nickel-base superalloy as claimed in claim 11 , in the form of a powder suitable for use in a powder-based manufacturing process13. A nickel-base ...

A NICKEL-BASED ALLOY

A nickel-based alloy composition consisting, in weight percent, of: between 5.0% and 6.9% aluminium, between 0.0% and 11.0% cobalt, between 6.0% and 11.6% chromium, between 0.0% and 4.0% molybdenum, between 0.0% and 2.0% niobium, between 0.6 and 8.6% tantalum, between 0.0% and 3.0% titanium, between 8.4% and 15.2% tungsten, between 0.02 wt. % and 0.35 wt. % carbon, between 0.001 and 0.2 wt. % boron, between 0.001 wt. % and 0.5 wt. %. zirconium, between 0.0 and 0.5% silicon, between 0.0 and 0.1% yttrium, between 0.0 and 0.1% lanthanum, between 0.0 and 0.1% cerium, between 0.0 and 0.003% sulphur, between 0.0 and 0.25% manganese, between 0.0 and 0.5% copper, between 0.0 and 2.0% hafnium, between 0.0 and 1.0% vanadium, between 0.0 and 4.0% iron, between 0.0 and 1.0% rhenium, the balance being nickel and incidental impurities, wherein the following equations are satisfied in which W, W, W, W, W, Wand Ware the weight percent of niobium, tantalum, titanium, chromium, molybdenum, tungsten and rhenium in the alloy respectively 6.6≤2W+W+1.44W, 22.2≥W+W+1.16 W+1.7W, 13.9≤W+1.17(W+3.3W). 1. A nickel-based alloy composition consisting , in weight percent , of: between 5.0% and 6.9% aluminium , between 0.0% and 11.0% cobalt , between 6.0% and 11.6% chromium , between 0.0% and 4.0% molybdenum , between 0.0% and 2.0% niobium , between 0.6 and 8.6% tantalum , between 0.0% and 3.0% titanium , between 8.4% and 15.2% tungsten , between 0.02 wt. % and 0.35 wt. % carbon , between 0.001 and 0.2 wt. % boron , between 0.001 wt. % and 0.5 wt. %. zirconium , between 0.0 and 0.5% silicon , between 0.0 and 0.1% yttrium , between 0.0 and 0.1% lanthanum , between 0.0 and 0.1% cerium , between 0.0 and 0.003% sulphur , between 0.0 and 0.25% manganese , between 0.0 and 0.5% copper , between 0.0 and 2.0% hafnium , between 0.0 and 1.0% vanadium , between 0.0 and 4.0% iron , between 0.0 and 1.0% rhenium , the balance being nickel and incidental impurities , wherein the following equations are satisfied ...

METHOD FOR PRODUCING A METAL FILM

A method for producing a metal film composed of an alloy having more than 50% nickel (a) melts the alloy in amounts of more than one ton in a vacuum induction furnace, or openly in an induction or arc furnace, followed by treatment in a VOD or VLF installation, (b) the alloy is cast into blocks, electrodes or as continuous casting to form a pre-product, (c) the pre-product is annealed if necessary at temperatures between 800° C.-1350° C. for 1-300 hours under air or protective gas, and (d) hot rolled between 1300° C.-600° C. to reduce the thickness of the starting material by a factor of 1.5-200, such that the pre-product has a thickness of 1-100 mm after the rolling and is not recrystallized, recovered, and/or is (dynamically) recrystallized having a grain size less than 300 μm, (e) the pre-product is pickled, (f) then cold worked to produce a film with a degree of deformation greater than 90% to a final thickness of 10-600 μm, (g) the film is cut into strips of 5-300 mm after the cold working, (h) the film strips are coated with a ceramic powder loosely or by an adhesive or by an oxide dissolved in alcohol or covered with a separating film and, if necessary, dried, (i) the film strips are wound annularly onto one or more mandrels or one or more sleeves, wherein the inner and the outer end are each spot-welded or clamped, (j) the annularly wound film strips are annealed under protective gas at temperatures between 600° C.-1200° C. for 1 min to 300 h, (k) wherein the annealed film-like material is recrystallized after the annealing and has a large proportion of cubic texture. 1. Method for the production of a metal foil from an alloy with more than 50% nickel , containing the following method steps:(a) the alloy is melted in amounts of more than one metric ton in a vacuum induction furnace or openly in an induction or arc furnace, followed by a treatment in a VOD or VLF system,(b) then the alloy is cast into ingots, electrodes or as continuous casting for the ...

NICKEL-BASED SUPERALLOY HAVING HIGH MECHANICAL STRENGTH AT A HIGH TEMPERATURE

A nickel-based superalloy includes, in weight percent, 4 to 6% aluminum, 5 to 8% cobalt, 6 to 9% chromium, 0.1 to 0.9% hafnium, 2 to 4% molybdenum, 5 to 7% rhenium, 5 to 7% tantalum, 2 to 5% tungsten, 0 to 0.1% silicon, the balance being of nickel and unavoidable impurities. 1. A nickel-based superalloy comprising , in weight percent , 4 to 6% aluminum , 5 to 8% cobalt , 6 to 9% chromium , 0.1 to 0.9% hafnium , 2 to 4% molybdenum , 5 to 7% rhenium , 5 to 7% tantalum , 2 to 5% tungsten , 0 to 0.1% silicon , the balance consisting of nickel and unavoidable impurities.2. The superalloy as claimed in claim 1 , wherein said superalloy comprises claim 1 , in weight percent claim 1 , 4.5 to 5.5% aluminum claim 1 , 5 to 8% cobalt claim 1 , 6.5 to 8.5% chromium claim 1 , 0.1 to 0.6% hafnium 2.5 to 3.5% molybdenum claim 1 , 5.5 to 6.5% rhenium claim 1 , 5.5 to 6.5% tantalum claim 1 , 2.5 to 4.5% tungsten claim 1 , 0 to 0.1% silicon claim 1 , the balance consisting of nickel and unavoidable impurities.3. The superalloy as claimed in claim 2 , wherein said superalloy comprises claim 2 , in weight percent claim 2 , 4.5 to 5.5% aluminum claim 2 , 5 to 8% cobalt claim 2 , 6.5 to 8.5% chromium claim 2 , 0.1 to 0.6% hafnium claim 2 , 2.5 to 3.5% molybdenum claim 2 , 5.5 to 6.5% rhenium claim 2 , 5.5 to 6.5% tantalum claim 2 , 2.5 to 4.5% tungsten claim 2 , the balance consisting of nickel and unavoidable impurities.4. The superalloy as claimed in claim 3 , wherein said superalloy comprises claim 3 , in weight percent claim 3 , 4.5 to 5.5% aluminum claim 3 , 5 to 8% cobalt claim 3 , 6.5 to 8.5% chromium claim 3 , 0.2 to 0.5% hafnium claim 3 , 2.5 to 3.5% molybdenum claim 3 , 5.5 to 6.5% rhenium claim 3 , 5.5 to 6.5% tantalum claim 3 , 2.5 to 4.5% tungsten claim 3 , the balance consisting of nickel and unavoidable impurities.5. The superalloy as claimed in claim 3 , wherein said superalloy comprises claim 3 , in weight percent claim 3 , 4.5 to 5.5% aluminum claim 3 , 6 to 8% cobalt ...

OXIDATION RESISTANT NICKEL BRAZE PUTTY

Disclosed is a braze putty composition including a sacrificial binder, a first nickel alloy and a second nickel alloy, a method of making the putty, and a method for using this putty to repair castings. 1. A braze putty composition comprising a sacrificial binder , a first nickel alloy and a second nickel alloy.2. The braze putty composition of claim 1 , wherein the sacrificial binder comprises an acrylic polymer having a glass transition temperature below about 20° C.3. The braze putty composition of claim 1 , wherein the first nickel alloy comprises up to about 0.02 wt % of boron and the second nickel alloy comprises boron in an amount no greater than 1.0 wt %.4. The braze putty composition of claim 1 , wherein the first nickel alloy comprises about 4.75 wt %-10.5 wt % of chromium claim 1 , about 5.5 wt %-6.7 wt % of aluminum claim 1 , up to about 13 wt % cobalt claim 1 , about 3.75 wt %-9.0 wt % of tantalum claim 1 , about 1.3 wt %-2.25 wt % of molybdenum claim 1 , about 3.0 wt %-6.8 wt % of tungsten claim 1 , about 2.6 wt %-3.25 wt % of rhenium claim 1 , up to about 0.02 wt % of boron claim 1 , about 0.05 wt %-2.0 wt % of hafnium claim 1 , up to about 0.14 wt % of carbon claim 1 , up to about 0.35 wt % of zirconium claim 1 , and a balance of nickel and the second nickel alloy comprises about 21.25 wt %-22.75 wt % of chromium claim 1 , about 5.7 wt %-6.3 wt % of aluminum claim 1 , about 11.5 wt %-12.5 wt % of cobalt claim 1 , about 5.7 wt %-6.3 wt % of silicon claim 1 , boron in an amount no greater than 1.0 wt % or 0.45 wt %-0.55 wt % of boron as described above claim 1 , and a balance of nickel.5. The braze putty composition of claim 1 , wherein the first nickel alloy is present in an amount of 20 to 80 weight percent and the second nickel alloy is present in an amount of 20 to 80 weight percent relative to the total amount of the first nickel alloy and the second nickel alloy.6. The braze putty composition of claim 5 , wherein the first nickel alloy is present ...

Article and method for making an article

An article and a method for making shaped cooling holes in an article are provided. The method includes the steps of depositing a metal alloy powder to form an initial layer including at least one aperture, melting the metal alloy powder with a focused energy source to transform the powder layer to a sheet of metal alloy, sequentially depositing an additional layer of the metal alloy powder to form a layer including at least one aperture corresponding to the at least one aperture in the initial layer, melting the additional layer of the metal alloy powder with the focused energy source to increase the sheet thickness, and repeating the steps of sequentially depositing and melting the additional layers of metal alloy powder until a structure including at least one aperture having a predetermined profile is obtained. The structure is attached to a substrate to make the article.

SX-NICKEL ALLOY HAVING IMPROVED TMF PROPERTIES, RAW MATERIAL AND COMPONENT

Provided is an improved composition of a nickel-based superalloy. The improved composition may have Ni-8Cr-10Co-0.6Mo-8Ta-1.25Re-5.7Al-OTi-0.1Hf-0.25Si-0.008B-0.0207C-0.02Y. 2. A raw material ,in particular a powder,{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'comprising the alloy as claimed in .'}3. A component ,{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'comprising the alloy as claimed in .'}4. The component as claimed in claim 3 ,wherein the component is a turbine component.5. The alloy as claimed in claim 1 , wherein the alloy contains no titanium (Ti).6. The component of claim 4 , wherein the turbine component is a turbine blade.8. The nickel-based alloy of claim 7 , wherein the alloy contains no Titanium (Ti). This application claims priority to PCT Application No. PCT/EP2017/051630, having a filing date of Jan. 26, 2017, based on German Application No. 10 2016 203 724.2, having a filing date of Mar. 8, 2016, the entire contents both of which are hereby incorporated by reference.The following relates to a nickel-based SX alloy having improved TMF properties, to a raw material and to a component.In order to permit a higher turbine inlet temperature and thus greater efficiency, nickel-based SX materials are presently the focus of research. These materials are thought to have substantially greater creep resistance in comparison to the known SX materials, and to have markedly greater tensile strength in particular at high temperatures.However, initial research into the TMF behavior shows that, at lower temperatures (373K) and large tensile oscillation amplitudes, the materials tend to brittle behavior and thus to reduced TMF lives.The LCF life at large tensile oscillation amplitudes is also reduced by the brittle fracture behavior between room temperature and 923K.Whereas previously the creep properties were considered to be decisive for lifespan, TMF properties are increasingly significant. This is due to improved cooling air designs, which produce ...

Process For Making A Turbine Wheel And Shaft Assembly

A process for making a turbine rotor includes steps of providing a shaft made of a first metal composition and having an integral pin projecting axially therefrom, providing a mold that defines a cavity for investment casting a turbine wheel, disposing the pin within the cavity of the mold, pre-heating the mold and the pin to a mold temperature, pouring a molten second metal composition into the cavity of the pre-heated mold such that the molten second metal composition envelopes the pin within the cavity, and controlling the process so that the pin acts as a chill member causing the second metal composition around the chill member to solidify with a finer equiaxed grain structure than would be the case without the chill member. The turbine wheel is joined to the shaft via the casting of the turbine wheel about the pin.

HIGH-STRENGTH, HEAT-RESISTANT Ni-BASE ALLOY, METHOD FOR PRODUCING SAME, AND GAS TURBINE BLADE

Provided is a high-strength, heat-resistant, Ni-base alloy comprising Co: from 5 to 12%, Cr: from 5 to 12%, Mo: from 0.5 to 3.0%, W: from 3.0 to 6.0%, Al: from 5.5 to 7.2%, Ti: from 1.0 to 3.0%, Ta: from 1.5 to 6.0%, Re: from 0 to 2.0%, and C: from 0.01 to 0.20%. The high-strength, heat-resistant, Ni-base alloy is constituted of a Ni-based alloy, the balance of the Ni-based alloy comprising Ni and inevitable impurities. The density of the high-strength, heat-resistant Ni-base alloy is less than 8.5 g/cm3. 113-. (canceled)14. A method for producing a heat-resistant Ni-base alloy using a Ni-base alloy , the method comprising;as solution heat treatment, heating a cast material obtained by directionally solidification of the Ni-alloy to a temperature in a range of from 1180 to 1320 ° C. and cooling the cast material to 900 ° C. or less at a cooling rate of 50 to 250 ° C./minute, and then;as stabilization heat treatment, heating the cast material to a temperature in a range of from 1050 to 1150 ° C. and cooling; and thenas aging heat treatment, heating the cast material to a temperature in a range of from 800 to 900° C. for not less than 4 hours,wherein the Ni-base alloy comprises, by mass %:Co: from 5 to 12%,Cr: from 5 to 12%,Mo: from 0.5 to 3.0%,W: from 3.0 to 6.0%,Al: from 5.5 to 7.2%,Ti: from 1.0 to 3.0%,Ta: from 1.5 to 6.0%,Re: from 0 to 2.0%, andC: from 0.01 to 0.20%,the balance of the Ni-base alloy comprising Ni and inevitable impurities, and a density of the heat-resistant Ni-base alloy being less than 8.5g/cm3,{'b': 1', '1', '1, 'claim-text': {'br': None, 'i': 'P', '1=1.2−0.0036×[% Co]−0.023×[% Cr]−0.072×[% Mo]−0.029×[% W]−0.12×[% Al]−0.072×[% Ti]−0.014×[% Ta]−0.06×[% Re]−0.13×[% C]\u2003\u2003(1).'}, 'wherein, a parameter P defined by Equation (1) by the content (mass %) of each component is taken to be a second-phase shape parameter P, and a content of each component of the Ni-base alloy is set such that the second-phase shape parameter P is in a range of from ...

Ni-BASED DIRECTIONALLY SOLIDIFIED ALLOY

The present invention provides first generation Ni-based directionally solidified alloy containing none of Co and Re, which has excellent TMF characteristics, creep property and environment-resistant characteristics, and is superior in cost performance in practical use. The Ni-based directionally solidified alloy according to one embodiment of the present invention consists of Cr: 6% by mass or more and 12% by mass or less; Mo: 0.4% by mass or more and 3.0% by mass or less; W: 6% by mass or more and 10% by mass or less; Al: 4.0% by mass or more and 6.5% by mass or less; Nb: 0% by mass or more and 1% by mass or less; Ta: 8% by mass or more and 12% by mass or less; Hf: 0% by mass or more and 0.15% by mass or less; Si: 0.01% by mass or more and 0.2% by mass or less; Zr: 0% by mass or more and 0.04% by mass or less; B: 0.01% by mass or more and 0.03% by mass or less; and C: 0.01% by mass or more and 0.3% by mass or less, and a balance of Ni and inevitable impurities. 1. Ni-based directionally solidified alloy consisting of:Cr: 6% by mass or more and 12% by mass or less;Mo: 0.4% by mass or more and 3.0% by mass or less;W: 6% by mass or more and 10% by mass or less;Al: 4.0% by mass or more and 6.5% by mass or less;Nb: 0% by mass or more and 1% by mass or less;Ta: 8% by mass or more and 12% by mass or less;Hf: 0% by mass or more and 0.15% by mass or less;Si: 0.01% by mass or more and 0.2% by mass or less;Zr: 0% by mass or more and 0.04% by mass or less;B: 0.01% by mass or more and 0.03% by mass or less; andC: 0.01% by mass or more and 0.3% by mass or less, anda balance of Ni and inevitable impurities.2. Ni-based directionally solidified alloy consisting of:Cr: 7% by mass or more and 12% by mass or less;Mo: 0.4% by mass or more and 2.5% by mass or less;W: 7% by mass or more and 10% by mass or less;Al: 4.0% by mass or more and 6.5% by mass or less;Nb: 0% by mass or more and 1% by mass or less;Ta: 9% by mass or more and 11% by mass or less;Hf: 0% by mass or more and 0.15% by ...

CASTING METHOD AND CAST ARTICLE

A casting method and cast article are provided. The casting method includes providing a casting furnace, the casting furnace including a withdrawal region in a lower end, positioning a mold within the casting furnace, positioning a molten material in the mold, partially withdrawing the mold a withdrawal distance through the withdrawal region in the casting furnace, the withdrawal distance providing a partially withdrawn portion, then reinserting at least a portion of the partially withdrawn portion into the casting furnace through the withdrawal region, and then completely withdrawing the mold from the casting furnace. The reinserting at least partially re-melts a solidified portion within the partially withdrawn portion to reduce or eliminate freckle grains. The cast article includes a microstructure and occurrence of freckle grains corresponding to being formed by a process comprising partially withdrawing, reinserting, and completely withdrawing of a mold from a casting furnace to form the cast article. 1. A casting method in a casting furnace , the casting furnace comprising a withdrawal region in a lower end , the method comprising:positioning a mold within the casting furnace;positioning a molten material in the mold;partially withdrawing the mold a withdrawal distance through the withdrawal region in the casting furnace, the withdrawal distance providing a partially withdrawn portion, at least partially solidifying the partially withdrawn portion; thenreinserting at least a portion of the partially withdrawn portion into the casting furnace through the withdrawal region, at least partially re-melting the partially withdrawn portion; and thencompletely withdrawing the mold from the casting furnace through the withdrawal region to produce a directionally solidified or single crystal cast article;wherein at least partially re-melting the partially withdrawn portion reduces or eliminates freckle grains from the partially withdrawn portion.2. The casting method of ...

Method for producing hot-forged material

To provide a method for producing a hot forged material in air, using a Ni-based super alloy for the die, which is advantageous in terms of the service life of the die, and using a glass-based lubricant which hardly causes any chemical reaction promoting oxidative corrosion. A method for producing a hot forged material, by placing on a lower die a material for hot forging, of which part or all of the surface is coated with a glass-based lubricant, and pressing the material for hot forging with the lower die and an upper die, to form a hot forged material, wherein one or both of the lower die and the upper die are made of a Ni-based superalloy, and wherein the surface of the die in contact with the material for hot forging is coated with a glass-based lubricant containing SiO2 as a main component, in which the total content of alkali metal oxides is 0 to 10.0% in mass %.

NICKEL ALLOYS FOR EXHAUST SYSTEM COMPONENTS

Disclosed are nickel alloys for exhaust system components having improved tensile strength, fatigue strength, oxidation resistance, and abrasion resistance at a high temperature condition. A nickel alloy for exhaust system components according to an embodiment is used for exhaust system components of a vehicle engine, the nickel alloy including: 0.01 to 0.2 wt % of C; 0.1 to 1.0 wt % of Si; 0.1 to 1.5 wt % of Mn; 8 to 24 wt % of Cr; 0.1 to 2.5 wt % of Nb; 0.1 to 4.0 wt % of Al; 0.01 to 1 wt % of Co; 0.01 to 5.0 wt % of Mo; 0.01 to 4 wt % of W; 0.1 to 1 wt % of Ta; 0.1 to 2.4 wt % of Ti; 4.0 to 11.0 wt % of Fe; a remainder being Ni; and inevitable impurities. 1. A nickel alloy for exhaust system components , wherein the nickel alloy is used for exhaust system components of a vehicle engine , the nickel alloy comprising:0.01-0.2 wt % C;0.1-1.0 wt % Si;0.1-1.5 wt % Mn;8-24 wt % Cr;0.1-2.5 wt % Nb;0.1-4.0 wt % Al;0.01-1 wt % Co;0.01-5.0 wt % Mo;0.01-4 wt % W;0.1-1 wt % Ta;0.1-2.4 wt % Ti;4.0-11.0 wt % Fe; anda remainder comprising Ni and any impurities.2. The nickel alloy of claim 1 , wherein the nickel alloy contains a Ta—Ti based compound and a complex carbide of (Cr claim 1 , Mo)C.3. The nickel alloy of claim 2 , wherein the nickel alloy has a tensile strength of 950 Mpa or more at a temperature higher than 20° C.4. The nickel alloy of claim 3 , wherein the nickel alloy has a fatigue strength of 350 Mpa or more at the temperature higher than 20° C.5. The nickel alloy of claim 4 , wherein the nickel alloy has an oxidation weight gain of 0.7 g/mor less at the temperature higher than 20° C.6. The nickel alloy of claim 5 , wherein the nickel alloy has an abrasion amount of 2.0 mg or less at the temperature higher than 20° C.7. The nickel alloy of claim 1 , wherein the nickel alloy has a tensile strength of 950 Mpa or more at a temperature higher than 20° C.8. The nickel alloy of claim 7 , wherein the nickel alloy has a fatigue strength of 350 Mpa or more at the ...

LOW RHENIUM SINGLE CRYSTAL SUPERALLOY FOR TURBINE BLADES AND VANE APPLICATIONS

A low rhenium nickel-base superalloy for single crystal casting that exhibits excellent high temperature creep resistance, while also exhibiting other desirable properties for such alloys, comprises 5.60% to 5.80% aluminum by weight, 9.4% to 9.9% cobalt by weight, 4.9% to 5.5% chromium by weight, 0.08% to 0.35% hafnium by weight, 0.50% to 0.70% molybdenum by weight, 1.4% to 1.6% rhenium by weight, 8.1% to 8.5% tantalum by weight, 0.60% to 0.80 titanium by weight, 7.6 to 8.0% tungsten by weight the balance comprising nickel and minor amounts of incidental impurity elements. 1. A nickel-base superalloy for single crystal casting , comprising:5.60% to 5.80% aluminum by weight;9.4% to 9.9% cobalt by weight;4.9% to 5.5% chromium by weight;0.08% to 0.35% hafnium by weight;0.50% to 0.70% molybdenum by weight;1.4% to 1.6% rhenium by weight;8.1% to 8.5% tantalum by weight;0.60% to 0.80 titanium by weight;7.6 to 8.0% tungsten by weight;the balance comprising nickel and minor amounts of incidental elements, the total amount of incidental elements being about 1% or less; andwherein the casting exhibits a rupture life of at least about 200.2 hours at a temperature of 1800° F. under a load of 36.0 ksi.2. The casting of comprising:about 5.72% aluminum by weight;about 9.7% cobalt by weight;about 5.4% chromium by weight;about 0.30% hafnium by weight;about 0.59% molybdenum by weight;about 1.5% rhenium by weight;about 8.3% tantalum by weight;about 0.71% titanium by weight; andabout 7.8% tungsten by weight.3. The casting of claim 1 , exhibiting a rupture life of at least about 983.5 hours at a temperature of 1600° F. under a load of 65 ksi claim 1 , and a rupture life of at least 199.6 hours at a temperature of 1900° F. under a load of 25 ksi.4. The casting of claim 1 , wherein the time to 1% creep at a temperature of 1800° F. under a load of 36 ksi is at least 109.7 hours.5. The casting of claim 4 , wherein the time to 1% creep at a temperature of 1600° F. under a load of 65 ksi is at ...

High oxidation-resistant alloy and gas turbine applications using the same

An alloy is disclosed, encompassing reduced amounts of Hafnium and Carbon so as to achieve an excellent oxidation resistance, as well as gas turbine applications using the same.

Arcuate Seed Casting Method

A casting method includes forming a seed. The seed has a first end and a second end. The forming includes bending a seed precursor. The seed second end is placed in contact or spaced facing relation a chill plate. The first end is contacted with molten material. The molten material is cooled and solidifies so that a crystalline structure of the seed propagates into the solidifying material. The forming further includes inserting the bent seed precursor into a sleeve leaving the bent seed precursor protruding from a first end of the sleeve 1. A casting method comprising:forming a seed, the seed having a first end and a second end, the forming including bending a seed precursor;placing the seed second end in contact or spaced facing relation a chill plate;contacting the first end with molten material; andcooling and solidifying the molten material so that a crystalline structure of the seed propagates into the solidifying material,wherein:the forming further comprises inserting the bent seed precursor into a sleeve leaving the bent seed precursor protruding from a first end of the sleeve.2. The method of wherein:the sleeve holds the bent seed precursor compressed.3. The method of whereinthe sleeve has a second end, the bent seed precursor has a first end and a second end, the protruding being of a portion of the bent seed precursor proximate the first end of the bent seed precursor, the second end of the bent seed precursor captured by an internal shoulder of the sleeve.4. The method of whereinthe sleeve has a second end, the bent seed precursor has a first end and a second end, the protruding being of a portion of the bent seed precursor proximate the first end of the bent seed precursor, the second end of the bent seed precursor captured by a slot of the sleeve.5. A casting method comprising:forming a seed, the seed having a first end and a second end and an inner diameter (ID) surface and an outer diameter (OD) surface;placing the seed second end in contact or ...

HIGH-TEMPERATURE NICKEL-BASED ALLOYS

The present disclosure relates to novel nickel-base alloy compositions including 7.25-7.75 wt % Cr, 0.6-1.0 wt % Mo, 8.5-9.1 wt % W, 6.0-6.4 wt % Al, 0.6-1.0 wt % Ti, 0.06-0.10 wt % C, 0.01-0.02 wt % B, 0.4-0.6 wt % Hf, and at least one of: 8.6-9.6 wt % Co and 4.0-4.8 wt % Ta; or 8.6-9.4 wt % Co, 3.8-4.4 wt % Ta, and 0.4-0.6 wt % Re, with the balance being nickel and trace impurities. Gas turbine blades or guide vanes are also provided, where the blades or vanes are formed using an alloy having such compositions. 1. A nickel-based alloy comprising:7.25-7.75 wt % Cr;0.6-1.0 wt % Mo;8.5-9.1 wt % W;6.0-6.4 wt % Al;0.6-1.0 wt % Ti;0.06-0.10 wt % C;0.01-0.02 wt % B;0.4-0.6 wt % Hf; andone of:8.6-9.6 wt % Co and 4.0-4.8 wt % Ta; or8.6-9.4 wt % Co, 3.8-4.4 wt % Ta, and 0.4-0.6 wt % Re,with the balance consisting of Ni and trace impurities.2. The alloy of claim 1 , comprising:8.6-9.6 wt % Co and 4.0-4.8 wt % Ta.3. The alloy of claim 1 , comprising:8.6-9.4 wt % Co, 3.8-4.4 wt % Ta, and 0.4-0.6 wt % Re.4. The nickel-based alloy of claim 1 , having a composition of:7.5 wt % Cr;0.8 wt % Mo;8.8 wt % W;6.2 wt % Al;0.8 wt % Ti;0.08 wt % C;0.015 wt % B;0.5 wt % Hf; andone of:9.1 wt % Co and 4.4 wt % Ta; or9.0 wt % Co, 4.1 wt % Ta, and 0.5 wt % Re,with the balance consisting of Ni and trace impurities.5. The alloy of claim 4 , comprising:9.1 wt % Co and 4.4 wt % Ta.6. The alloy of claim 4 , comprising:9.0 wt % Co, 4.1 wt % Ta, and 0.5 wt % Re.7. The alloy of claim 4 , wherein an amount of Al+Ta+Ti is between 10.6 and 12.2 wt %.9. The gas turbine component of claim 8 , wherein the nickel-based alloy comprises 8.6-9.6 wt % Co and 4.0-4.8 wt % Ta.10. The gas turbine component of claim 8 , wherein the nickel-based alloy comprises 8.6-9.4 wt % Co claim 8 , 3.8-4.4 wt % Ta claim 8 , and 0.4-0.6 wt % Re.11. The gas turbine component of claim 8 , wherein the nickel-based alloy has a composition of:7.5 wt % Cr;0.8 wt % Mo;8.8 wt % W;6.2 wt % Al;0.8 wt % Ti;0.08 wt % C;0.015 wt % B;0.5 wt % ...

HIGH TEMPERATURE ALLOY FOR CASTING ENGINE VALVES

A high temperature alloy is disclosed. The high temperature alloy may have on a weight basis: about 9.0-10.0 weight % of Co, about 0.25 weight % maximum of Fe, about 8.0-9.0 weight % of Cr, about 4.75-5.50 weight % of Al, about 1.0-1.5 weight % of Ti, about 0-2.0 weight % of Mo, about 6.0-9.0 weight %, of W, about 0.12-0.18 weight % of C, about 0.01-0.03 weight % of Zr, about 0.005-0.015 weight % of B, about 0.5-1.5 weight % of Ta, a balance of Ni, and incidental impurities. 120-. (canceled)21. A high temperature alloy , comprising , on a weight basis:Co: 9.0-10.0 weight %,Cr: 8.0-9.0 weight %,Al: 4.75-5.50 weight %,Ti: 1.0-1.5 weight %,Mo: 0-2.0 weight %,W: 6.0-9.0 weight %,C: 0.12-0.18 weight %,Zr: 0.01-0.03 weight %,B: 0.005-0.015 weight %,Ta: 0.5-1.5 weight %, anda balance of Ni and incidental impurities.22. The high temperature alloy of claim 21 , wherein Cr is about 8.5 weight %.23. The high temperature alloy of claim 22 , wherein Mo is about 1.75 weight %.24. The high temperature alloy of claim 23 , wherein W is about 7.5 weight %.25. The high temperature alloy of claim 24 , wherein Ta is about 1.25 weight %.26. A high temperature alloy claim 24 , comprising claim 24 , on a weight basis:Co: 4.0-7.0 weight %,Cr: 15.0-17.0 weight %,Al: 4.75-5.50 weight %,Ti: 0.75-1.5 weight %,Mo: 0-2.0 weight %,Nb: 0-0.7 weight %,W: 1.0-3.0 weight %,C: 0.12-0.18 weight %,Zr: 0.01-0.03 weight %,B: 0.005-0.015 weight %,Ta: 0.5-1.5 weight %, anda balance of Ni and incidental impurities.27. The high temperature alloy of claim 26 , including claim 26 , on a weight basis:Co: about 7.0 weight %,Cr: about 16.0 weight %,Al: about 5.0 weight %,Ti: about 1.0 weight %,Mo: about 1.5 weight %,Nb: about 0.5 weight %,W: about 1.5 weight %,C: about 0.15 weight %,Zr: about 0.02 weight %,B: about 0.01 weight %,Ta: about 1.0 weight %, anda balance of Ni and incidental impurities.28. The high temperature alloy of claim 27 , wherein a solidification temperature range of the high temperature alloy is ...

Ni-Al BASE MATERIAL HAVING OPTIMIZED OXIDATION RESISTANT AT HIGH TEMPERATURES AND FURNACE TRANSFER ROLLS MADE THEREFROM

A high temperature oxidation resistant nickel-aluminide alloy composition and furnace rolls formed therefrom. The inventive nickel-aluminide alloy composition comprises 0.08-0.1 wt. % Zr, 2.5-3.0 wt. % Mo, 7.5-8.5 wt. % Al, 7.5-8.5 wt. % Cr, about 0.01 wt. % B and the balance being substantially nickel. 1. A nickel-aluminide alloy comprising 0.15 wt % or less Zr.2. The nickel-aluminide alloy of claim 1 , wherein said Zr ranges from about 0.08 -0.1 wt %.3. The nickel-aluminide alloy of claim 1 , wherein said alloy further comprises from about 2.5 to 3.0 wt. % Mo.4. The nickel-aluminide alloy of claim 4 , wherein said alloy further comprises about 2.8 wt % Mo.5. The nickel-aluminide alloy of claim 1 , wherein said alloy further comprises from about 7.5 to 8.5 wt. % Al.6. The nickel-aluminide alloy of claim 5 , wherein said alloy further comprises from about 7.5 to 8.5 wt. % Cr.7. The nickel-aluminide alloy of claim 1 , wherein said alloy further comprises about 0.015 wt. % B or less.8. The nickel-aluminide alloy of claim 7 , wherein said alloy further comprises about 0.01 wt. % B.9. The nickel-aluminide alloy of claim 1 , wherein said alloy further comprises in wt. %:C-0.05 max; Si-0.1 max; Fe-0.3 max; S-0.005 max; Mn-0.1 max; P-0.01 max; and Cu-0.3 max.10. The nickel-aluminide alloy of claim 9 , wherein said alloy contains no more than trace amounts of the other elements from group IVB claim 9 , VB and VIB of the periodic table.11. A furnace roll for a high temperature furnace comprising a cast roll of a nickel-aluminide alloy comprising 0.15 wt % or less Zr.12. The furnace roll of claim 11 , wherein said Zr ranges from about 0.08 -0.1 wt %.13. The furnace roll of claim 11 , wherein said alloy further comprises from about 2.5 to 3.0 wt. % Mo.14. The furnace roll of claim 14 , wherein said alloy further comprises about 2.8 wt % Mo.15. The furnace roll of claim 11 , wherein said alloy further comprises from about 7.5 to 8.5 wt. % Al.16. The furnace roll of claim 15 , ...

NICKEL-BASED ALLOY AND TURBINE COMPONENT HAVING NICKEL-BASED ALLOY

A nickel-based alloy and a turbine component are disclosed. The alloy includes, by weight, between about 0.8% and about 1.3% hafnium, between about 5.7% and about 6.4% aluminum, between about 7.0% and about 10.0% cobalt, up to about 0.1% carbon, up to about 8.7% chromium, up to about 0.6% molybdenum, up to about 9.7% tungsten, up to about 0.9% titanium, up to about 0.02% boron, up to about 0.1% manganese, up to about 0.06% silicon, up to about 0.01% phosphorus, up to about 0.004% sulfur, up to about 0.02% zirconium, up to about 1.8% niobium, up to about 0.1% vanadium, up to about 0.1% copper, up to about 0.2% iron, up to about 0.003% magnesium, up to about 0.002% oxygen, up to about 0.002% nitrogen, and a balance nickel. The turbine component is a turbine bucket, a turbine nozzle, or any other suitable turbine component including the alloy. 1. A nickel-based alloy , comprising , by weight:between about 0.8% and about 1.3% hafnium, between about 5.7% and about 6.4% aluminum, between about 7.0% and about 10.0% cobalt, up to about 0.1% carbon, up to about 8.7% chromium, up to about 0.6% molybdenum, up to about 9.7% tungsten, up to about 0.9% titanium, up to about 0.02% boron, up to about 0.1% manganese, up to about 0.06% silicon, up to about 0.01% phosphorus, up to about 0.004% sulfur, up to about 0.02% zirconium, up to about 1.8% niobium, up to about 0.1% vanadium, up to about 0.1% copper, up to about 0.2% iron, up to about 0.003% magnesium, up to about 0.002% oxygen, up to about 0.002% nitrogen, and a balance nickel.2. The alloy of claim 1 , wherein the hafnium is present at a concentration of claim 1 , by weight claim 1 , between about 0.8% and about 1.1%.3. The alloy of claim 1 , further comprising tantalum at a concentration of claim 1 , by weight claim 1 , between about 3.1% and about 3.6%.4. The alloy of claim 1 , wherein the alloy includes a directionally-solidified microstructure.5. The alloy of claim 1 , wherein the alloy is a portion of a turbine bucket.6. ...

NI-BASE SUPERALLOY COMPOSITION AND METHOD FOR SLM PROCESSING SUCH NI-BASE SUPERALLOY COMPOSITION

A Ni-base superalloy composition to be used for powder-based additive manufacturing (AM) technology, such as selective laser melting (SLM) or electron beam melting (EBM). The cracking susceptibility during an AM process is considerably reduced by controlling the amount of elements, especially Hf, that form low-melting eutectics. 1. Ni-base superalloy composition wherein:the Ni-based superalloy is configured to form a γ/γ′-microstructure after a heat treatment and used for additive manufacturing of three dimensional articles with a γ/γ′-microstructure, wherein the amount of elements that form low melting eutectics is controlled.2. The Ni-base superalloy composition according to claim 1 , wherein the Ni based superalloy is used in powder bed-based additive manufacturing technology and the Ni based super alloy comprises first elements not bound in precipitates forming low-melting eutectics claim 1 , wherein the amount of the first elements is increased with respect to standard compositions.3. The Ni-base superalloy according to claim 2 , wherein the first elements comprise Hf.4. The Ni-base superalloy composition according to claim 3 , wherein the first elements comprise Hf with an Hf content in the range 1.2 wt-% to 5 wt-%.5. The Ni-base superalloy composition according to claim 4 , wherein the first elements comprise Hf with an Hf content in the range 1.6 wt-% to 3.5 wt-%.6. The Ni-base superalloy composition according to claim 5 , wherein the first elements comprise Hf with an Hf content in the range 1.7 wt-% to 2.8 wt-%.7. The Ni-base superalloy composition as claimed in claim 3 , wherein the superalloy composition contains a minimum amount of >1.2 wt-% Hf claim 3 , and that C is present with a Hf [at-%]/C [at-%] ratio >1.55.8. The Ni-base superalloy composition according th claim 7 , wherein C is defined as a Hf [at-%]/C [at-%] ratio >1.91.9. The Ni-base superalloy composition according to claim 7 , wherein C is defined as C>0.01 wt-% for grain boundary ...

SUPERALLOYS AND COMPONENTS FORMED THEREOF

A gamma prime nickel-base superalloy and components formed therefrom that exhibit improved high-temperature dwell capabilities, including creep and hold time fatigue crack growth behavior. A particular example of a component is a powder metallurgy turbine disk of a gas turbine engine. The gamma-prime nickel-base superalloy contains, by weight: 16.0 to 30.0% cobalt; 9.5 to 12.5% chromium; 4.0 to 6.0% tantalum; 2.0 to 4.0% aluminum; 2.0 to 3.4% titanium; 3.0 to 6.0% tungsten; 1.0 to 4.0% molybdenum; 1.5 to 3.5% niobium; up to 1.0% hafnium; 0.02 to 0.20% carbon; 0.01 to 0.05% boron; 0.02 to 0.10% zirconium; the balance essentially nickel and impurities. The superalloy has a W+Nb−Cr value of at least −6, is free of observable amounts of sigma and eta phases, and exhibits a time to 0.2% creep at 1300° F. and 100 ksi of at least 1000 hours. 1. A gamma-prime nickel-base superalloy comprises , by weight:16.0 to 30.0% cobalt;9.5 to 12.5% chromium;4.0 to 6.0% tantalum;2.0 to 4.0% aluminum;2.0 to 3.4% titanium;3.0 to 6.0% tungsten;1.0 to 4.0% molybdenum;1.5 to 3.5% niobium;up to 1.0% hafnium;0.02 to 0.20% carbon;0.01 to 0.05% boron;0.02 to 0.10% zirconium;the balance essentially nickel and impurities;wherein the superalloy has a W+Nb−Cr value of at least −6, is free of observable amounts of sigma and eta phases, and exhibits a time to 0.2% creep at 1300° F. and 100 ksi of at least 1000 hours.2. The gamma-prime nickel-base superalloy according to claim 1 , wherein the chromium content is 10.0 to 12.5 weight percent.3. The gamma-prime nickel-base superalloy according to claim 1 , wherein the niobium content is 1.8 to 2.2 weight percent.4. The gamma-prime nickel-base superalloy according to claim 1 , wherein the tungsten content is 3.0 to 5.0 weight percent.5. The gamma-prime nickel-base superalloy according to claim 1 , wherein the chromium content is 10.0 to 12.5 weight percent claim 1 , the niobium content is 1.8 to 2.2 weight percent claim 1 , and the tungsten content is 3.0 ...

BARRIER LAYERS COMPRISING NI-INCLUSIVE ALLOYS AND/OR OTHER METALLIC ALLOYS, DOUBLE BARRIER LAYERS, COATED ARTICLES INCLUDING DOUBLE BARRIER LAYERS, AND METHODS OF MAKING THE SAME

Certain example embodiments relate to Ni-inclusive ternary alloy being provided as a barrier layer for protecting an IR reflecting layer comprising silver or the like. The provision of a barrier layer comprising nickel, chromium, and/or molybdenum and/or oxides thereof may improve corrosion resistance, as well as chemical and mechanical durability. In certain examples, more than one barrier layer may be used on at least one side of the layer comprising silver. In still further examples, a NiCrMo-based layer may be used as the functional layer, rather than or in addition to as a barrier layer, in a coating. 126-. (canceled)27. A coated article including a coating supported by a glass substrate , the coating from the glass substrate outwardly comprising:a first dielectric layer on the glass substrate;an oxided layer comprising, by % metal, 54-58 wt. % Ni, 20-22.5 wt. % Cr, 12.5-14.5 wt. % Mo, 1-5 wt. % W, and 1-5 wt. % Fe over at least the IR reflecting layer;a second dielectric layer on the glass substrate and over at least the first dielectric layer and the oxided layer comprising, by % metal, 54-58 wt. % Ni, 20-22.5 wt. % Cr, 12.5-14.5 wt. % Mo, 1-5 wt. % W, and 1-5 wt. % Fe;wherein the oxided layer comprising, by % metal, 54-58 wt. % Ni, 20-22.5 wt. % Cr, 12.5-14.5 wt. % Mo, 1-5 wt. % W, and 1-5 wt. % Fe is located between and directly contacting the first and second dielectric layers;a first IR reflecting layer comprising silver over at least the first and second dielectric layers;a third dielectric layer located over at least the first IR reflecting layer.28. The coated article of claim 27 , wherein the coating is a low-E coating.29. The coated article of claim 27 , wherein the first and second dielectric layers comprise silicon nitride.30. The coated article of claim 27 , wherein the coating further comprises a dielectric layer comprising zirconium oxide located over at least the third dielectric layer.31. The coated article of claim 27 , wherein the oxided ...

PRECIPITATION STRENGTHENED NICKEL BASED WELDING MATERIAL FOR FUSION WELDING OF SUPERALLOYS

A precipitation strengthened nickel based welding material that comprises 5-15 wt. % Co, 5-25 wt. % Cr, 1-6 wt. % Al, 0.05-0.2 wt. % C, 0.015-0.4 wt. % B, 1-3 wt. % Si, chemical elements selected from among tungsten and molybdenum from about 1 to 20 wt. %, chemical elements selected from among titanium, zirconium, hafnium, tantalum and rhenium from about 1 to 18 wt. % and nickel with impurities to balance, wherein the boron content is inversely proportional to silicon content and decreases from about 0.3 wt. % to about 0.015 wt. % when silicon content increases from about 1 wt. % to about 3 wt. % produces sound high strength and high oxidation resistance crack free welds on precipitation strengthened superalloys and single crystal materials. 4. The method of precipitation strengthening nickel based welding material for fusion welding of superalloys of claim 3 , wherein the boron content is reduced proportionately from about 0.4 wt. % to about 0.1 wt. % with a proportionate increase in the silicon content from about 1 wt. % to about 3 wt. % such that the total boron and silicon content ranges from about 1.4 wt. % to 3.1 wt. %.5. The method according to claim 1 , wherein the precipitation strengthened nickel based welding material for fusion welding of superalloys produced is a welding powder.6. The method according to claim 1 , wherein the precipitation strengthened nickel based welding material for fusion welding of superalloys produced is a welding wire.7. The method according to claim 1 , wherein the precipitation strengthened nickel based welding material for fusion welding of superalloys produced is for use in a repair section of a turbine engine component.11. The precipitation strengthened nickel based welding material claimed in wherein the boron content reduced proportionately from about 0.4 wt. % to about 0.1 wt. % with a proportionate increase in the silicon content from about 1 wt. % to about 3 wt. % such that the total boron and silicon content ranges ...

ALLOY, PROTECTIVE LAYER AND COMPONENT

Known protective layers having a high Cr content and additionally a silicon form brittle phases which additionally become brittle under the influence of carbon during use. The protective layer hereof has a composition 22% to 24% cobalt (Co), 10.5% to 11.5% aluminum (AI), 0.2% to 0.4% yttrium (Y) and/or at least one equivalent metal from the group comprising scandium and the rare earth elements, 14% to 16% chrome (Cr), optionally 0.3% to 0.9% tantalum, the remainder nickel (Ni). 1. An alloy ,which contains at least the following elements (data in wt %):22%-24% cobalt (Co),in particular 23% cobalt (Co),14%-16% chromium (Cr),10.5%-11.5% aluminum (Al),0.2%-0.4% of at least one metal from the group comprising scandium (Sc) and/or rare earth elements, includingin particular yttrium (Y), andoptionally from 0.3% to 0.9% tantalum (Ta).2. The alloy as claimed in claim 1 , containing 0.3 wt % yttrium (Y).3. The alloy as claimed in claim 1 , not containing rhenium (Re).4. The alloy as claimed in claim 1 , not containing silicon (Si).5. The alloy as claimed in claim 1 , which contains at least 0.4 wt % tantalum (Ta).6. The alloy as claimed in claim 1 , not containing zirconium (Zr) and/or not containing titanium (Ti) and/or not containing gallium (Ga) and/or not containing germanium (Ge) and/or not containing platinum (Pt) and/or not containing hafnium (Hf) and/or not containing cerium (Ce) and/or not containing iron (Fe) and/or not containing palladium (Pd) and/or not containing boron (B) and/or not containing carbon (C).7. The alloy as claimed in claim 1 , consisting of cobalt claim 1 , chromium claim 1 , aluminum claim 1 , yttrium claim 1 , nickel and the optional constituent tantalum.8. The alloy as claimed in claim 7 , consisting of cobalt claim 7 , chromium claim 7 , aluminum claim 7 , yttrium claim 7 , nickel and tantalum.9. The alloy as claimed in claim 1 , in which nickel (Ni) forms a matrix of the alloy.10. A protective layer for protecting a component against ...

ALLOY, PROTECTIVE LAYER AND COMPONENT

Known protective layers having a high Cr-content and a silicone in addition, form brittle phases that embrittle further under the influence of carbon during use. The protective layer according to the invention is composed of 22% to 26% cobalt (Co), 10.5% to 12% aluminum (Al), 0.2% to 0.4% Yttrium (Y) and/or at least one equivalent metal from the group comprising Scandium and the rare earth elements, 15% to 16% chrome (Cr), optionally 0.3% to 1.5% tantal, the remainder nickel (Ni). 116-. (canceled)17. An alloy , which contains at least the following elements (data in wt %): 22%-26% cobalt (Co) , 15%-16% chromium (Cr) , 10.5%-12% aluminum (Al) , 0.2% -0.6% , of at least one metal from the group comprising scandium (Sc) and/or the rare earth elements , and remainder nickel (Ni).18. The alloy as claimed in claim 17 , containing 0.5 wt % yttrium (Y).19. The alloy as claimed in claim 17 , not containing rhenium (Re).20. The alloy as claimed in claim 17 , not containing silicon (Si).21. The alloy as claimed in claim 17 , which contains tantalum (Ta).22. The alloy as claimed in claim 17 , not containing zirconium (Zr) and/or not containing titanium (Ti) and/or not containing gallium (Ga) and/or not containing germanium (Ge) and/or not containing platinum (Pt) and/or not containing hafnium (Hf) and/or not containing cerium (Ce) and/or not containing iron (Fe) and/or not containing palladium (Pd) and/or not containing boron (B) and/or not containing carbon (C).2321. The alloy as claimed in claim 17 , consisting of cobalt claim 17 , chromium claim 17 , aluminum claim 17 , yttrium claim 17 , nickel and the optional constituent tantalum.24. The alloy as claimed in claim 17 , in which nickel (Ni) forms the matrix.25. The alloy as claimed in claim 17 , which comprises 1.2%-1.5% tantalum (Ta).26. A protective layer for protecting a component against corrosion and/or oxidation claim 17 , particularly at high temperatures claim 17 , wherein the layer has the composition of the alloy ...

NI-BASED CASTING SUPERALLOY AND CAST ARTICLE THEREFROM

It is an objective of the invention to provide a low cost Ni-based casting superalloy suitable for casting articles having a far better balance among a high-temperature mechanical strength, a grain boundary strength and a oxidation resistance than conventional Ni-based superalloy cast articles. There is provided an Ni-base casting superalloy including: in mass %, 0.03 to 0.15% of C; 0.005 to 0.04% of B; 0.01 to 1% of Hf; 0.05% or less of Zr; 3.5 to 4.9% of Al; 4.4 to 8% of Ta; 2.6 to 3.9% of Ti; 0.05 to 1% of Nb; 8 to 12% of Cr; 1 to 6.9% of Co; 4 to 10% of W; 0.1 to 0.95% of Mo; 0.02 to 1.1% of Si and/or 0.1 to 3% of Fe; and the balance including Ni and incidental impurities. 1. An Ni-based casting superalloy comprising: 0.03 to 0.15 mass % of C; 0.005 to 0.04 mass % of B; 0.01 to 1 mass % of Hf; 0.05 mass % or less of Zr; 3.5 to 4.9 mass % of Al; 4.4 to 8 mass % of Ta; 2.6 to 3.9 mass % of Ti; 0.05 to 1 mass % of Nb; 8 to 12 mass % of Cr; 1 to 6.9 mass % of Co; 4 to 10 mass % of W; 0.1 to 0.95 mass % of Mo; at least one of 0.02 to 1.1 mass % of Si and 0.1 to 3 mass % of Fe; and the balance including Ni and inevitable impurities.2. The Ni-based casting superalloy according to claim 1 , wherein content of the Si is more than 0.4 mass % and total content of the Al claim 1 , the Ti and the Si is 8.8 mass % or less.3. The Ni-based casting superalloy according to claim 1 , wherein content of the Fe is 1 mass % or more and total content of the Co and the Fe is from 1 mass % to 6.9 mass %.4. The Ni-based casting superalloy according to claim 1 , wherein content of the Co is from 1 mass % to 4.9 mass % and content of the Mo is from 0.1 mass % to 0.45 mass %.5. An article cast from the Ni-based casting superalloy according to .6. The article according to claim 5 , wherein the article has a matrix consisting entirely of columnar grains claim 5 , entirely of a single crystal claim 5 , or partially of columnar grains and partially of a single crystal.7. The article according ...

REPAIR OR REMANUFACTURE OF COMBUSTOR LINER PANELS WITH AN OXIDATION RESISTANT BRAZE

A method to fill a gap in a liner panel according to one disclosed non-limiting embodiment of the present disclosure includes: applying a nickel braze alloy composition onto a gap in a liner panel; subjecting the nickel braze alloy composition to a melt cycle; and subjecting the nickel braze alloy composition to a diffusion cycle after the melt cycle.

POWDER ALLOY COMPOSITION, GAS TURBINE ENGINE COMPONENT AND METHOD FOR MANUFACTURE OF THE SAME

A Ni-based superalloy powder having a freezing range of not more than 80° C. is disclosed, with a composition, expressed in weight percent, of: Ni; 9-25 Co; 3-15 Cr; 0-5 Mo; 0-12 W; 3-9 Al; 0-6.5 Nb; 0.3-1 C; 0-6.5 Ta; 0-3 Ti, and incidental impurities. It is disclosed in methods for manufacturing or repair of gas turbine engine components such as gas turbine blades using additive layer manufacturing techniques. 3. The Ni-based superalloy powder of claim 1 , wherein the powder has an average (d) particle size in the range 10-150 μm.4. The Ni-based superalloy powder of claim 1 , wherein the powder has a particle size distribution such that dand dare in the range 10-150 μm.5. The Ni-based superalloy powder of claim 1 , wherein the powder has an average (d) particle size in the range 15-45 μm.6. The Ni-based superalloy powder of claim 1 , wherein the powder has a particle size distribution such that dand dare in the range 15-45 μm.7. The Ni-based superalloy powder of claim 1 , wherein the powder has an average (d) particle size in the range 45-110 μm.8. The Ni-based superalloy powder of claim 1 , wherein the powder has a particle size distribution such that dand dare in the range 45-110 μm.9. A method of manufacturing a component claim 1 , the method comprising the steps of:providing a Ni-based superalloy powder; and{'claim-ref': {'@idref': 'CLM-00001', 'claim 1'}, 'performing additive layer manufacturing by melting and solidifying the Ni-based superalloy powder to form one layer of the Ni-based superalloy powder in a predetermined shape, disposing a further layer of the Ni-based superalloy powder over said one layer and melting and solidifying said further layer of the Ni-based superalloy powder in a predetermined shape, and repeating as needed to form the component, wherein the Ni-based superalloy powder is according to .'}10. The method of claim 9 , wherein the component is a gas turbine engine component.11. The method of claim 10 , further comprising a step of ...

Ni-Based Superalloy Powder for Additive Manufacturing and an Article Made Therefrom

A nickel base superalloy powder for additive manufacturing applications is disclosed. The alloy powder has the following broad weight percent composition:C 0-0.1Mn0.5 max.Si  0-0.03Cr 4-16Fe 0-1.5Mo0-6W0-8Co 0-15Ti0-2Al0.5-5.5Nb0-6Ta 7.5-14.5Hf 0-2.0Zr 0-0.1Re0-6Ru0-3B  0-0.03The balance of the alloy is at least 50% nickel and the usual impurities. An article of manufacture made from the alloy is also disclosed.

BULK NICKEL-PHOSPHORUS-BORON GLASSES BEARING MANGANESE

The disclosure is directed to Ni—P—B alloys bearing Mn and optionally Cr and Mo that are capable of forming a metallic glass, and more particularly metallic glass rods with diameters at least 1 mm and as large as 5 mm or larger. The disclosure is further directed to Ni—Mn—Cr—Mo—P—B alloys capable of demonstrating a good combination of glass forming ability, strength, toughness, bending ductility, and corrosion resistance. 1. An alloy represented by the following formula (subscripts denote atomic percentages):{'br': None, 'sub': (100-a-b-c)', 'a', 'b', 'c-d', 'd, 'NiMnXPB\u2003\u2003(1)'}where:a is between 0.5 and 10,b is up to 15,c is between 14 and 24,d is between 1 and 8, andwherein X can be Cr and/or Mo and the alloy is capable of forming a metallic glass.2. The alloy according to claim 1 , wherein b is at least 1 claim 1 , and wherein the alloy also comprises at least one of Nb or Ta at a combined atomic concentration of less than 1 percent.3. The alloy according to claim 1 , wherein b is 0 claim 1 , and wherein the alloy also comprises at least one of Nb or Ta at a combined atomic concentration of less than 0.5 percent.4. The alloy according to claim 1 , wherein up to 1 atomic percent of P is substituted by Si.5. The alloy according to claim 1 , wherein Ni is substituted in accordance with at least one of the following up to 50 atomic percent of Ni is substituted by Co claim 1 , up to 30 atomic percent of Ni is substituted by Fe claim 1 , or up to 10 atomic percent of Ni is substituted by Cu.6. The alloy according to claim 1 , wherein the critical rod diameter is at least 1 mm.7. A metallic glass formed of the alloy according to .8. The alloy according to claim 1 , wherein b=0 claim 1 , a is at least 2 and up to 9.5 claim 1 , c is between 16.5 and 21.5 claim 1 , and d is between 1 and 6.5.9. An alloy according to claim 8 , wherein a is between 3 and 8 and the critical rod diameter is at least 2 mm.10. An alloy according to claim 8 , wherein a is between 6 and 7 ...

OXIDE PARTICLE DISPERSION-STRENGTHENED NI-BASE SUPERALLOY

An oxide particle dispersion-strengthened Ni-base superalloy includes Ni, 0.1% by weight to 14.0% by weight of Ru, 0.1% by weight to 14.0% by weight of Al, and inevitable impurities and has a crystal structure containing 0.01% by weight to 3.0% by weight of dispersed oxide particles based on the total amount of the superalloy. 1. An oxide particle dispersion-strengthened Ni-base superalloy having a composition comprising Ni , 0.1% by weight to 14.0% by weight of Ru , 0.1% by weight to 14.0% by weight of Al , and inevitable impurities ,the superalloy also having a crystal structure containing 0.01% by weight to 3.0% by weight of dispersed oxide particles based on the total amount of the superalloy.2. The oxide particle dispersion-strengthened Ni-base superalloy according to claim 1 , which comprises 0.1% by weight to 14.0% by weight of Ru claim 1 , 0.1% by weight to 14.0% by weight of Al claim 1 , and at least one of 0.1% by weight to 14.0% by weight of Re claim 1 , 0.1% by weight to 20.0% by weight of Co claim 1 , 0.1% by weight to 20.0% by weight of Cr claim 1 , 0.1% by weight to 15.0% by weight of Mo claim 1 , 0.1% by weight to 20.0% by weight of W claim 1 , 0.1% by weight to 10.0% by weight of Ti claim 1 , 0.1% by weight to 10.0% by weight of Nb claim 1 , 0.1% by weight to 15.0% by weight of Ta claim 1 , 0.01% by weight to 10.0% by weight of Hf claim 1 , 0.01% by weight to 10.0% by weight of Zr claim 1 , 0.1% by weight to 5.0% by weight of V claim 1 , 0.1% by weight to 10.0% by weight of Pt claim 1 , 0.1% by weight to 10.0% by weight of Pd claim 1 , 0.1% by weight to 10.0% by weight of Ir claim 1 , 0.001% by weight to 1.0% by weight of B claim 1 , or 0.001% by weight to 1.0% by weight of C. The present invention relates to an oxide particle dispersion-strengthened Ni-base superalloy.Components to be exposed to high-temperature environments, such as aircraft engines and power generation gas turbines, are required to be made of materials having high mechanical ...

BRAZE ALLOY COMPOSITIONS AND BRAZING METHODS FOR SUPERALLOYS

A multi-component braze filler alloy comprising 60-70% by weight CM247 superalloy and BRB braze alloy is diffusion brazed to a CM247 alloy base substrate, such as a gas turbine blade or vane. The substrate/braze interface may be subsequently weld-repaired without de-melting and migrating the braze alloy from the interface. The weld zone and surrounding area are solidification crack resistant. After the alloy composition is brazed to the base substrate the component may be returned to service. Thereafter the component remains repairable by welding or re-brazing, if needed to correct future in-service defects. 1. A material for the braze repair of a nickel-base superalloy turbine component comprising a CM247/BRB mixture of CM247 base alloy in the range from approximately 60% to 70% by weight and the balance comprises BRB braze alloy.2. A material as in claim 1 , wherein the nickel-base superalloy turbine component comprises CM247.3. A material as in claim 1 , wherein the Ni-base superalloy component is a turbine vane or blade.4. A material as in claim 1 , wherein the CM247/BRB mixture comprises about 80% of CM247 base alloy by weight and the balance comprises the BRB braze alloy wherein the components brazed with the material are not subjected to temperatures exceeding about 2270 deg. F. during the brazing process.5. A material as in claim 4 , wherein the nickel-base superalloy turbine component comprises CM247.6. A material as in claim 4 , wherein the Ni-base superalloy component is a turbine vane or blade.7. An article of manufacture comprising a Ni-base superalloy component wherein the Ni-base superalloy component has a portion thereof repaired by brazing with a brazing material claim 4 , wherein the brazing material comprises a mixture of CM247 base alloy in the range from about 60% to about 70% by weight and the balance comprising a BRB braze alloy.8. An article of manufacture as in claim 7 , wherein the nickel-base superalloy turbine component comprises CM247.9. ...

Laser powder deposition weld rework for gas turbine engine non-fusion weldable nickel castings

A method of reworking or repairing a component includes removing a casting defect from a component manufactured of a non-fusion weldable base alloy to form a cavity that results in a through hole; sealing the through hole with a backing; and at least partially filling the cavity with a multiple of layers of a multiple of laser powder deposition spots, each of the multiple of laser powder deposition spots formed of a filler alloy, a first layer of the multiple of layers includes a perimeter of the multiple of laser powder deposition spots that overlap a wall of the cavity and the backing.

NICKEL ALLOY

The invention relates to a nickel alloy derived from René 125, but with reduced levels of certain elements (Zr, B, P, S, Si and, to a lesser extent, Ti and Hf) in order to limit the appearance of cracks upon solidification in a moulding process. Specifically, 4.80%≦Al≦5.00%, 1.48%≦Hf≦1.52%, 2.28%≦Ti≦2.33%, 0.005%≦B≦0.01%, 1.77%≦Mo≦1.97%, and Zr≦0.007%. Other elements can have levels that match those of René 125. 1. A nickel alloy , comprising:nickel,9.50% to 9.90% by weight of cobalt,8.70% to 9.00% by weight of chromium,6.65% to 7.05% by weight of tungsten,3.67% to 3.87% by weight of tantalum,0.10% to 0.12% by weight of carbon,1.77% to 1.97% by weight of molybdenum,4.80% to 5.00% by weight of aluminium,1.48% to 1.52% by weight of hafnium,2.28% to 2.33% by weight of titanium,0.005% to 0.01% by weight of boron, andless than 0.007% by weight of zirconium.2. The nickel alloy according to claim 1 , further comprising:less than 0.001% by weight of phosphorous, andless than 0.001% by weight of sulphur.3. The nickel alloy according to claim 1 , comprising: more than 59.83% by weight of nickel.4. The nickel alloy according to claim 1 , wherein a total weight of titanium claim 1 , hafnium and aluminium is less than 8.77%.5. The nickel alloy according to claim 1 , wherein the nickel alloy is suitable for manufacturing a bladed distributor part of an aeronautics engine stator.6. The nickel alloy according to claim 5 , wherein the nickel alloy is treated with a T3R heat treatment. The subject of the invention is a nickel alloy.It has been conceived to improve the foundry manufacture of certain parts of complex shape such as distributor blades used in engine stators in aeronautics.These parts are constituted of blades fitted into platforms, the assembly of which on an engine constitutes a ring. Certain of these parts are traditionally constructed from a nickel alloy known as René 125, but which is particularly liable to produce cracks on moulding, during the solidification of the ...

PROCESS FOR MANUFACTURING A PART MADE OF NICKLE-BASED SUPERALLOY CONTAINING HAFNIUM

The invention relates to a process for manufacturing a part made of nickel-based monocrystalline superalloy containing hafnium. This process is noteworthy in that it comprises the following successive steps consisting in:—manufacturing a nickel-based monocrystalline superalloy that is not doped with hafnium,—manufacturing a part from this superalloy,—directly depositing on said part a layer of hafnium having a thickness of between 50 nm and 800 nm,—carrying out a diffusion treatment of the hafnium so as to form an interdiffusion layer at the surface of said part and to thus obtain a part made of nickel-based monocrystalline superalloy containing hafnium. 1. A process for manufacturing a hafnium-containing nickel-based single-crystal superalloy part , wherein the process comprises the following successive steps consisting in:manufacturing a nickel-based, non-hafnium-doped, single-crystal superalloy,manufacturing a part from this superalloy,depositing, directly on said part, a layer of hafnium having a thickness comprised between 50 nm and 800 nm,carrying out a hafnium diffusion treatment so as to form an interdiffusion layer on the surface of said part, and thereby obtain a hafniumcontaining nickel-based single-crystal superalloy part.2. The process according to claim 1 , wherein the deposition of the layer of hafnium is carried out by physical vapour deposition (PVD).3. The process according to claim 2 , wherein the deposition of the layer of hafnium is carried out by cathode sputtering.4. The process according to claim 1 , wherein the deposition of the layer of hafnium is carried out by chemical vapour deposition (CVD) claim 1 , preferably by a technique selected from low-pressure chemical vapour deposition (LPCVD) claim 1 , chemical vapour aluminizing (CVA) claim 1 , ultrahigh vacuum chemical vapour deposition (UHVCVD) claim 1 , plasma enhanced chemical vapour deposition (PECVD) claim 1 , atmospheric pressure chemical vapour deposition (APCVD) claim 1 , atomic ...

NICKEL-BASE SUPERALLOY

The novel nickel-base superalloy useful in an additive manufacturing process or a powder-based manufacturing process comprises the following composition in wt %: 5. The nickel-base superalloy of claim 1 , in a physical form which is suitable for use in an additive manufacturing process.6. The nickel-base superalloy of claim 1 , in the form of a wire claim 1 , rod or powder suitable for use in an additive manufacturing process.7. The nickel-base superalloy of claim 1 , in the form of a wire claim 1 , rod or powder suitable for use in a directed energy deposition (DED) additive manufacturing process.8. The nickel-base superalloy of claim 5 , which is suitable for use in a manufacturing process selected from laser-based additive manufacturing (LBAM) claim 5 , direct laser deposition (DLD) claim 5 , Laser powder bed fusion (LPBF) claim 5 , Selective Laser Sintering (SLS) electron beam additive manufacturing (EBAM) claim 5 , laser engineered net shaping (LENS) claim 5 , selective laser melting (SLM) claim 5 , SLM three-dimensional printing (SLM 3D printing) claim 5 , direct metal laser sintering (DMLS) claim 5 , direct metal laser sintering three-dimensional printing (DML 3D printing) claim 5 , electron beam melting (EBM) claim 5 , direct metal deposition (DMD) claim 5 , direct metal tooling (DMT) claim 5 , direct metal tooling three-dimensional printing (DMT 3D printing) claim 5 , construction laser additive direct (CLAD) and ion fusion formation (IFF).9. The nickel-base superalloy of claim 1 , in a physical form which is suitable for use in a powder-based manufacturing process.10. The nickel-base superalloy of claim 1 , in the form of a powder suitable for use in a powder-based manufacturing process.11. The nickel-base superalloy of claim 1 , in the form of a powder suitable for use in hot isostatic pressing (HIP).12. The nickel-base superalloy of claim 1 , in the form of a powder suitable for use in metal injection moulding (MIM).13. A metal article claim 1 , ...

High temperature niobium-bearing superalloys

Nickel-base superalloys having gamma prime strengthening precipitates in a gamma matrix and little or no tertiary incoherent phases, such as delta, delta variants and eta.

Nickel Alloy For Repairs

A nickel base repair alloy comprises a blend of about 40 to 60 wt % of a first nickel based braze alloy containing boron, about 15 to 35 wt % of a first nickel based filler material, and the remainder consisting of a blend of a second nickel based filler material and a low melting eutectic braze nickel based alloy. 116-. (canceled)17. A material for repairing a crack in a nickel based alloy component consisting essentially of about 7.0 to 10.0 wt % chromium , about 4.0 to 7.0 wt % tungsten , about 3.0 to 6.0 wt % aluminum , about 1.0 to 5.0 wt % tantalum , about 0.5 to 3.0 wt % boron , about 9.0 to 11.0 wt % cobalt , about 0.5 to 2.0 wt % molybdenum , up to about 2.5 wt % rhenium , about 0.5 to 2.5 wt % hafnium , up to 1.0 wt % titanium , up to 0.03 wt % yttrium , and the balance nickel.18. The material according to claim 17 , wherein said chromium content is about 8.5 to 9.5 wt %.19. The material according to claim 17 , wherein said tungsten content is about 5.0 to 6.2 wt %.20. The material according to claim 17 , wherein said aluminum content is about 4.0 to 5.0 wt %.21. The material according to claim 17 , wherein said titanium content is about 0.15 to 0.4 wt %.22. The material according to claim 17 , wherein said tantalum content is about 3.0 to 4.0 wt %.23. The material according to claim 17 , wherein said boron content is about 1.0 to 1.5 wt %.24. The material according to claim 17 , wherein said cobalt content is about 10 wt % to 11 wt %.25. The material according to claim 17 , wherein said molybdenum content is about 0.9 to 1.3 wt %.26. The material according to claim 17 , wherein said rhenium content is about 1.0 to 2.0 wt %.27. The material according to claim 17 , wherein said hafnium content is about 1.0 to 1.3 wt %.28. The material according to claim 17 , wherein said yttrium content is about 0.01 to 0.02 wt %. (1) Field of the InventionThe present invention relates to a nickel base repair alloy which may be used to repair workpieces, such as turbine ...

NICKEL-BASED SUPERALLOY WITH MICROSTRUCTURE INCLUDING RAFTING-RESISTANT GAMMA PRIME PHASE AND ARTICLE PREPARED THEREFROM

In a non-limiting example, an article having a body including a nickel-based superalloy is provided. The nickel-based superalloy has a microstructure that includes a gamma phase matrix and a gamma prime phase including a plurality of rafting-resistant gamma prime particles dispersed in the gamma phase matrix. The plurality of the rafting-resistant gamma prime particles has an average particle perimeter of about 3 microns to about 15 microns, an average aspect ratio of about 1.2 to about 3, and where the microstructure of the nickel-based superalloy is substantially uniform throughout the body. 1. An article comprising:a body having a first side wall, a second side wall opposite to the first side wall, and a body dimension extending between the first side wall and the second side wall, the body further including a nickel-based superalloy having a microstructure that includes:a gamma phase matrix, anda gamma prime phase including a plurality of rafting-resistant gamma prime particles dispersed in the gamma phase matrix, wherein the plurality of the rafting-resistant gamma prime particles has an average particle perimeter of about 3.0 microns to about 15.0 microns, an average aspect ratio of about 1.2 to about 3.0, and wherein one or both of the average particle perimeter and the average aspect ratio of the plurality of rafting-resistant gamma prime particles have a measured value that is substantially uniform throughout the body dimension of the body.2. The article of claim 1 , wherein the body has a weight of no less than about 15 pounds.3. The article of claim 1 , wherein the body has a weight in a range of about 15 pounds to about 55 pounds.4. The article of claim 1 , wherein the gamma prime phase is present in about 55 volume percent (% v/v) to about 75 volume percent (% v/v) of the superalloy.5. The article of claim 1 , wherein the plurality of the rafting-resistant gamma prime particles has an average particle size of about 1.0 micron to about 6.0 microns.6. The ...

Thermal barrier-coated ni alloy component and manufacturing method thereof

A thermal barrier-coated Ni alloy component includes: a substrate made of a Ni alloy containing Al; an intermediate layer formed on a surface of the substrate; and a thermal barrier layer made of a ceramic and formed on a surface of the intermediate layer. The intermediate layer includes a γ′ layer, which is formed from a γ′-Ni 3 Al phase on the surface on the thermal barrier layer side, and contains Pt.

METHOD, BRAZED ARTICLE, AND BRAZING ASSEMBLY

A method includes heating a brazing material in a braze chamber of a first component to a braze temperature to melt the brazing material. The brazing material flows from the braze chamber, through at least one internal channel of the first component, and into a braze gap between the first component and a second component to braze the first component to the second component. A brazed article includes a first component having a braze chamber and at least one internal channel extending from the braze chamber to an external surface, a second component having at least one braze surface separated from the external surface of the first component by a braze gap, and a braze material in the braze gap. A braze assembly includes a first component, a second component, and a brazing material in the braze chamber. 1. A method comprising:heating a brazing material in a braze chamber of a first component to a braze temperature to melt the brazing material such that the brazing material flows from the braze chamber, through at least one internal channel of the first component, and into a braze gap between the first component and a second component to braze the first component to the second component.2. The method of further comprising positioning the first component in an aperture of the second component to provide the braze gap prior to the heating.3. The method of further comprising tack welding the first component to the second component prior to heating the brazing material in the braze chamber.4. The method of claim 1 , wherein the braze gap has a width in the range of about 10 μm to about 100 μm (about 0.4 mil to about 4.0 mil) such that the brazing material flows by capillary action in the braze gap.5. The method of claim 1 , wherein the heating comprises induction heating the first component.6. The method of claim 1 , wherein the heating comprises heating the brazing material claim 1 , the first component claim 1 , and the second component in a vacuum furnace.7. The method ...

HYBRID ADDITIVE MANUFACTURING METHODS USING HYBRID ADDITIVELY MANUFACTURED FEATURES FOR HYBRID COMPONENTS

A hybrid additive manufacturing method comprises building an additive structure on a pre-sintered preform base, wherein building the additive structure comprises iteratively fusing together a plurality of layers of additive material with at least a first layer of additive material joined to the pre-sintered preform base, and wherein the pre-sintered preform base comprises an initial shape. The hybrid additive manufacturing method further comprises modifying the initial shape of the pre-sintered preform base comprising the additive structure into a modified shape comprising the additive structure, and, joining the pre-sintered preform base in its modified shape to a component. 1. A hybrid additive manufacturing method comprising:building an additive structure on a pre-sintered preform base, wherein building the additive structure comprises iteratively fusing together a plurality of layers of additive material with at least a first layer of additive material joined to the pre-sintered preform base, and wherein the pre-sintered preform base comprises an initial shape;modifying the initial shape of the pre-sintered preform base comprising the additive structure into a modified shape comprising the additive structure;joining the pre-sintered preform base in its modified shape to a component.2. The hybrid additive manufacturing method of claim 1 , wherein the initial shape comprises a planar surface.3. The hybrid additive manufacturing method of claim 1 , wherein the modified shape comprises a non-planar surface.4. The hybrid additive manufacturing method of claim 3 , wherein the non-planar surface comprises a curved surface.5. The hybrid additive manufacturing method of claim 1 , wherein joining the pre-sintered preform base in its modified shape to the component comprises joining the pre-sintered preform base to a curved surface of the component.6. The hybrid additive manufacturing method of claim 1 , wherein the component comprises a turbine component.7. The hybrid ...

WELD FILLER FOR SUPERALLOYS

A weld filler metal for a superalloy for welding is disclosed. The weld filler metal includes a preformed article that contains a first material with a melting point of approximately 2300 to 2500° F., and a second material with a melting point of approximately 1800 to 2200° F., wherein a ratio of the first material and the second material is variable. Related processes and articles are also disclosed. 1. A weld filler metal for a superalloy for welding , the weld filler metal comprising:a preformed article including:a first material with a melting point of approximately 2300 to 2500° F.; anda second material with a melting point of approximately 1800 to 2200° F., wherein a ratio of the first material and the second material is variable.2. The weld filler metal of claim 1 , wherein at least one of the first and second materials includes at least one of a cobalt based system and a nickel based system.3. The weld filler metal of claim 1 , wherein the ratio of the first material and the second material is chosen based on at least one of: a material content of the superalloy and a melting point of the superalloy being welded.4. The weld filler metal of claim 3 , wherein the first material includes a material chosen from a group comprising: a list of materials in Table 1.5. The weld filler metal of claim 3 , wherein the second material includes a material chosen from a group comprising: a list of materials in Table 2.6. The weld filler metal of claim 1 , wherein a shape of the preformed article comprises a wire shape.7. The weld filler metal of claim 1 , wherein a shape of the preformed article comprises a shape matching an area of the superalloy to be welded.8. A method of welding a superalloy claim 1 , the method comprising:applying a preformed article to an area of the superalloy, the preformed article including: a first material with a melting point of approximately 2300 to 2500° F.; and a second material with a melting point of approximately 1800 to 2200° F., wherein ...

Alumina-Forming, High Temperature Creep Resistant Ni-Based Alloys

An alumina-forming, high temperature creep resistant alloy is composed essentially of, in terms of weight percent: up to 10 Fe, 3.3 to 4.6 Al, 6 to 22 Cr, 0.68 to 0.74 Mn, 5.2 to 6.6 Mo, 0.4 to 1.2 Ti, up to 0.1 Hf, 0.005 to 0.05 La, 0.4 to 0.6 W, 0.1 to 0.35 C, up to 0.002 B, 0.001 to 0.02 N, balance Ni. 16.-. (canceled)7. An alloy consisting essentially of , in weight percent:Fe 0.01 to 10Al 3.3 to 4.6Cr 6 to 22Mn 0.68 to 0.74Mo 5.2 to 6.6Ti 0.4 to 1.2Hf up to 0.1La 0.005 to 0.05W 0.4 to 0.6C 0.1 to 0.35B up to 0.002N 0.001 to 0.02{'sup': '2', 'sub': '2', 'Ni balance, wherein the alloy has Al+Cr from 9.3 to 26.6, and wherein the specimen mass change (mg/cm) after 200 1-hr cycles at 1150° C. in wet air (10% HO) is no less than −1, and no more than +1.'}8. The alloy of claim 7 , wherein Fe is present in an amount of 1 to 6 weight percent.9. The alloy of claim 7 , wherein Cr is present in an amount of 11.64 to 22 weight percent.10. The alloy of claim 7 , wherein Fe is present in an amount from 1.93 to 10.11. The alloy of claim 7 , wherein Al+Cr is present in an amount from 15.06 to 26.6.12. The alloy of claim 7 , wherein Al+Cr is present in an amount from 19.22 to 26.6.13. The alloy of claim 7 , wherein Fe is present in an amount from 5.84 to 10.14. The alloy of claim 7 , wherein the alloy has a yield strength of at least 83 Ksi at room temperature and at least 55 Ksi at 882° C.15. The alloy of claim 7 , wherein the alloy has a creep rupture life of at least 593.6 hrs at 1093° C. and a stress of 1 Ksi.16. The alloy of claim 7 , wherein the alloy has a creep rupture life of at least 166.7 at 982° C. and a stress of 3 Ksi.17. The alloy of claim 7 , wherein MCis present from 2.23 to 4.7 wt. % at 900° C.18. The alloy of claim 7 , wherein MC is present from 0 to 3.8 wt. % at 900° C.19. The alloy of claim 7 , wherein MCis present from 2.17 to 4.57 wt. % at 1100° C.20. The alloy of claim 7 , wherein MC is present from 0.01 to 1.69 wt. % at 1100° C.21. The alloy of claim 7 , ...

METAL LEADING EDGE PROTECTIVE STRIPS FOR AIRFOIL COMPONENTS AND METHOD THEREFOR

A metallic leading edge protective strip adapted to provide impact protection for a leading edge of an airfoil of a turbomachine. The protective strip is formed of a stainless steel or a nickel-based alloy and is denser and provides increased strength and elasticity characteristics as compared to an identical protective strip formed of a titanium-based alloy. The protective strip is particularly suitable for use with composite blades and allows for thinner airfoils, thereby improving engine efficiency. 1. A metal leading edge protective strip adapted to provide impact protection for a leading edge of an airfoil of a turbomachine , the protective strip being formed of a stainless steel or a nickel-based alloy and being denser and providing increased strength and elasticity characteristics as compared to an identical protective strip formed of a titanium-based alloy.2. An airfoil of a turbomachine having a leading edge protected by the metal leading edge protective strip of .3. The airfoil of claim 2 , wherein the airfoil is formed of a polymer matrix composite.4. The metal leading edge protective strip of claim 1 , wherein the protective strip is formed of a nickel-based alloy.5. The metal leading edge protective strip of claim 4 , wherein the nickel-based alloy consists of claim 4 , by weight claim 4 , 50-55% nickel claim 4 , 17-21% chromium claim 4 , 2.8-3.33% molybdenum claim 4 , 4.75-5.5% niobium claim 4 , 0-1.0% cobalt claim 4 , 0.65-1.15 titanium claim 4 , 0.2-0.8% aluminum claim 4 , 0-0.35% manganese claim 4 , 0-0.3% copper claim 4 , 0-0.08% carbon claim 4 , 0-0.006% boron claim 4 , the balance iron and incidental impurities.6. An airfoil of a turbomachine having a leading edge protected by the metal leading edge protective strip of .7. The airfoil of claim 6 , wherein the airfoil is formed of a polymer matrix composite.8. The metal leading edge protective strip of claim 1 , wherein the protective strip is formed of a stainless steel alloy.9. The metal leading ...

SUPERALLOY PART AND METHOD OF PROCESSING

A method for repairing a part and the resulting is disclosed. The method includes positioning a plug having an inner braze element coupled thereto into a cavity defined by an internal surface of a component. The cavity has a circular cross-section at the external surface of the component. The plug completely fills the circular cross-section and the inner braze element is within the cavity. A braze paste is positioned at least partially around the plug at the external surface. The component is positioned such that the inner braze element is above the plug. The component is subjected to a thermal cycle to melt the inner braze element around the plug, completely sealing the cavity by forming a metallurgical bond with the plug and the internal surface of the component. During the thermal cycle the braze paste is melted to form a metallurgical bond with the plug and external surface. 1. A method comprising:positioning a plug having an inner braze element coupled thereto into a cavity defined by an internal surface of a component, wherein the cavity has a circular cross-section at an external surface of the component, wherein the plug fills the circular cross-section, and wherein the inner braze element is within the cavity;positioning a braze paste at least partially around the plug at the external surface;positioning the component such that the inner braze element is above the plug; andsubjecting the component to a thermal cycle to melt the inner braze element around the plug, sealing the cavity by forming a metallurgical bond with the plug and the internal surface of the component.2. The method of claim 1 , further comprised grinding the component to smooth the external surface.3. The method of claim 1 , wherein the inner braze element comprises a mixture of a powdered low-melt braze material claim 1 , a powdered high-melt material claim 1 , and a binder.4. The method of claim 1 , wherein the braze paste comprises a braze filler material and a nickel based metal filler ...

NICKEL BASED SUPERALLOY ARTICLE AND METHOD FOR FORMING AN ARTICLE

An article and a method for forming a single crystal casting are disclosed. The article includes a single crystal nickel-based superalloy having a composition including greater than about 80 ppm boron (B) and a substantially single crystal microstructure with at least one grain boundary. A creep rupture strength of the article is substantially maintained up to a mismatched grain boundary of about 40 degrees. The method for forming a single crystal casting includes positioning a mold on a cooling plate, the mold including a single crystal selector, providing a molten nickel-based superalloy composition in the mold, the molten composition including greater than about 80 ppm boron (B), cooling the molten composition with the cooling plate, and forming a unidirectional temperature gradient by withdrawing the mold from within a heat source to form the single crystal casting including a substantially single crystal microstructure having at least one grain boundary. 1. A single crystal superalloy article comprising:a nickel-based superalloy having a composition including greater than about 80 ppm boron (B);wherein the article includes a substantially single crystal microstructure having at least one grain boundary, the article having a creep rupture strength that is substantially maintained up to a mismatched grain boundary of about 40 degrees.2. The article of claim 1 , further comprising between about 80 ppm and about 130 ppm boron (B).3. The article of claim 1 , further comprising between about 80 ppm and about 100 ppm boron (B).4. The article of claim 1 , wherein the composition comprises claim 1 , by weight percent:about 5.75% to about 6.25% chromium (Cr);about 7.0% to about 8.0% cobalt (Co);about 6.2% to about 6.7% aluminum (Al);up to about 0.04% titanium (Ti);about 6.4% to about 6.8% tantalum (Ta);about 6.0% to about 6.5% tungsten (W);about 1.3% to about 1.7% molybdenum (Mo);about 0.03% to about 0.11% carbon (C);about 0.008% to about 0.013% boron (B);about 0.12% to ...

ARTICLE

An article includes a substrate and a structure including direct metal laser melted material of predetermined thickness attached to the substrate, the structure formed by providing and depositing a metal alloy powder to form an initial layer having a preselected thickness and shape including at least one aperture, melting the metal alloy powder with a focused energy source, transforming the powder layer to a sheet of metal alloy, sequentially depositing an additional layer of the metal alloy powder over the sheet of metal alloy, the additional preselected shape including an aperture corresponding to the aperture in the initial layer, and melting each additional layer of the metal alloy powder with the focused energy source, increasing the thickness of the sheet and forming at least one aperture having a predetermined profile, the article further including a passageway through the structure including the aperture and a corresponding metering hole. 1. An article comprising:a substrate; and providing a metal alloy powder;', 'depositing the metal alloy powder to form an initial layer having a preselected thickness and a preselected shape including at least one aperture;', 'melting the metal alloy powder with a focused energy source, transforming the powder layer to a sheet of metal alloy;', 'sequentially depositing at least one additional layer of the metal alloy powder over the sheet of metal alloy, each of the at least one additional layers having an additional preselected thickness and additional preselected shape, the additional preselected shape including at least one aperture corresponding to the at least on aperture in the initial layer; and', 'melting each of the at least one additional layers of the metal alloy powder with the focused energy source, increasing the thickness of the sheet and forming at least one aperture having a predetermined profile;, 'a structure including direct metal laser melted material of predetermined thickness attached to the substrate ...

High Strength Alloys for High Temperature Service in Liquid-Salt Cooled Energy Systems

An essentially cobalt-free alloy consists essentially of, in terms of weight percent: 6.3 to 7.2 Cr, 0.5 to 2 Al, 0 to 5 Fe, 0.7 to 0.8 Mn, 9 to 12.5 Mo, 0 to 6 Ta, 0.75 to 3.5 Ti, 0.01 to 0.25 Nb, 0.2 to 0.6 W, 0.02 to 0.04 C, 0 to 0.001 B, 0.0001 to 0.002 N, balance Ni. The alloy is characterized by a γ′ microstructural component in the range of 3 to 17.6 weight percent of the total composition. The alloy is further characterized by, at 850° C., a yield strength of at least 60 Ksi, a tensile strength of at least 70 Ksi, a creep rupture life at 12 Ksi of at least 700 hours, and a corrosion rate, expressed in weight loss [g/(cmsec)]10during a 1000 hour immersion in liquid FLiNaK at 850° C., in the range of 5.5 to 17. 1. An essentially cobalt-free , γ′-strengthened alloy consisting essentially of , expressed in weight percent of the total composition:Cr 6.3 to 7.2Al 0.5 to 2Fe 0 to 5Mn 0.7 to 0.8Mo 9 to 12.5Ta 0 to 6Ti 0.75 to 3.5Nb 0.01 to 0.25W 0.2 to 0.6C 0.02 to 0.04B 0 to 0.001N 0.0001 to 0.002Ni balancesaid alloy having a γ′ microstructural component in an amount of a calculated weight percent of at least 3 and no more than 17.6; and{'sup': 2', '−11, 'said alloy being characterized by, at 850° C., a yield strength of at least 60 Ksi, a tensile strength of at least 70 Ksi, and a creep rupture life at 12 Ksi of at least 700 hours, and a corrosion rate, expressed in weight loss [g/(cmsec)]10during a 1000 hour immersion in liquid FLiNaK at 850° C., in the range of 5.5 to 17.'}2. An alloy in accordance with wherein the range of Al is 0.75 to 2 weight percent.3. An alloy in accordance with wherein the range of Fe is 0 to 0.05 weight percent.4. An alloy in accordance with wherein said γ′ microstructural component in an amount of a calculated weight percent of at least 3 and no more than 11.8.5. An alloy in accordance with wherein said γ′ microstructural component in an amount of a calculated weight percent of at least 3 and no more than 9.4.6. An alloy in accordance ...

HIGH TEMPERATURE ALLOY FOR CASTING ENGINE VALVES

A high temperature alloy is disclosed. The high temperature alloy may have on a weight basis: about 9.0-10.0 weight % of Co, about 0.25 weight % maximum of Fe, about 8.0-9.0 weight % of Cr, about 4.75-5.50 weight % of Al, about 1.0-1.5 weight % of Ti, about 0-2.0 weight % of Mo, about 6.0-9.0 weight %, of W, about 0.12-0.18 weight % of C, about 0.01-0.03 weight % of Zr, about 0.005-0.015 weight % of B, about 0.5-1.5 weight % of Ta, a balance of Ni, and incidental impurities. 1. A high temperature alloy , comprising , on a weight basis:Co: 9.0-10.0 weight %,Fe: 0.25% maximum,Cr: 8.0-9.0 weight %,Al: 4.75-5.50 weight %,Ti: 1.0-1.5 weight %,Mo: 0-2.0 weight %,W: 6.0-9.0 weight %,C: 0.12-0.18 weight %,Zr: 0.01-0.03 weight %,B: 0.005-0.015 weight %,Ta: 0.5-1.5 weight %, anda balance of Ni and incidental impurities.2. The high temperature alloy of claim 1 , wherein a solidification temperature range of the high temperature alloy is between about 50° C. and about 60° C.3. The high temperature alloy of claim 1 , wherein a shrinkage during solidification ranges between about 5% and 5.5%.4. The high temperature alloy of claim 1 , wherein the amount of γ′ phase in the alloy ranges between about 50 weight % and 60 weight % at a temperature of about 800° C.5. The high temperature alloy of claim 1 , wherein Cr is about 8.5 weight %.6. The high temperature alloy of claim 5 , wherein Mo is about 1.75 weight %.7. The high temperature alloy of claim 6 , wherein W is about 7.5 weight %.8. The high temperature alloy of claim 7 , wherein Ta is about 1.25 weight %.9. The high temperature alloy of claim 7 , includingCo: about 9.5 weight %,Fe: about 0.1 weight %,Al: about 5.25 weight %,Ti: about 1.25 weight %,C: about 0.15 weight %,Zr: about 0.02 weight %, andB: about 0.01 weight %.10. The high temperature alloy of claim 1 , includingCo: about 9.5 weight %,Fe: about 0.1 weight %,Cr: about 8.5 weight %,Al: about 5.25 weight %,Ti: about 1.25 weight %,Mo: about 1.25 weight %,W: about 6.0 ...

HIGH-STRENGTH, HEAT-RESISTANT Ni-BASE ALLOY, METHOD FOR PRODUCING SAME, AND GAS TURBINE BLADE

Provided is a high-strength, heat-resistant, Ni-base alloy comprising Co: from 5 to 12%, Cr: from 5 to 12%, Mo: from 0.5 to 3.0%, W: from 3.0 to 6.0%, Al: from 5.5 to 7.2%, Ti: from 1.0 to 3.0%, Ta: from 1.5 to 6.0%, Re: from 0 to 2.0%, and C: from 0.01 to 0.20%. The high-strength, heat-resistant, Ni-base alloy is constituted of a Ni-based alloy, the balance of the Ni-based alloy comprising Ni and inevitable impurities. The density of the high-strength, heat-resistant Ni-base alloy is less than 8.5 g/cm 3 .

NICKEL-BASED SUPERALLOY, SINGLE-CRYSTAL BLADE AND TURBOMACHINE

The invention relates to a nickel-based superalloy comprising, in percentages by mass, 5.0 to 6.0% aluminum, 6.0 to 9.5% tantalum, 0 to 1.50% titanium, 8.0 to 10.0% cobalt, 6.0 to 7.0% chromium, 0.30 to 0.90% molybdenum, 5.5 to 6.5% tungsten, 0 to 2.50% rhenium, 0.05 to 0.15% hafnium, 0.70 to 4.30% platinum, 0 to 0.15% silicon, the remainder being nickel and unavoidable impurities. The invention also relates to a single-crystal blade comprising such an alloy and a turbomachine comprising such a blade. 1. A nickel-based superalloy comprising , in weight percent , 5.0 to 6.0% aluminum , 6.0 to 9.5% tantalum , 0 to 1.50% titanium , 8.0 to 10.0% cobalt , 6.0 to 7.0% chromium , 0.30 to 0.90% molybdenum , 5.5 to 6.5% tungsten , 0 to 2.50% rhenium , 0.05 to 0.15% hafnium , 0.70 to 4.30% platinum , 0 to 0.15% silicon , the remainder being nickel and unavoidable impurities.2. The superalloy as claimed in claim 1 , comprising claim 1 , in percentages by mass claim 1 , 5.0 to 6.0% aluminum claim 1 , 6.0 to 9.5% tantalum claim 1 , 0 to 1.50% titanium claim 1 , 8.0 to 10.0% cobalt claim 1 , 6.0 to 7.0% chromium claim 1 , 0.30 to 0.90% molybdenum claim 1 , 5.5 to 6.5% tungsten claim 1 , 0 to 2.50% rhenium claim 1 , 0.05 to 0.15% hafnium claim 1 , 1.70 to 4.30% platinum claim 1 , 0 to 0.15% silicon claim 1 , the remainder being nickel and unavoidable impurities.3. The superalloy as claimed in claim 1 , comprising claim 1 , in percentages by mass claim 1 , 5.0 to 6.0% aluminum claim 1 , 6.0 to 7.0% tantalum claim 1 , 0 to 1.50% titanium claim 1 , 8.0 to 10.0% cobalt claim 1 , 6.0 to 7.0% chromium claim 1 , 0.30 to 0.90% molybdenum claim 1 , 5.5 to 6.5% tungsten claim 1 , 0 to 2.50% rhenium claim 1 , 0.05 to 0.15% hafnium claim 1 , 1.70 to 4.30% platinum claim 1 , 0 to 0.15% silicon claim 1 , the remainder being nickel and unavoidable impurities.4. The superalloy as claimed in claim 1 , comprising claim 1 , in percentages by mass claim 1 , 5.0 to 6.0% aluminum claim 1 , 8.5 to 9.5% ...

CLADDED ARTICLES AND METHODS OF MAKING THE SAME

In one aspect, methods of making cladded articles are described herein. A method of making a cladded article, in some embodiments, comprises disposing over a surface of a metallic substrate a sheet comprising organic binder and powder metal or powder alloy having a solidus temperature at least 100° C. less than the metallic substrate and heating the powder metal or powder alloy to provide a sintered metal or sintered alloy cladding metallurgically bonded to the metallic substrate. 1. A method of making a cladded article comprising:disposing over a surface of a metallic substrate a sheet comprising organic binder and powder nickel-based alloy having a solidus temperature at least about 100° C. less than solidus temperature of the metallic substrate and;heating the powder nickel-based alloy to provide a substantially fully dense sintered nickel-based alloy cladding metallurgically bonded to the metallic substrate, the sintered nickel-based alloy cladding comprising 0-30 wt. % chromium, 0-28 wt. % molybdenum, 0-15 wt. % tungsten, 0-6 wt. % niobium, 0-6 wt. % tantalum, 0-30 wt. % iron, 0-15 wt. % cobalt, 0-2 wt. % carbon, 0-2 wt. % manganese, 0-10 wt. % silicon, 0-10 wt. % phosphorus, 0-0.1 wt. % sulfur, 0-1 wt. % aluminum, 0-6 wt. % titanium, 0-50 wt. % copper, 0-5 wt. % boron and the balance nickel.2. The method of claim 1 , wherein the solidus temperature of the powder nickel-based alloy is at least 150° C. less than the solidus temperature of the metallic substrate.3. The method of claim 1 , wherein the solidus temperature of the powder nickel-based alloy is at least 200° C. less than the solidus temperature of the metallic substrate.4. The method of claim 1 , wherein the sintered nickel-based alloy comprises 8-25 wt. % chromium claim 1 , 5-20% wt. % molybdenum claim 1 , 0-6 wt. % tungsten claim 1 , 0-5 wt. % total of niobium and tantalum claim 1 , 0-4 wt. % cobalt claim 1 , 0-30 wt. % iron claim 1 , 0-1 wt. % manganese claim 1 , 0.1-5 wt. % boron and the balance ...

Intermediate Strength Alloys for High Temperature Service in Liquid-Salt Cooled Energy Systems

An alloy consists essentially of, in terms of weight percent: 6 to 8.5 Cr, 5.5 to 13.5 Mo, 0.4 to 7.5 W, 1 to 2 Ti, 0.7 to 0.85 Mn, 0.05 to 0.3 Al, up to to 0.1 Co, 0.08 to 0.5 C, 1 to 5 Ta, 1 to 4 Nb, 1 to 3 Hf, balance Ni. The alloy is characterized by, at 850° C., a yield strength of at least 36 Ksi, a tensile strength of at least 40 Ksi, a creep rupture life at 12 Ksi of at least 72.1 hours, and a corrosion rate, expressed in weight loss [g/(cm2sec)]×10during a 1000 hour immersion in liquid FLiNaK at 850° C., in the range of 8 to 25. 1. An alloy consisting essentially of , in terms of weight percent:Cr 6 to 8.5Mo 5.5 to 13.5W 0.4 to 7.5Ti 1 to 2Mn 0.7 to 0.85Al 0.05 to 0.3Co <0.005 to 0.1C 0.08 to 0.5Ta 1 to 5Nb 1 to 4Hf 1 to 3Ni balance{'sup': 2', '−11, 'said alloy being characterized by, at 850° C., a yield strength of at least 36 Ksi, a tensile strength of at least 40 Ksi, a creep rupture life at 12 Ksi of at least 72.1 hours, and a corrosion rate, expressed in weight loss [g/(cmsec)]10during a 1000 hour immersion in liquid FLiNaK at 850° C., in the range of 8 to 25.'}2. An alloy in accordance with wherein said alloy is essentially Fe free.3. An alloy in accordance with wherein the range of Cr is 6.7 to 8.3 weight percent.4. An alloy in accordance with wherein the range of Mo is 5.81 to 12.93 weight percent.5. An alloy in accordance with wherein the range of W is 0.52 to 6.99 weight percent.6. An alloy in accordance with wherein the range of Ti is 1.15 to 1.22 weight percent.7. An alloy in accordance with wherein the range of Mn is 0.75 to 0.79 weight percent.8. An alloy in accordance with wherein the range of Al is 0.08 to 0.11 weight percent.9. An alloy in accordance with wherein the range of Co is 0.01 to 0.08 weight percent.10. An alloy in accordance with wherein said alloy is essentially Co free.11. An alloy in accordance with wherein the range of Ta is 1.18 to 4.82 weight percent.12. An alloy in accordance with wherein the range of Nb is 1.06 to 3.76 ...

Ni-BASED SINGLE CRYSTAL SUPERALLOY

Provided is a Ni-based single crystal superalloy containing 1. A Ni-based single crystal superalloy comprising6% by mass or more and 12% by mass or less of Cr,0.4% by mass or more and 3.0% by mass or less of Mo,6% by mass or more and 10% by mass or less of W,4.0% by mass or more and 6.5% by mass or less of Al,0% by mass or more and 1% by mass or less of Nb,8% by mass or more and 12% by mass or less of Ta,0% by mass or more and 0.15% by mass or less of Hf,0.01% by mass or more and 0.2% by mass or less of Si, and0% by mass or more and 0.04% by mass or less of Zr, andoptionally containing at least one element selected from B, C, Y, La, Ce, and V,with a balance being Ni and inevitable impurities.2. A Ni-based single crystal superalloy comprising7% by mass or more and 12% by mass or less of Cr,0.4% by mass or more and 2.5% by mass or less of Mo,7% by mass or more and 10% by mass or less of W,4.0% by mass or more and 6.5% by mass or less of Al,0% by mass or more and 1% by mass or less of Nb,9% by mass or more and 11% by mass or less of Ta,0% by mass or more and 0.15% by mass or less of Hf,0.01% by mass or more and 0.2% by mass or less of Si, and0% by mass or more and 0.04% by mass or less of Zr, andoptionally containing at least one element selected from B, C, Y, La, Ce, and V,with a balance being Ni and inevitable impurities.3. A Ni-based single crystal superalloy comprising8% by mass or more and 10% by mass or less of Cr,0.4% by mass or more and 2.0% by mass or less of Mo,7% by mass or more and 9% by mass or less of W,4.0% by mass or more and 6.5% by mass or less ofAl,0% by mass or more and 1% by mass or less of Nb,10% by mass or more and 11% by mass or less of Ta,0% by mass or more and 0.15% by mass or less of Hf,0.01% by mass or more and 0.2% by mass or less of Si, and0% by mass or more and 0.04% by mass or less of Zr, andoptionally containing at least one element selected from B, C, Y, La, Ce, and V,with a balance being Ni and inevitable impurities.4. The Ni-based ...

PROCESS AND PRINTED ARTICLE

A process includes forming a printed article having an external surface and at least one microfeature with an internal surface by additive manufacture, coating the external surface and the internal surface of the printed article with a metallic microlayer to form a coated article, and densifying the coated article to form a component. After formation, the printed article has a porosity such that the printed article is not at full density. A densified component includes a printed article having an external surface and at least one microfeature with an internal surface and a metallic microlayer coating the external surface and the internal surface of the printed article. The printed article is formed by additive manufacture. 1. A process comprising:forming a printed article having an external surface and at least one microfeature with an internal surface by additive manufacture, wherein the printed article has a porosity such that the printed article is not at full density;coating the external surface and the internal surface of the printed article with a metallic microlayer to form a coated article; anddensifying the coated article to form a component.2. The process of claim 1 , wherein the coating comprises depositing the metallic microlayer on the external surface and the internal surface of the printed article by a coating method selected from the group consisting of plating claim 1 , physical vapor deposition claim 1 , chemical vapor deposition claim 1 , thermal spraying claim 1 , cold spraying claim 1 , plasma spraying claim 1 , cathodic arc claim 1 , spark plasma sintering claim 1 , and plasma spray physical vapor deposition.3. The process of claim 1 , wherein the densifying comprises hot isostatic pressing.4. The process of claim 1 , wherein the component is greater than 90% of full density.5. The process of claim 1 , wherein the printed article is formed of a superalloy including a composition claim 1 , by weight claim 1 , selected from the group consisting ...

CAST NICKEL-BASE SUPERALLOY INCLUDING IRON

A cast nickel-base superalloy that includes iron added substitutionally for nickel. The cast nickel-base superalloy comprises, in weight percent about 1-6% iron, about 7.5-19.1% cobalt, about 7-22.5% chromium, about 1.2-6.2% aluminum, optionally up to about 5% titanium, optionally up to about 6.5% tantalum, optionally up to about 1% Nb, about 2-6% W, optionally up to about 3% Re, optionally up to about 4% Mo, about 0.05-0.18% C, optionally up to about 0.15% Hf, about 0.004-0.015 B, optionally up to about 0.1% Zr, and the balance Ni and incidental impurities. The superalloy is characterized by a γ′ solvus temperature that is within 5% of the γ′ solvus temperature of the superalloy that does not include 1-6% Fe and a mole fraction of γ′ that is within 15% of the mole fraction of the superalloy that does not include 1-6% Fe. 1. A cast nickel-base superalloy comprising , in weight percent , about 4-5% Fe , wherein the superalloy is: 8.5-9.5% Co;', '14-16% Cr;', '3-3.5% Al;', '3.4-5% Ti;', 'up to 2.8% Ta;', 'up to about 0.85% Nb;', '2.6-4% W;', '1.5-4% Mo;', '0.1-0.18% C;', '0.01-0.015 B;', 'up to 0.03% Zr; and', 'the balance Ni and incidental impurities; or, 'a medium γ′ alloy having a composition further including, in weight percent 7.5-8.0% Co;', '7-10.5% Cr;', '3.5-6.2% Al;', 'up to about 4% Ti;', '4.5-6.8% Ta;', 'up to 0.6% Nb;', '4.6-6.4% W;', 'up to 3.2% Re;', '1.3-1.7% Mo;', '0.04-0.06% C;', '0.13-0.17% Hf;', '0.003-0.005% B; and', 'the balance Ni and incidental impurities., 'a high γ′ alloy having a composition further including, in weight percent2. The superalloy of claim 1 , wherein the superalloy is characterized by a γ′ mole fraction that is no more than 15% less than a comparative γ′ mole fraction of a comparable superalloy that does not include 1-6% Fe.3. The superalloy of claim 1 , wherein the superalloy is characterized by a γ′ solvus temperature that is no more than 5% less than a comparative γ′ solvus temperature of the comparable superalloy that does ...

Nickel-Based Superalloys and Articles

Rhenium-free nickel based alloys are provided. More particularly, the alloys comprise preferred levels and ratios of elements so as to achieve good high temperature strength of both gamma matrix phase and gamma prime precipitates, as well as good environmental resistance, without using rhenium. When cast and directionally solidified into single crystal form, the alloys exhibit creep and oxidation resistance substantially equivalent to or better than rhenium-bearing single-crystal alloys. Further, the alloys can be processed by directional solidification into articles in single crystal form or columnar structure comprising fine dendrite arm spacing, e.g., less than 400 μm, if need be, so that further improvements in mechanical properties in the articles can be seen. 1. A rhenium-free , nickel-based alloy comprising from about 4.0 wt % to about 10 wt % cobalt (Co) , from about 4.0 wt % to about 7.5 wt % chromium (Cr) , from about 0.5 wt % to about 2.5 wt % molybdenum (Mo) , from about 8.2 wt % to about 10 wt % tungsten (W) , from about 4.0 wt % to about 6.5 wt % aluminum (Al) , titanium (Ti) present in an amount up to 1.0 wt % , from about 6.5 wt % to about 10.0 wt % of tantalum (Ta) , from about 0 wt % to about 1.5 wt % hafnium (Hf) , carbon (C) present in an amount up to about 0.1 wt % , boron (B) present in an amount from about 0.001 wt % to about 0.01 wt % , up to about 0.1 wt % yttrium (Y) , with the remainder being nickel (Ni) and incidental impurities , and wherein:Ta/Al is from about 1.24 to about 2.0;Al+0.15Ta is from about 6.0 wt % to about 8.5 wt %;Al+0.15Hf is from about 5.0 wt % to about 7.0 wt %; andMo+0.52W is from about 4.2 wt % to about 6.5 wt %.2. The nickel-based alloy of claim 1 , comprising from about 4.5 wt % to about 6.0 wt % cobalt (Co) claim 1 , from about 6.0 wt % to about 7.5 wt % chromium (Cr) claim 1 , from about 0.7 wt % to about 2.1 wt % molybdenum (Mo) claim 1 , from about 8.2 wt % to about 9.5 wt % tungsten (W) claim 1 , from about 4.3 ...

MOLDING MACHINE CYLINDER AND ITS PRODUCTION METHOD

A molding machine cylinder comprising a lining layer having a structure comprising 20-50% by area of tungsten carbide particles and 1-10% by area of tungsten-based metal carboboride particles in a nickel-based alloy matrix, and containing 1-7.5% by mass of Fe, can be produced by a centrifugal casting method comprising a first step of heating at higher than 1140° C. and lower than 1200° C., and a second step of heating at 1080-1140° C. after melting the raw material powder. 1. A method for producing a molding machine cylinder comprising a lining layer having a structure comprising 20-50% by area of tungsten carbide particles and 1-10% by area of tungsten-based metal carboboride particles in a nickel-based alloy matrix , and containing 1-7.5% by mass of Fe , comprising the steps ofcharging a raw material for the lining layer into a steel cylinder, said raw material comprising 40-70 parts by mass of nickel-based alloy powder containing 1-5% by mass of B, and 60-30 parts by mass of tungsten carbide powder;melting said raw material for the lining layer while rotating said cylinder at 5-30 rpm;increasing the number of rotation of said cylinder for centrifugal casting, to form a centrifugally cast layer comprising an outside lining layer and an inside particle-lack layer on an inner surface of said cylinder; andremoving said particle-lack layer by machining;said raw material for the lining layer being melted by a first step of heating at higher than 1140° C. and lower than 1200° C., and a second step of heating at 1080-1140° C. after said first heating step.2. The method for producing a molding machine cylinder according to claim 1 , wherein said alloy powder comprises 0.01-1% by mass of C claim 1 , 1-5% by mass of B claim 1 , 2-20% by mass of Cr claim 1 , 0.2-5% by mass of Si claim 1 , 0.2-5% by mass of Mn claim 1 , 2-30% by mass of Co claim 1 , 0-5% by mass of Cu claim 1 , and 0-1% by mass of Fe claim 1 , the balance being nickel and inevitable impurities.3. The method ...

SUPERALLOY COMPOSITE PREFORMS AND APPLICATIONS THEREOF

In one aspect, composite preforms for the repair of superalloy parts and/or apparatus are described herein. For example, a composite preform comprises a nickel-based superalloy powder component, a nickel-based braze alloy powder component and a melting point depressant component disposed in a fibrous polymeric matrix. The fibrous polymeric matrix can form a flexible cloth in which the nickel-based superalloy powder component, nickel-based braze alloy powder component and melting point depressant component are dispersed. 1. A method of repairing a nickel-based superalloy part comprising:providing an assembly by application of at least one composite preform to a damaged area of the nickel-based superalloy part, the composite preform including a nickel-based superalloy powder component, a nickel-based braze alloy powder component and a melting point depressant component disposed in a fibrous polymeric matrix, the melting point depressant component comprising boron in an amount of 0.3 to 1.5 weight percent of the composite preform; andheating the assembly to form a filler alloy metallurgically bonded to the damaged area, the filler alloy formed from the nickel-based superalloy powder component and the nickel-based braze alloy powder component, wherein the filler alloy is a load bearing component of the nickel-based superalloy part and exhibits tensile strength greater than 50 percent of tensile strength of the nickel-based superalloy of the part.2. The method of claim 1 , wherein the nickel-based braze alloy powder component has a melting point lower than the nickel-based superalloy powder component.3. The method of claim 2 , wherein the assembly is heated to a temperature greater than the melting point of the nickel-based braze alloy powder component and less than the melting point of the nickel-based superalloy powder component.4. The method of claim 1 , wherein the filler alloy is substantially fully dense.5. The method of claim 1 , wherein the filler alloy forms a ...