ПАЯНОЕ СОЕДИНЕНИЕ МЕЖДУ МЕТАЛЛИЧЕСКОЙ ДЕТАЛЬЮ НА ОСНОВЕ ТИТАНА И ДЕТАЛЬЮ ИЗ КЕРАМИЧЕСКОГО МАТЕРИАЛА НА ОСНОВЕ КАРБИДА КРЕМНИЯ (SiC) И/ИЛИ УГЛЕРОДА

Изобретение относится к области соединения пайкой металлической детали на основе титана и детали из керамического материала на основе карбида кремния (SiC) и/или углерода. Данное соединение может быть использовано в авиации, в частности в турбомашине, для соединения деталей, входящих в состав сопла, камеры сгорания и форсажной камеры. Соединение содержит многослойную структуру, включающую в себя следующие элементы, соединенные друг с другом путем пайки: металлическая деталь (10) на основе титана, первая прокладка (11), способная деформироваться для приспосабливания к разнице в расширении металлической детали (10) и детали из керамического материала (20) на основе карбида кремния и/или углерода, вторая жесткая прокладка (12) из нитрида алюминия (AlN) или вольфрама (W) с коэффициентом расширения, близким к коэффициенту расширения упомянутой детали из керамического материала (20), и деталь из керамического материала (20). Технический результат изобретения - создание спая, позволяющего компенсировать ...

СБОРКА МЕТАЛЛИЧЕСКОЙ ДЕТАЛИ И ДЕТАЛИ, ВЫПОЛНЕННОЙ ИЗ КЕРАМИЧЕСКОГО МАТЕРИАЛА НА ОСНОВЕ SiC И/ИЛИ НА ОСНОВЕ С

Изобретение относится к сборке металлической детали и детали, выполненной из керамического материала на основе карбида кремния и/или углерода, и может быть использовано в области авиации: в соплах, камерах сгорания и оборудовании дожигания турбомашин. Сборка металлической детали (1) из сплава на основе никеля или кобальта и детали (7) из керамического материала на основе карбида кремния (SiC) и/или углерода (С) имеет многослойную структуру, включающую следующие элементы, соединенные вместе попарно в следующем порядке путем спаивания: металлическая деталь (1), первая промежуточная деталь (3), вторая промежуточная деталь (5) и деталь из керамического материала. Вторая промежуточная деталь (5) выполнена из нитрида алюминия и/или муллита, имеющего коэффициент расширения меньший, чем коэффициент расширения материала, составляющего металлическую деталь (1). Первая промежуточная деталь (3) выполнена из ковкого металла и способна деформироваться для компенсации разницы расширений между указанной ...

СПОСОБ ПОВЫШЕНИЯ ДОЛГОВЕЧНОСТИ И УЛУЧШЕНИЯ ХАРАКТЕРИСТИК ФАКЕЛЬНОГО НАКОНЕЧНИКА, ФАКЕЛЬНЫЙ НАКОНЕЧНИК

Изобретение относится к области энергетики, в частности к факельным наконечникам. Способ повышения долговечности и улучшения характеристик факельного наконечника, при котором наносят покрытие, состоящее из материала с низким коэффициентом излучения на одну или более из поверхностей компонента факельного наконечника для уменьшения прямого излучения пламени и теплопроводности при работе факельного наконечника. Покрытие наносят на поверхности факельной бочки, элемента горелки и/или стабилизирующего язычка факельного наконечника. Поверхность (поверхности), на которую наносят покрытие, подвержена прямому воздействию пламени при работе факельного наконечника. Покрытие наносят на внутренние и/или внешние компоненты факельного наконечника, не являющиеся горелкой. Материал покрытия с низким коэффициентом излучения имеет коэффициент излучения менее чем приблизительно 0,80. Материал покрытия с низким коэффициентом излучения имеет толщину между от приблизительно 1 мил до приблизительно 25 мил. Плотность ...

СПОСОБ ИЗГОТОВЛЕНИЯ ФУТЕРОВКИ В ПРОМЫШЛЕННОЙ ПЕЧИ БОЛЬШОГО ОБЪЕМА, А ТАКЖЕ ПРОМЫШЛЕННАЯ ПЕЧЬ С ФУТЕРОВКОЙ И ОГНЕУПОРНЫЙ КИРПИЧ ДЛЯ ТАКОЙ ФУТЕРОВКИ.

FIELD: manufacturing technology. SUBSTANCE: invention relates to unburned, not containing carbon compacted refractory products as refractory lining facing flame of industrial furnaces of large volume for producing cement, lime, magnesium oxide and doloma. For production of refractory lining mixture of granulate refractory materials is produced, which form ceramic binder at temperatures higher than 900 °C, at least one of first temporary binder, which provides binding particles granulate in range of temperatures from room temperature to 500 °C, and at least one second temporary binder, which provides binding particles granulate in temperature range from 300 up to 1,000 o C. Compacted from mixture bricks have compression strength in cold state of more than 20 MPa and represent magnesium chromite bricks, magnesium-spinel and spinel bricks, bricks from zirconium dioxide stabilised with magnesium oxide and zirconium, stabilised with magnesium oxide, bricks from magnesia herzynite and magnesia galaxite, dolomite, dolomite-magnesite and lime bricks, forsterite and olivine bricks, bricks from magnesia forsterite, bricks from magnesia pleonaste, magnesite bricks. As first temporary binder lignosulfonate, synthetic resin, pitch, dextrin, organic acids are used in amount of 0.5-8 wt%, and as second binder - metallic Al, Mg, Si, Fe, fine-grained oxides, calcium aluminate, clay, etc. in amount of 0.5-15 wt%. EFFECT: production of refractory products with lower thermal conductivity in ensuring maintenance of given dimensions, as well as with high strength at industrial furnace operation regardless of temperature. 21 cl, 1 tbl, 1 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК F27B 7/28 C04B 35/63 C04B 35/03 C04B 35/42 C04B 35/443 (13) 2 587 194 C2 (2006.01) (2006.01) (2006.01) (2006.01) (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2014116646/03, 26.11.2013 (24) Дата начала отсчета срока действия патента: 26.11. ...

ТЕПЛОЗАЩИТНЫЙ ЭКРАН, В ЧАСТНОСТИ ДЛЯ КОНСТРУКЦИОННЫХ ЭЛЕМЕНТОВ ГАЗОТУРБИННЫХ УСТАНОВОК

Изобретение относится к теплозащитному экрану для защиты несущей конструкции (1) от горячей среды с состоящей из жаростойкого материала футеровкой (2а), которая составлена из покрывающих поверхность с оставлением зазоров (2b), расположенных рядом друг с другом и закрепленных с возможностью перемещения под действием тепла на несущей конструкции (1) с помощью болта (4), устойчивых к высоким температурам, в основном пластинообразных элементов (2) теплозащитного экрана. Элементы (2) теплозащитного экрана состоят из стойкого к эрозии и коррозии материала. Между каждым элементом (2) и несущей конструкцией (1) расположен изоляционный кирпич (3) из огнестойкой керамики. Изобретение повышает эффективность теплозащиты при повышенных температурах. 41 з.п.ф-лы, 5 ил.

ОГНЕУПОРНАЯ ПЛИТКА, В ЧАСТНОСТИ, ДЛЯ ГАЗОГЕНЕРАТОРА

Изобретение относится к области огнеупорных материалов. Огнеупорная плитка для защиты внутренней стенки реактора газогенератора имеет линию выравнивания из двух мест крепления. Причем любые два соседних места крепления на указанной линии выравнивания отстоят друг от друга на постоянном расстоянии А. Первое место крепления и последнее место крепления на указанной линии выравнивания отстоят друг от друга в направлении указанной линии на расстояния α1 и α2 от первого края и второго края указанной плитки, ближе всего проходящих к первому месту крепления и последнему месту крепления. При этом величина A-(α1+α2) находится в пределах от 2 до 10 мм. Огнеупорная футеровка для защиты внутренней стенки реактора газогенератора содержит набор из огнеупорных плиток, прикрепленных к крепежным элементам, закрепленным на стенке. При этом указанная футеровка содержит, по меньшей мере, одну плитку. Технический результат заключается в усилении защиты, обеспечиваемой огнеупорной футеровкой. 2 н. 18 з.п. ф-лы ...

СПОСОБ ИЗГОТОВЛЕНИЯ КОМПОЗИТНОЙ СТЕНКИ

Способ изготовления композитной стенки, выполненной в виде конструкции типа «сандвич», содержащей внутренний слой из пористого металла с открытыми порами, скрепленный с внутренним облицовочным слоем и внешним облицовочным слоем, заключается в изготовлении основы внутреннего слоя заданной формы из газопроницаемого пористого материала с открытыми порами. Затем осуществляют импрегнирование указанной основы парами металла и нанесение пористого слоя металла на открытые внутреннюю и внешнюю поверхности основы с формированием посредством процесса вакуумной металлизации внутреннего слоя из пористого металла с открытыми порами. Далее формируют внутренний облицовочный слой и внешний облицовочный слой поверх внутреннего слоя из пористого металла посредством распыления материала оболочки, выбранного из группы, содержащей металлы и керамику. Изобретение позволяет уменьшить стоимость изготовления композитной стенки и улучшить рабочие характеристики камеры сгорания газотурбинного двигателя. 9 з.п. ф-лы ...

МНОГОСЛОЙНОЕ БАРЬЕРНОЕ ПОКРЫТИЕ ДЛЯ ЗАЩИТЫ ОТ ВОЗДЕЙСТВИЯ ОКРУЖАЮЩЕЙ СРЕДЫ И ОТНОСЯЩИЕСЯ К НЕМУ ИЗДЕЛИЯ И СПОСОБЫ

... 1. Изделие (100), содержащее подложку (105) и множество групп покрытий, расположенных поверх указанной подложки (105), где каждая группа (115, 120, 125) покрытий содержит слой (116) геттера кислорода и барьерный слой (117). 2. Изделие (100) по п.1, в котором указанный слой (116) геттера кислорода содержит кремний. 3. Изделие (100) по п.2, в котором указанный слой (116) геттера кислорода содержит по меньшей мере один материал, выбранный из группы, состоящей из элементарного кремния и силицида. 4. Изделие (100) по п.1, в котором указанный барьерный слой (117) содержит керамику. 5. Изделие (100) по п.5, в котором указанная керамика содержит оксид. 6. Изделие (100) по п.6, в котором указанный оксид содержит по меньшей мере одно соединение, выбранное из группы, состоящей из алюмосиликата, силиката и алюмината. 7. Изделие (100) по п.1, в котором указанное множество (110) групп (115, 120, 125) покрытий образует последовательность указанных барьерных слоев (117) барьеров, имеющих по меньшей мере ...

ПОРИСТЫЕ СТРУКТУРЫ С ПОВТОРЯЮЩИМСЯ ПОРЯДКОМ РАСПОЛОЖЕНИЯ ПРОДОЛГОВАТЫХ ОТВЕРСТИЙ

КАМЕРА СГОРАНИЯ ДЛЯ ТУРБОМАШИНЫ

... 1. Камера сгорания для турбомашины, такой как турбореактивный или турбовинтовой авиационный двигатель, содержащая внутреннюю и наружную кольцевые стенки в виде тел вращения, связанные кольцевой стенкой днища камеры, отличающаяся тем, что ее внутренняя стенка выполнена из материала одной толщины, толщина которого и/или свойства изменяются вдоль продольной оси и в окружном направлении упомянутой стенки, а ее кольцевая наружная стенка имеет, по существу, постоянную величину.2. Камера сгорания по п.1, отличающаяся тем, что ее внутренняя стенка, выполненная из материала одной толщины, содержит, по меньшей мере, одну зону, называемую горячей, с большим температурным градиентом и большей толщины и, по меньшей мере, одну холодную зону с меньшим температурным градиентом и меньшей толщины.3. Камера сгорания по п.1, отличающаяся тем, что ее внутренняя стенка выполнена одной толщины из материала, имеющего, по меньшей мере, две соседних зоны, образованных из различных материалов.4. Камера сгорания по ...

МАТЕРИАЛ ДЛЯ ГАЗИФИКАТОРА НА ОСНОВЕ ОКСИДОВ АЛЮМИНИЯ И МАГНИЯ

1. Плавлено-литое огнеупорное изделие, имеющее следующий химический состав в массовых процентах в пересчете на оксиды:2. Огнеупорное изделие по п.1, в котором содержание CuO составляет более или равно 0,10 мас.% и менее или равно 0,8 мас.%.3. Огнеупорное изделие по п.2, в котором содержание CuO составляет более или равно 0,15 мас.% и менее или равно 0,7 мас.%.4. Огнеупорное изделие по п.3, в котором содержание CuO составляет более или равно 0,20 мас.% и менее или равно 0,6 мас.%.5. Огнеупорное изделие по п.1, в котором содержание BOсоставляет более или равно 0,05 мас.%.6. Огнеупорное изделие по п.5, в котором содержание BOсоставляет более или равно 0,1 мас.%.7. Огнеупорное изделие по п.1, в котором содержание BOсоставляет менее или равно 0,6 мас.%.8. Огнеупорное изделие по п.7, в котором содержание BOсоставляет менее или равно 0,3 мас.%.9. Огнеупорное изделие по п.1, в котором содержание оксида алюминия AlOсоставляет менее или равно 70 мас.% и более или равно 55 мас.%.10. Огнеупорное изделие по п.9, в котором содержание оксида алюминия AlOсоставляет менее или равно 68 мас.% и более или равно 60 мас.%.11. Огнеупорное изделие по п.1, в котором содержание MgO составляет менее или равно 45 мас.% и более или равно 28,2 мас.%.12. Огнеупорное изделие по п.11, в котором содержание MgO составляет менее или равно 40 мас.% и более или равно 30 мас.%.13. Огнеупорное изделие по п.1, в котором:- содержание СаО составляет менее или равно 0,6 мас.%; и/или- содержание NaO+KO составляет менее или равно 0,25 мас.%; и/или- содержание диоксида кремния SiOсоставляет менее или равно 0,15 мас.%; и/или- содержание оксида железа и/или оксида титана, FeO+TiO, составляет менее 0,4 мас.%; и/или- содержание оксида хрома составляет менее 0,1 мас.%.14. Газификатор РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК C04B 35/107 (13) 2011 148 476 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2011148476/03, 01.06.2010 (71) Заявитель(и): СЕН-ГОБЕН ...

СПОСОБ НАНЕСЕНИЯ ПОКРЫТИЯ И АНТИКОРРОЗИОННОЕ ПОКРЫТИЕ ДЛЯ КОМПОНЕНТОВ ТУРБИН

1. Способ покрытия поверхности (23) потенциально топливопроводящего компонента (3, 20) детали турбины, в котором поверхность (23) методом химического осаждения из газовой фазы сначала покрывают слоем нитрида титана (21), а затем слоем оксида α-алюминия (22). ! 2. Способ по п.1, в котором покрывается поверхность (23), которая содержит сталь марки 16Мо3. ! 3. Способ по п.1, в котором покрываемую поверхность (23) сначала нагревают, нагретую поверхность (23) покрывают нитридом титана и сразу после этого оксидом α-алюминия и затем покрытую поверхность снова охлаждают. ! 4. Способ по п.1, в котором покрытие нитридом титана и оксидом α-алюминия проводится в одной и той же печи (1). ! 5. Способ по п.1, в котором поверхность (23) покрывают нитридом титана путем газофазного аммонолиза или плазменным нанесением в атмосфере водорода. ! 6. Способ по п.1, в котором поверхность (23) в рамках химического осаждения из газовой фазы нагревают со скоростью повышения температуры от 700°С/ч до 900°С/ч. ! 7. Способ по п.1, в котором поверхность (23) в рамках химического осаждения из газовой фазы нагревают и/или охлаждают при давлении от 50 мбар до 150 мбар. ! 8. Способ по одному из пп.1-7, в котором поверхность (23) во время нагревания и/или охлаждения в рамках химического осаждения из газовой фазы продувают газом, содержащим аргон и водород. ! 9. Способ по п.1, в котором поверхность (23) в рамках химического осаждения из газовой фазы охлаждают со скоростью снижения температуры от 300°С/ч до 500°С/ч. ! 10. Способ по п.1, в котором поверхность (23) в рамках химического осаждения из газовой фазы покрывают при температуре от 900°С до 1100°С. ! 11. Способ по п.1, в котором поверхность (23) в рамках химического оса� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2011 105 001 (13) A (51) МПК C23C 16/40 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (71) Заявитель(и): СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) (21)(22) Заявка: 2011105001/02, 23.06.2009 Приоритет(ы): (30) ...

Brandschutzvorrichtung für eine Feuerstätte.

Brandschutzvorrichtung für eine Feuerstätte (F) für deren Anordnung mit ihrer genormt gedämmten Wandung (W) neben einer wärmegedämmten Anbauwand (A) mit oder aus brennbaren Baustoffen (B) mit einem U-Wert ≤ 0,40 W mK an deren Grenzwandung keine höheren Temperaturen als 85 °C bei Nennleistungsbetrieb auftritt, dadurch gekennzeichnet, dass die genormt gedämmte Wandung (W) mit einer Brandschutz-Leichtbauplatte (L) aus nichtbrennbarem Dämmmaterial mit einer Wärmeleitfähigkeit ≤ 0,080 W/m.K und einer Dicke (D) von ≥ 40 mm belegt ist.

HALBLEITERSCHALTUNG MIT SPEICHER UND PULSTREIBERSCHALTUNG.

Fahrzeugheizgerät

Ein Fahrzeugheizgerät umfasst eine Brennkammerbaugruppe (12) mit einem Brennkammergehäuse (14), das mit einem - bezogen auf eine Brennkammerlängsachse (L) - nach radial außen greifenden Befestigungsbereich (36) an einem Wärmetauschergehäuse (26) festgelegt ist, wobei eine Außenwand (40) einen das Brennkammergehäuse (14) bereichsweise umgebenden Druckraum (38) für in das Brennkammergehäuse (14) einzuleitende Luft nach radial außen begrenzt, wobei die Außenwand (40) an das Wärmetauschergehäuse (24) angrenzt und im Angrenzungsbereich der Außenwand (40) an das Wärmetauschergehäuse (24) wenigstens in einem Umfangsbereich Trennmaterial (54; 80) mit geringerer Wärmeleitfähigkeit als das Wärmetauschergehäuse (24) und die Außenwand (40) angeordnet ist.

A method of making multiply-perforated part out of ceramic matrix composite material

Incinerator

Burner for a fuel cell system with two reaction chambers

Die Erfindung betrifft einen Brenner (1) für ein Brennstoffzellensystem (100), insbesondere ein SOFC-System, wobei der Brenner (1) als Startbrenner und/oder Nachbrenner ausgebildet und angeordnet ist, umfassend einen ersten Betriebsfluidleitabschnitt (2) und einen zweiten Betriebsfluidleitabschnitt (3), wobei der Brenner (1) zwei nacheinander angeordnete und jeweils einen Kammereingang (4a, 4b) und einen Kammerausgang (5a, 5b) aufweisende Reaktionskammern (6, 7) umfasst, wobei in Strömungsrichtung ein Kammereingang (4b) einer zweiten Reaktionskammer (7) auf einen Kammerausgang (5a) einer ersten Kammer Reaktionskammer (6) folgt, wobei die Reaktionskammern (6, 7) jeweils ein katalytisches Material (18) aufweisen, wobei die erste Reaktionskammer (6) eine elektrische Heizeinrichtung (11) aufweist, wobei die Heizeinrichtung (11) spiralförmig ausgebildet ist, um ein erstes Betriebsfluid zu erwärmen, zu verdampfen und/oder zu reformieren. Weiter betrifft die Erfindung eine Verwendung eines solchen ...

DEVICE FOR THE PRODUCTION OF HYDROGEN BROMIDE

PROCEDURE FOR THE THERMAL TREATMENT OF PURIFY-HASTY SOLIDS AND DEVICE FOR ITS EXECUTION

COMPOUND CERAMIC(S) MATERIAL WITH GRADED THERMOCHEMICAL PROTECTIVE LAYER

Method of manufacturing high strength glass fibers in a direct melt operation and products formed there from

A method of forming high strength glass fibers in a glass melter substantially free of platinum or other noble metal materials, products made there from and batch compositions suited for use in the method are disclosed. One glass composition for use in the present invention includes 50-75 weight % SiO2, 13-30 weight % Al2O3, 5-20 weight % MgO, 0- 10 weight % CaO, 0 to 5 weight % RO where RO is the sum Of LiO, NaO and KO, has a higher fiberizing temperature, e.g. 2400 - 2900° F (1316 - 1593 ° C) and/or a liquidus temperature that is below the fiberizing temperature by as little as 45 ° F (25° C). Another glass composition for use in the method of the present invention is up to about 64-75 weight percent SiO, 16-24 weight percent AlO, 8-12 weight percent MgO and 0.25-3 weight percent RO, where RO equals the sum Of LiO, NaO and KO, has a fiberizing temperature less than about 2650° F (1454 ° C), and a T of at least 80° F (45 ° C). A forehearth (12) for transporting molten glass from the glass ...

Apparatus for incineration or gasification using high temperature corrosion resistant alloy

SMOOTH OUTER COATING FOR COMBUSTOR COMPONENTS AND COATING METHOD THEREFOR

REFRACTORY VESSEL AND LINING THEREFOR

A refractory vessel that can be used as a gasifier for black liquor includes a generally cylindrical metal shell having a dome. A refractory shell has a cylindrical portion spaced inwardly from the metal shell and a dome portion that is spaced inwardly from the metal dome. The refractory shell is sized to provide an expansion gap between the liner and the metal shell. A selectively crushable liner is positioned in the gap. The liner has a predetermined yield stress that will provide controlled resistance to expansion of the refractory shell.

REFRACTORY PANELS WITH GROUT-CAPTURING CHANNELS

A refractory panel is formed with recesses delineating a pair of adjoining brick relief patterns. One or more depressions are formed in the recesses such tha t grout or the like placed in the recesses form fingers that harden into position.

VOID STRUCTURES WITH REPEATING ELONGATED-APERTURE PATTERN

Void structures, systems and devices with void structures, and methods of fabricating void structures are disclosed. A void structure is disclosed with a repeating elongated-aperture pattern designed to provide negative Poisson's Ratio behavior under macroscopic stress and strain loading. The pattern can include horizontal and vertical elliptically shaped apertures that are arranged on horizontal and vertical lines in a way that the lines are equally spaced in both dimensions. The centers of each aperture is on a crossing point of two of the lines. The vertical and horizontal elliptically shaped apertures alternate on the vertical and horizontal lines such that any vertical aperture is surrounded by horizontal apertures along the lines (and vice versa), and the next vertical apertures are found on both diagonals. The voids can also act as cooling and/or damping holes and, due to their arrangement, also as stress reduction features.

DEVICE FOR PRODUCING METHANE GAS AND USE OF SUCH A DEVICE

L' invention concerne un dispositif de production d'un gaz méthane (G) comportant une enceinte (1), des moyens de convoyage du produit dans l'enceinte qui comprennent une vis (10) montée pour tourner dans l'enceinte selon un axe géométrique de rotation, des moyens de chauffage par effet Joule de la vis, une unité d'élimination (12) d'impuretés présentes dans le gaz issu du traitement thermique du produit, ladite unité étant raccordée à une sortie haute de l'enceinte, et un système de purification (21) du gaz en sortie de l'unité d' élimination.

ENGINE COMPONENT AND METHODS FOR AN ENGINE COMPONENT

An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a multi-faceted diffusing section configured to improve the adhesion of a coating on the substrate.

NOVEL MICROWAVE ASSISTED FLASH PYROLYSIS SYSTEM AND METHOD THEREOF

The present invention provides a microwave assisted flash pyrolysis system to carry out microwave assisted flash pyrolysis in an industrial scale. The microwave assisted flash pyrolysis system comprises at least one microwave generator; a chamber comprises: at least one feedstock inlet, at least one baffle plate, a microwave-transparent rotating window, and at least one microwave inlet, at least one wet gas outlet, and at least one dry end product outlet. The present invention also provides a method using the same system to carry out microwave assisted flash pyrolysis.

CONFIGURATION FOR JOINING A CERAMIC THERMAL INSULATING MATERIAL TO A METALLIC STRUCTURE

Configuration (10) for joining a ceramic layer (1) comprising a thermal insulating material to a metallic layer (2), the configuration (10) comprising an interface layer (11) made of metallic material, located between the ceramic layer (1) and the metallic layer (2), comprising a plurality of interlocking elements (20) on one of its sides, facing the ceramic layer (1), the ceramic layer (1) comprising a plurality of cavities (30) aimed at connecting with the corresponding interlocking elements (20) of the interface layer (11), the configuration (10) also comprising a brazing layer (40) by means of which the interface layer (11) is joint to the metallic layer (2). The invention also refers to a method for obtaining such configuration (10).

METHOD OF MANUFACTURING HIGH STRENGTH GLASS FIBERS IN A DIRECT MELT OPERATION AND PRODUCTS FORMED THERE FROM

A process for producing glass fibers comprises charging raw glass batch to a melting zone; heating the batch to form a fiberizable molten glass; and fiberizing the molten glass to produce glass fibers having a strength of greater than about 700 KPsi and a density <= 2.486 g/cc. The batch comprises 64-75 wt% SiO2; 16-26 wt% Al2O3; <= 2.0 wt.% CaO; 8-12 wt% MgO; and 0-3 wt% R2O (=sum of Li2O, Na2O and K2O). In another process, a glass batch comprising 68-69 wt% SiO2; 20-22 wt% Al2O3; <= 2.0 wt.% CaO; 9-10 wt% MgO; and 1-3 wt% Li2O is melted to form a fiberizable molten glass. In a further process, a glass batch comprising 64-75 wt SiO2; 16-24 wt% Al2O3; <=2.0 wt.% CaO; 8-12 wt% MgO; and 0.25-3 wt% R2O (=sum of Li2O, Na2O and K2O) is heated and fiberized. Articles formed from the produced glass fibers are also provided.

COMBUSTION CHAMBER

A combustion chamber has a vertically oriented body with an inner surface defining an inner combustion area. A burner is disposed adjacent one end of the body so that the flame of the burner when lit will extend into the combustion area. An annular insert is disposed in the combustion area and generally surrounds the flame of the burner. The annular insert defines a secondary gas introduction zone for introducing secondary gases into the combustion area so that the recycled gases can be oxidized by the burner flame. The insert has an inner surface presenting at least one opening for allowing fluid communication between the introduction zone and the combustion area. The opening is disposed tangentially to the insert inner surface to direct gases in rotational motion to define a film of gases adjacent the inner surface of the combustion chamber. The body of the chamber can include an outer shell and an inner cylindrical liner. The outer shell has a generally horizontal inwardly extending ...

System having a layered structure and method of manufacturing the same.

Ein System enthält eine Schichtstruktur. Die Schichtstruktur enthält eine erste (50) und eine zweite (52) koaleszierte Schicht und eine Zwischenschicht (54), die zwischen der ersten (50) und der zweiten (52) koaleszierten Schicht angeordnet ist. Die erste und die zweite (52) koaleszierte Schicht haben ein höheres Mass an Koaleszenz als die Zwischenschicht (54).

Refractory wall, in particular for a combustion furnace.

Eine insbesondere für den Einsatz in einem Verbrennungsofen vorgesehene feuerfeste Wand umfasst eine Rohrwand (1) aus durch Stege (12) verbundenen Rohren (11) und eine im Abstand zu der Rohrwand vorgesetzte feuerfeste Schutzverkleidung (2) aus einer Vielzahl von neben- und übereinander angeordneten feuerfesten Platten (21), die über je mindestens eine Plattenhalterung (22) an den Stegen (12) der Rohrwand befestigt sind. Zwischen der Rohrwand (1) und der Schutzverkleidung (2) ist ein Zwischenraum (3) vorhanden, in welchem zumindest zonenweise ein partikuläres Füllmaterial (P) angeordnet ist, welches den Wärmeübergang zwischen Schutzverkleidung und Rohrwand erhöht. Durch Materialauswahl und zonenweise lokale Verteilung des partikulären Füllmaterials kann der Wärmeübergang quantitativ und lokal gezielt beeinflusst und damit den jeweiligen Betriebserfordernissen des Verbrennungsofens optimal angepasst werden.

Feuerfeste Wand, insbesondere für einen Verbrennungsofen.

Eine insbesondere für den Einsatz in einem Verbrennungsofen vorgesehene feuerfeste Wand umfasst eine Rohrwand (1) aus durch Stege (12) verbundenen Rohren (11) und eine im Abstand zu der Rohrwand vorgesetzte feuerfeste Schutzverkleidung (2) aus einer Vielzahl von neben- und übereinander angeordneten feuerfesten Platten (21), die über je mindestens eine Plattenhalterung (22) an den Stegen (12) der Rohrwand befestigt sind. Zwischen der Rohrwand (1) und der Schutzverkleidung (2) ist ein Zwischenraum (3) vorhanden, in welchem zumindest zonenweise ein partikuläres Füllmaterial (P) angeordnet ist, welches den Wärmeübergang zwischen Schutzverkleidung und Rohrwand erhöht. Durch Materialauswahl und zonenweise lokale Verteilung des partikulären Füllmaterials kann der Wärmeübergang quantitativ und lokal gezielt beeinflusst und damit den jeweiligen Betriebserfordernissen des Verbrennungsofens optimal angepasst werden.

Feuerfeste Wand, insbesondere für einen Verbrennungsofen.

Eine feuerfeste Wand insbesondere für einen Verbrennungsofen, umfasst ein, insbesondere metallisches, Basiselement (1) und eine dem Basiselement (1) vorgesetzte feuerfeste Schutzverkleidung (2) aus feuerfesten Platten (21). Zum Schutz gegen durch die Schutzverkleidung (2) hindurchgetretene Rauchgase weist das Basiselement (1) zumindest an einer der Schutzverkleidung (2) zugewandten Seite eine keramische Korrosionsschutzschicht (10) auf.

Refractory wall, in particular for a combustion furnace.

Eine feuerfeste Wand, insbesondere für einen Verbrennungsofen, umfasst ein, insbesondere metallisches, Basiselement (1) und eine dem Basiselement (1) vorgesetzte feuerfeste Schutzverkleidung (2) aus feuerfesten Platten (21). Zum Schutz gegen durch die Schutzverkleidung (2) hindurchgetretene Rauchgase weist das Basiselement (1) zumindest an einer der Schutzverkleidung (2) zugewandten Seite eine keramische Korrosionsschutzschicht (10) auf.

REFRACTORY CERAMIC BATCH COMPOSITION, USE OF A BATCH COMPOSITION OF THIS TYPE, AND METALLURGICAL MELTING VESSEL

INSTALLATION FOR BURNING FUEL AT HIGH TEMPERATURE AND HIGH PRESSURE

СПОСОБ И УСТРОЙСТВО ДЛЯ СЖИГАНИЯ ТОПЛИВА ПРИ ВЫСОКОЙ ТЕМПЕРАТУРЕ И ВЫСОКОМ ДАВЛЕНИИ И СООТВЕТСТВУЮЩИЕ СИСТЕМА И СРЕДСТВА

В заявке описано устройство камеры сгорания, содержащее смесительную установку, предназначенную для смешивания углеродного топлива с обогащенным кислородом и рабочим телом с образованием топливной смеси. Камера сгорания, по меньшей мере, частично сформирована испарительным элементом. Испарительный элемент, по меньшей мере, частично охвачен элементом защитной оболочки высокого давления. Камера сгорания имеет противолежащие входную и выходную части. Входная часть камеры сгорания выполнена с возможностью приема топливной смеси для ее сжигания при некоторой температуре горения. Камера сгорания выполнена с возможностью направления получающихся продуктов горения к выходной части. Испарительный элемент направляет сквозь себя испаряющуюся субстанцию в камеру сгорания для предотвращения непосредственного взаимодействия между продуктами горения и испарительным элементом. Описаны также соответствующие системы, устройства и способы.

SYSTEM AND METHOD OF HIGH EFFECTIVE ENERGY PRODUCTION USING CIRCULATING WORKING MEDIUM CARBON DIOXIDE

ЛОПАТКА ГАЗОВОЇ ТУРБІНИ З УДОСКОНАЛЕНИМИ КОНТУРАМИ ОХОЛОДЖЕННЯ

Лопатка газової турбіни для авіаційного двигуна обладнана принаймні трьома охолоджуючими контурами. Перший охолоджуючий контур містить принаймні одну порожнину на увігнутому боці пера лопатки, витягнуту у радіальному напрямку поблизу увігнутої поверхні пера. Другий охолоджуючий контур не залежить від першого охолоджуючого контуру і містить принаймні одну порожнину на опуклому боці пера, витягнуту в радіальному напрямку поблизу опуклої поверхні пера. Третій охолоджуючий контур незалежний від першого і другого охолоджуючих контурів і містить принаймні одну центральну порожнину, розташовану у центральній частині пера лопатки між порожниною на увігнутому боці пера і порожниною на опуклому боці пера, принаймні одну порожнину поблизу вхідної крайки пера, з'єднувальні отвори , що зв'язують центральну порожнину та порожнину поблизу вхідної крайки пера, а також випускні отвори , що сполучаються з указаною порожниною поблизу вхідної крайки пера та виходять на вхідну крайку пера. Таке виконання дозволяє ...

INSTALLATION FOR BURNING FUEL AT HIGH TEMPERATURE AND HIGH PRESSURE

SYSTEM AND METHOD FOR HIGH EFFICIENCY POWER GENERATION USING A CARBON DIOXIDE CIRCULATING WORKING FLUID

REFRACTORY CERAMIC BATCH COMPOSITION, USE OF A BATCH COMPOSITION OF THIS TYPE, AND METALLURGICAL MELTING VESSEL

METHOD AND APPARATUS FOR COMBUSTING A FUEL AT HIGH PRESSURE AND HIGH TEMPERATURE, AND ASSOCIATED SYSTEM AND DEVICES

SELF-CLEANING WINDOW FOR A COMBUSTION HEATER AND GLASS WALL

PART OF COMPOSITE MATERIAL

La présente invention concerne une pièce en matériau composite comprenant au moins : - un renfort fibreux comprenant des fibres de carbure de silicium présentant une teneur en oxygène inférieure ou égale à 1% en pourcentage atomique, et - une matrice présente dans la porosité du renfort fibreux et comprenant au moins un silicate de terre rare, de la mullite ou un mélange de mullite et d'au moins un silicate de terre rare.

COMPONENT WITH DIAGONALLY EXTENDING RECESSES IN THE SURFACE AND METHOD FOR OPERATING A TURBINE

Thermally stressed components can be protected against excessive heat input by active cooling, or by applying thermal insulation layers. The invention increases said effect, by providing diagonally extending slots (19) in the surface (16) of the component (1, 120, 130). COPYRIGHT KIPO & WIPO 2010 ...

aparelho e método para combustão de um combustível em alta pressão e alta temperatura e sistema e dispositivo associados.

GASIFICATION REACTOR COMPRISING A PRESSURE ABSORBING COMPLIANT STRUCTURE

A reactor for gasification of feedstocks for gasification, adapted to handle feedstocks for gasification comprising organic and inorganic compounds, wherein said compounds during gasification in the presence of oxygen and/or air at a gasification temperature, wherein the melting temperatures of the constituent inorganic compounds is at least 100°C lower than the gasification temperature, are converted to a hot reducing gas above 950°C but below 1300°C and comprising CO, CO2, ¾ and H2O (g), and a salt melt, wherein said reactor (100) comprises an outer reactor shell (7) and an inner refractory lining (2, 3, 4), wherein a compliant structure (5) is placed in a ring-shaped coaxial expansion space (6) between said outer reactor shell (7) and said inner refractory lining (2, 3, 4), wherein said compliant structure has a resilience and comprises a plurality of substantially parallel arranged metal profiles (12), adapted to distribute the compressive load between said reactor shell (7) and the ...

DEVICE FOR PRODUCING, STORING, AND SUPPLYING HEAT TO AN AREA TO BE HEATED

The invention relates to a device for producing, storing and supplying heat to an area to be heated, said device comprising a combustion chamber (12) which is defined and surrounded by an envelope (14) consisting of a fireproof material, a combustion device (46) which is arranged in the combustion chamber (12) and can be supplied with a gas/air mixture, and an air evacuation duct (84) arranged in a lower region (80) of the combustion chamber (12). Said combustion chamber (12) is sealed from the gas/air mixture which is supplied to the combustion device (46) and to be burned, and the combustion device (46) is embodied as a fully pre-mixed gas jet burner (48) with a combustion medium (50) having a homogeneous, permeable matt structure or the like.

Gradual oxidation and autoignition temperature controls

Described herein are embodiments of systems and methods for oxidizing gases. In some embodiments, a reaction chamber is configured to receive a fuel gas and maintain the gas at a temperature within the reaction chamber that is above an autoignition temperature of the gas. The reaction chamber may also be configured to maintain a reaction temperature within the reaction chamber below a flameout temperature. In some embodiments, heat and product gases from the oxidation process can be used, for example, to drive a turbine, reciprocating engine, and injected back into the reaction chamber.

CONDUCTIVE PANEL SURFACE COOLING AUGMENTATION FOR GAS TURBINE ENGINE COMBUSTOR

A liner panel for use in a combustor of a gas turbine engine includes a substrate with a hot side and a cold side; a bond coat on at least one of the hot side and the cold side of the substrate; and a convective feature on the cold side of the substrate of a material different than a material of the substrate. A wall assembly for use in a combustor of a gas turbine engine includes a shell with a multiple of impingement flow passages; and a liner panel mounted to the shell, where the panel includes a convective feature which faces the shell. A method of cooling a liner panel for a combustor section of a gas turbine engine includes directing an impingement flow towards a convective feature of a liner panel; and directing an effusion flow through the liner panel.

METHOD FOR HIGH EFFICIENCY POWER GENERATION USING A CARBON DIOXIDE CIRCULATING WORKING FLUID

Matrix and coating system

Matrix for use in components or layers is made up of particles with a core (7) made from a first element or compound which is enclosed in a sheath (4) made from a second element or compound. The core is made from a metal, metal oxide, non-metal oxide, glass, Si-O-C (sic) or a mixture of these. An independent claim is included for layer systems comprising a substrate and a layer containing the matrix.

PART IN CERAMIC MATRIX COMPOSITE

CERAMIC LINING

PROBLEM TO BE SOLVED: To guarantee a controllable line contact over the entire operational conditions by providing a fixed element with a head part beveled roundly and pushing it against a supporting face having linear cross-section at the opening in a wall panel using that part. SOLUTION: An insulation layer 2 of ceramic fiber material is employed in the metallic supporting wall 1 of a gas turbine combustor. A through hole for containing a fixed element 4 is made in the center of a wall panel 3 wherein the fixed element 4 is a pin comprising a head part, a drum part and a base part. Each wall panel 3 is provided with a plurality of openings 6. A constant contact is kept surely between the head part 20 of the fixed element 4 arranged in the opening 6 and the wall panel 3. The head part 20 is thereby provided with a spherical supporting face which is utilized for abutting against a supporting face 22 having linear cross-section. According to the means, a region forming line contact can be ...

Lining segment for pipes and pipelines comprises spacer bars protruding from a first edge with a first intermediate chamber formed between the spacers

Lining segment (10) comprises spacer bars (18) protruding from a first edge (14) with a first intermediate chamber (26) formed between the spacers. A second spacer bar (20) protrudes from a second edge and is not wider than the first intermediate chamber. The first spacer bars are arranged relative to the second spacer bars in a V-shaped manner. Preferred Features: The edges are parallel to each other or form an angle with each other. The segment has a planar base section (12).

Accessible twin chamber kiln has insulation portion with outer wall which comprises lockable access opening for input and removal of insulation packages in insulation space between outer wall and combustion chamber

The twin chamber kiln (1) has an insulation portion (2) surrounded a combustion chamber (3), which comprises outer wall (5) and insulation space (4) between outer wall and combustion chamber for accommodating insulation packages (7) such as mineral wool. The outer wall comprises lockable access opening for the input and removal of the insulation packages in the insulation space. Independent claims are included for the following: (1) method for replacing insulation portion of twin chamber kiln; and (2) method for manufacturing insulation package.

Ceramic materials

A combustion chamber sealing ring and a combustion chamber including such a ring

Methods of manufacturing and repairing air cooled gas turbine components

A component for use in a gas turbine engine includes a substrate 33 having first and second surfaces. At least one aperture 160 extends through the substrate from the first surface to the second surface and has a first open area. The component has a first coating 212 applied adjacent to the aperture and second coating 214 applied to overlay the first coating adjacent to the aperture. At least a portion of the first coating is exposed adjacent to the aperture by subsequent removal of a portion of the second coating adjacent to the aperture. Turbine component coatings can be repaired in a similar manner by removal of the damaged coating prior to the application of the new coatings. Preferred embodiments include the coating and repair of components such as combuster liners having cooling holes.

A method of manufacturing a thermal barrier coated article

Combusution for gas-or-liquid-fuelled turbine

combustion apparatus

Gas incinerator with fragmentary insulation bed

An incinerator 20 includes a generally vertical combustion chamber 40 where gas G, admitted into a proximal end of chamber 40, is burned in the presence of air A, and combustion products C are discharged at a distal end (outlet 60), and a thermally insulating fragmentary bed 62 (e.g. pumice supported by metal tray 64, formed to drain water from bed 62) extending generally horizontally across chamber 40. Bed 62 may include fragments of about 50mm diameter, to a vertical depth of 150mm to 200mm, held in compartments. Chamber 40 may have an inner 48 and outer 50 wall, forming a first passage 52, and a flame shield 54, forming a second passage 56, through which dilution air D flows before mixing with combustion products C in chamber 40. Incinerator 20 may be installed on an LNG carrier (10, Figure 1) (i.e. ship) to burn boil-off gas.

PROCEDURE FOR THE ATTACHMENT OF FIREPROOF STRUCTURE AS PROTECTION FOR WATER PIPES

TWO-LAYER FIREPROOF PLATE AS WELL AS PROCEDURE FOR THEIR PRODUCTION

Burner for a fuel cell system with two reaction chambers

Die Erfindung betrifft einen Brenner (1) für ein Brennstoffzellensystem (100), insbesondere ein SOFC-System, wobei der Brenner (1) als Startbrenner und/oder Nachbrenner ausgebildet und angeordnet ist, umfassend einen ersten Betriebsfluidleitabschnitt (2) und einen zweiten Betriebsfluidleitabschnitt (3), wobei der Brenner (1) zwei nacheinander angeordnete und jeweils einen Kammereingang (4a, 4b) und einen Kammerausgang (5a, 5b) aufweisende Reaktionskammern (6, 7) umfasst, wobei in Strömungsrichtung ein Kammereingang (4b) einer zweiten Reaktionskammer (7) auf einen Kammerausgang (5a) einer ersten Kammer Reaktionskammer (6) folgt, wobei die Reaktionskammern (6, 7) jeweils ein katalytisches Material (18) aufweisen. Weiter betrifft die Erfindung eine Verwendung eines solchen Brenners (1) und ein Brennstoffzellensystem mit einem solchen Brenner (1). Des Weiteren betrifft die Erfindung ein Verfahren zum Betreiben eines Brennstoffzellensystems mit einem solchen Brenner (1).

WASTE BURNING APPARATUS FOR CONSTRAINT VENTILATION FORM

Support shelves for gasifier dome and thermocouple

A gasifier lining comprises a first support shelf located directly under a dome area of the gasifier lining: and a second support shelf located directly under a thermocouple that penetrates the gasifier lining. A method of producing a gasifier comprising support shelves comprises providing a first support shelf directly under a thermocouple insertion area in a lining of the gasifier; and providing a second support shelf m the lining of the gasifier directly under a dome area of the gasifier.

A COMBUSTION CHAMBER SEALING RING, AND A COMBUSTION CHAMBER INCLUDING SUCH A RING

The present invention provides a fixing or sealing ring (1) for maximizing cooling at the end of a combustion chamber wall. For this purpose, the ring (1) is constituted by a sleeve (1a) which is fixed around the end of a wall (51a) of the combustion chamber by means of a plurality of orifices for receiving fasteners or by means of any other system for connecting the ring to the wall. The sleeve (1a) includes at least one recess (3) in its face facing the wall (51a) of the combustion chamber, thereby reducing the area of the sleeve (1a) that presses against the wall (51a), and co-operating with said wall to form an open cavity (6) in which a cooling air stream (63) can flow.

METHOD FOR PRODUCING FABRICATED PARTS BASED ON .BETA.-SIC FOR USING IN AGGRESSIVE MEDIA

BRAZED JOINT BETWEEN A TITANIUM-BASED METAL PART AND A CERAMIC PART BASED ON SILICON CARBIDE (SIC) AND/OR CARBON

Assemblage par brasage entre une pièce métallique à base de titane et une pièce en matériau céramique à base de carbure de silicium (SiC) et/ou de carbone. Cet assemblage comporte une structure empilée comportant les éléments suivants assemblés deux à deux par brasage: la pièce métallique (10) à base de titane, un premier intercalaire (11) apte à se déformer pour accommoder un différentiel de dilatation entre la pièce métallique (10) et une pièce en matériau céramique (20) à base de carbure de silicium et/ou de carbone, un deuxième intercalaire (12) rigide, de coefficient de dilatation proche de celui de ladite pièce en matériau céramique (20) en nitrure d'aluminium (AIN) ou en tungstène (W) , et la pièce en matériau céramique (20).

ALUMINA-MAGNESIA MATERIAL FOR A GASIFIER

La présente invention concerne un produit réfractaire fondu et coulé présentant une composition chimique telle que, en pourcentages massiques sur la base des oxydes : - AI2O3 : complément à 100%; - MgO : 28% à 50%; - CuO 0,05% à 1,0%; --B2O3 : 1,0%; - SiO2 : < 0,5%; - Na2O + K2O : < 0,3%; - CaO : < 1,0%; - Fe2O3 + TiO2 : < 0,55%; - autres espèces oxydes : < 0,5%.

SYSTEM AND METHOD FOR HIGH EFFICIENCY POWER GENERATION USING A CARBON DIOXIDE CIRCULATING WORKING FLUID

The present invention provides methods and system for power generation using a high efficiency combustor (220) in combination with a CO2 circulating fluid (236). The methods and systems advantageously can make use of a low pressure ratio power turbine (320) and an economizer heat exchanger (420) in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO2 circulating fluid. Fuel derived CO2 can be captured and delivered at pipeline pressure. Other impurities can be captured.

REFRACTORY CERAMIC BATCH, USE OF A BATCH OF THIS KIND AND A METALLURGICAL MELTING VESSEL

The invention relates to a refractory ceramic batch composition for producing an unshaped refractory ceramic product; to the use of a batch composition of this type for lining metallurgical melting vessels; and to a metallurgical melting vessel lined with an unshaped refractory ceramic product based on a batch composition of this type.

USE OF NON-FIRED REFRACTORY PRODUCTS AS A LINING OF LARGE-VOLUME INDUSTRIAL FURNACES AND INDUSTRIAL FURNACES LINED WITH THE NON-FIRED REFRACTORY PRODUCTS

The invention relates to the use of non-fired refractory products, free of carbon carriers, particularly molded using presses or not molded, containing binders and, in each instance, granulations of the refractory materials that enter into ceramic binding at temperatures above 900°C, for the production of: magnesia chromite bricks, magnesia spinel and spinel bricks, magnesia zirconia and magnesia zircon bricks, magnesia hercynite and magnesia galaxite bricks, dolomite, dolomite-magnesia, and lime bricks, forsterite and olivine bricks, magnesia forsterite bricks, magnesia pleonast bricks, magnesia bricks, as a fire-side, refractory lining of large-volume industrial furnaces operated with an oxidizing or essentially oxidizing atmosphere, for the production of cement, lime, magnesia, and doloma, in the form of pressed bricks or non-molded masses, wherein the bricks have a cold pressure strength above 20 MPa, and the products contain at least a first temporary binder that guarantees binding ...

FLUID FUEL BURNING DEVICE

A fluid fuel burning device, comprising: an elongated combustion compartment comprising side walls, where distal end is open allowing fluid communication from inside the combustion compartment and out of compartment; an insulation layer arranged on the inner surface of the side walls and/or on an inner surface of the proximal end of the compartment, preventing heat inside the compartment from radiating away from the compartment from the side walls and/or the proximal end, air flow means for providing a current of air, a fuel nozzle for aerification of the fluid fuel inside the combustion compartment, fuel feeding means for feeding fluid fuel to the fuel nozzle, pressure providing means for applying pressure to the fluid fuel fed via the fuel feeding means, and where the insulation layer comprises a heat absorbent layer that is of a temperature retentive material and radiating heat from the absorbent layer into the combustion compartment.

NOVEL MICROWAVE ASSISTED FLASH PYROLYSIS SYSTEM AND METHOD THEREOF

The present invention provides a microwave assisted flash pyrolysis system to carry out microwave assisted flash pyrolysis in an industrial scale. The microwave assisted flash pyrolysis system comprises at least one microwave generator; a chamber comprises: at least one feedstock inlet, at least one baffle plate, a microwave-transparent rotating window, and at least one microwave inlet, at least one wet gas outlet, and at least one dry end product outlet. The present invention also provides a method using the same system to carry out microwave assisted flash pyrolysis.

Combustion Chamber

VOID STRUCTURES WITH REPEATING ELONGATED-APERTURE PATTERN

REFRACTORY CERAMIC CHARGE, SAID CHARGE APPLICATION TYPE AND METALLURGICAL MELTING CAPACITY

КІЛЬЦЕВА КАМЕРА ЗГОРЯННЯ З ДВОМА ГОЛОВКАМИ,ЗМІЩЕНИМИ ОДНА ВІДНОСНО ОДНОЇ

Кільцева камера згоряння для авіаційного газотурбінного двигуна, обладнана двома головками, які зміщені одна відносно одної, яка містить пускову головку, що має декілька форсункових систем, розподілених на торцевій стінці, що належить камері пускової головки, яка з'єднує внутрішню поздовжню бокову стінку камери із зовнішньою поздовжньою боковою стінкою пускової головки, і злітну головку, яка зміщена радіально і уздовж осі від пускової головки та містить декілька форсункових систем, розподілених на торцевій стінці, що належить камері злітної головки, яка з'єднує зовнішню поздовжню бокову стінку пускової головки та зовнішню поздовжню бокову стінку злітної головки. Пускова головка обладнана принаймні кількістю N по суті ідентичних форсункових систем сумарною пропускною спроможністю РА і призначена для режиму запуску та швидкостей, близьких до швидкостей неробочого ходу, а злітна головка обладнана принаймні кількістю 2N по суті ідентичних форсункових систем сумарною пропускною спроможністю ...

INSTALLATION FOR BURNING FUEL AT HIGH TEMPERATURE AND HIGH PRESSURE

SYSTEM AND METHOD FOR HIGH EFFECTIVE ENERGY PRODUCTION USING AS CIRCULATING WORKING MEDIUM CARBON DIOXIDE

通过光反射来降低温度的改进的高温中心体及其制造方法

... 用于气体流径中的高温气体涡轮部件，该气体流径也是一种镜面光反射器。高温反射薄层施加到部件的气体流径上，也就是，施加到构成燃烧热气边界的部件的表面上。部件通常包括一个覆盖在高温金属部件上的隔热涂层，以允许部件在高温下工作。必须对隔热涂层进行抛光，以便获得一个适合于将辐射能反射到气体流径中的表面。然后通过一个在不增大表面的粗糙度的情况下就足以将反射层粘结到抛光表面上的程序来将高温反射薄层施加到抛光的隔热涂层上。被反射的辐射能不会汇聚到其它任何硬件部件上。该部件设计成可使辐射能返回到气体流径中或传送到大气环境中，而不会被吸收到部件壁面中而仅使壁面温度升高。 ...

Microwave flash thermal cracking system and method thereof

TRANSPARENT WALL OF A HEATED CHAMBER SELF-CLEANING

CRACKING FURNACE

METHOD FOR REALIZATION Of a MULTIPERFORATE COMPOSITE MATERIAL PART AMATRICE CERAMIC

COMBUSTION CHAMBER FOR TURBOSHAFT ENGINE

L'invention concerne une chambre de combustion (1) pour turbomachine telle qu'un turboréacteur ou un turbopropulseur d'avion, comportant des parois annulaires interne et externe (3, 4) de révolution, reliées par une paroi annulaire de fond de chambre (5). Au moins une desdites parois interne et externe (3, 4) est constituée d'une seule épaisseur de matériau dont l'épaisseur et/ou la nature varie le long de l'axe longitudinal et/ou de la direction circonférentielle de ladite paroi (3, 4).

Fireplace e.g. opened fireplace, for use in chimney, has inlet located in combustion space between intermediate and lower walls, and outlet located near outlet pipe between intermediate and upper walls

L'invention concerne un foyer de cheminée (100) comportant: - un volume de combustion (118), - une buse d'évacuation (116), et - une chicane (150) comportant: - une paroi inférieure (156) constituant une frontière avec le volume de combustion (118) et réalisée dans un matériau présentant de fortes capacités à transmettre la chaleur, - une paroi supérieure (114, 164) réalisée dans un matériau présentant de fortes capacités à transmettre la chaleur, -une paroi intermédiaire (158) disposée entre la paroi inférieure (156) et la paroi supérieure (114, 164) et réalisée dans un matériau présentant de fortes capacités d'isolant thermique, - une entrée (152) se situant dans le volume de combustion (118) entre la paroi intermédiaire (158) et la paroi inférieure (156), et - une sortie (154) se situant au voisinage de la buse d'évacuation (116) entre la paroi intermédiaire (158) et la paroi supérieure (114, 164).

PRODUCT CALCINING VITRIFIES

PROCESS AND SYSTEM TO DETECT MATTER DEFECTS IN THE ENGINES HAVE TURBINE HAS COMBUSTION.

Système pour détecter des défauts dans un conduit de combustion d'un système de combustion d'un moteur à turbine à combustion pendant le fonctionnement du moteur à turbine à combustion, le conduit de combustion comportant un côté chaud, qui est exposé à des gaz de combustion et, à l'opposé du côté chaud, un côté froid. Le système peut comporter : un revêtement témoin (163) disposé sur une surface extérieure du conduit de combustion, le revêtement témoin (163) étant constitué par une substance détectable ; et un détecteur de gaz installé en aval du système de combustion, le détecteur de gaz étant conçu pour réaliser une mesure de la quantité de substance détectable dans les produits de combustion du moteur à turbine à combustion.

Metal injection molding process and components formed therewith

A process of producing a metallic component having a desired shape that includes at least one nonuniform section, as well as metallic components produced by such a process. The process uses a composition containing a mixture of a polymeric binder and a metal powder that includes particles of an alloy having a reactive element that renders the alloy uncastable. The composition is metal injection molded to yield a green compact having a shape corresponding to the shape of the metallic component, including its at least one nonuniform section. A majority of the binder is then removed from the green compact, and then the green compact is sintered to remove a remainder of the binder and fuse particles of the metal powder together to form the metallic component and the nonuniform section thereof.

A combustor applied in thermophotovoltaic system

A combustor applied in thermophotovoltaic system comprises a combustion device and a reversed tube covering the combustion device. The combustion device includes a combustion body made of a transparent, and temperature resistant material and a burning unit disposed in the combustion body. When a burning-supported medium is adopted during burning via the burning unit, the radiant intensity is increased. The reversed tube thence further redirects the hot product gas for reheating an outer wail of the combustion body in combustion. Therefore, uniform illumination is accordingly resulted for enhancing the radiant intensity. Accordingly, a photovoltaic cell plate connected to the combustor preferably transforms light into electricity. The present invention fully utilizes a micro system as well as miniature energy to offer advanced electricity.

Fireplace

A fireplace is provided that includes a combustion space delimited by a combustion-space lining and accessible through a door or flap. The combustion-space lining is at least partially composed of a ceramic or glass-ceramic material. The fireplace also includes a wall element disposed on a side of the combustion-space lining that faces away from the combustion space so that so that an intermediate space is formed between the side and the wall element. A heat exchanger or insulating material can be positioned in the intermediate space.

Integral Ceramic Matrix Composite Fastener With Polymer Rigidization

A gas turbine engine component includes a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure. The gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material. The at least one fastener connects the gas turbine engine component body to an engine support structure. 1. A gas turbine engine component comprising:a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure, wherein the gas turbine engine component body initially comprises a rigidized preform structure formed from a polymer based material; andan engine support structure, wherein the at least one fastener connects the gas turbine engine component body to the engine support structure.2. The gas turbine engine component according to wherein the rigidized preform structure has an opening to receive the fastener claim 1 , and wherein the fastener initially comprises a separate woven fastener formed from a fiber based material claim 1 , and wherein the woven fastener is received within the opening of the rigidized preform and subsequently infiltrated with a matrix material to form the single-piece structure as a finished component.3. The gas turbine engine component according to wherein the rigidized preform structure includes the polymer based material prior to forming the opening.4. The gas turbine engine component according to wherein the single-piece structure that forms the finished component does not include the polymer based material.5. The gas turbine engine component according to wherein the rigid perform structure is oxidized to remove the polymer based material prior to being infiltrated with the matrix material.6. The gas turbine engine component according to ...

VOID STRUCTURES WITH REPEATING ELONGATED-APERTURE PATTERN

Void structures, systems and devices with void structures, and methods of fabricating void structures are disclosed. A void structure is disclosed with a repeating elongated-aperture pattern designed to provide negative Poisson's Ratio behavior under macroscopic stress and strain loading. The pattern can include horizontal and vertical elliptically shaped apertures that are arranged on horizontal and vertical lines in a way that the lines are equally spaced in both dimensions. The centers of each aperture is on a crossing point of two of the lines. The vertical and horizontal elliptically shaped apertures alternate on the vertical and horizontal lines such that any vertical aperture is surrounded by horizontal apertures along the lines (and vice versa), and the next vertical apertures are found on both diagonals. The voids can also act as cooling and/or damping holes and, due to their arrangement, also as stress reduction features. 1. A void structure comprising:a rigid or semi-rigid body with a first plurality of first elongated apertures and a second plurality of second elongated apertures, each of the elongated apertures having a major axis and a minor axis, the major axes of the first elongated apertures being perpendicular to the major axes of the second elongated apertures, the first and second pluralities of elongated apertures being arranged in an array of rows and columns, each of the rows and each of the columns alternating between the first and the second elongated apertures, the apertures being cooperatively configured to achieve negative Poisson's Ratio behavior under stress or strain, or both.2. The void structure of claim 1 , wherein the first and second elongated apertures are elliptical.3. The void structure of claim 1 , wherein the first and second elongated apertures are I-shaped.4. The void structure of claim 1 , wherein the first and second elongated apertures each includes spaced holes connected by a stem.5. The void structure of claim 1 , ...

CERAMIC HEAT SHIELDS HAVING SURFACE INFILTRATION FOR PREVENTING CORROSION AND EROSION ATTACKS PROTECTING A COMPONENT, METHOD FOR LASER DRILLING, AND COMPONENT

An improved ceramic heat shield for a gas turbine is provided. The ceramic heat shield has a porous ceramic body and according to the embodiments an infiltration coating that is provided in a surface layer of the porous ceramic body and contains an infiltration coating material designed to gas-tightly seal pores of the ceramic body. 1. A ceramic heat shield for a gas turbine , comprising:a porous ceramic body,includingan infiltration coating which is infiltrated in a surface layer of the porous ceramic body and contains an infiltration coating material which is configured for closing pores of the ceramic body in a manner as gas-tight as possible.2. The ceramic heat shield as claimed in claim 1 , wherein the porous ceramic body contains mullite or aluminum oxide claim 1 , or is composed of mullite or aluminum oxide.3. The ceramic heat shield as claimed in claim 1 , wherein the infiltration material contains yttrium aluminum garnet or is composed of yttrium aluminum garnet claim 1 , or comprises aluminum oxide claim 1 , aluminum zirconate claim 1 , or is composed thereof.4. The ceramic heat shield as claimed in claim 1 , wherein the infiltration coating is at least one of a thickness of less than 400 μm claim 1 , has 400 μm claim 1 , and is at least 10 μm thick.5. The ceramic heat shield as claimed in claim 1 , wherein the surface layer extends across an end face and across lateral faces of the porous ceramic body.6. A gas turbine or a combustion chamber having a ceramic heat shield as claimed in .7. A method for producing a ceramic heat shield for a gas turbine claim 1 , comprising the following method steps:providing a porous ceramic body;generating an infiltration coating in a surface layer of the porous ceramic body, wherein the infiltration coating contains an infiltration coating material which is configured for closing pores of the porous ceramic body in a gas-tight manner.8. The method as claimed in claim 7 , wherein the generating of the infiltration coating ...

COMBUSTOR LINER ATTACHMENT ASSEMBLY FOR GAS TURBINE ENGINE

A combustor liner panel attachment assembly. The assembly includes a first liner extending from a first end to a second end, and circumferentially to partially define a combustion zone. The assembly also includes a second liner disposed circumferentially adjacent to the first liner. The assembly further includes a radial support having a shoulder in contact with a radially inner surface of each of the first liner and the second liner to radially retain the first liner and the second liner, the radial support allowing the first liner and the second liner to thermally grow axially. 1. A combustor liner panel attachment assembly comprising:a first liner extending from a first end to a second end, and circumferentially to partially define a combustion zone;a second liner disposed circumferentially adjacent to the first liner; anda radial support having a shoulder in contact with a radially inner surface of each of the first liner and the second liner to radially retain the first liner and the second liner, the radial support allowing the first liner and the second liner to thermally grow axially.2. The combustor liner panel attachment assembly of claim 1 , wherein the radial support is a T-head bolt.3. The combustor liner panel attachment assembly of claim 1 , wherein the shoulder of the radial support is disposed in a recess defined by the first liner and the second liner.4. The combustor liner panel attachment assembly of claim 1 , further comprising:a spring element located adjacent to a portion of the first liner and operatively coupled to a stationary structure, the spring element having a recessed segment; anda protrusion feature extending radially outwardly from the first liner, the protrusion feature disposed within the recessed segment of the spring element to axially retain the first liner.5. The combustor liner panel attachment assembly of claim 4 , wherein the spring element is operatively coupled to a bulkhead structure.6. The combustor liner panel ...

CRACKING FURNACE

The invention relates to a cracking furnace containing a tubular vertical chamber which comprises an inlet for introducing a gas to be treated and an outlet for removing said gas from the chamber, means for heating said gas which include a heating tube extending vertically inside the chamber and coaxial with the chamber, the heating tube being shaped in such a way as to have a closed lower end and being arranged in such a way that the lower end thereof is arranged in the chamber and such that the upper end thereof is connected to a burner of the heating means arranged outside the chamber. The invention also relates to an assembly comprising such a cracking furnace and a device for thermal treatment of biomass and/or waste, an outlet of which is connected to the inlet of said cracking furnace. 1. A cracking furnace comprising both a vertical tubular enclosure that includes an inlet for introducing a gas for treatment and an outlet for discharging said gas from the enclosure , and also means for heating said gas that comprise a heater tube extending vertically inside the enclosure and coaxially with the enclosure , the heater tube being shaped so as to have its bottom end closed and being arranged so that its bottom end is arranged inside the enclosure and so that its top end is connected to a burner of the heater means , which burner is arranged outside the enclosure.2. The cracking furnace according to claim 1 , wherein the enclosure is shaped so as to be of circular section.3. The cracking furnace according to claim 1 , wherein the heater tube is shaped so as to be of circular section.4. The cracking furnace according to claim 1 , wherein the inlet is arranged to cause the gas for treatment to penetrate into the enclosure along the inside wall of the enclosure.5. The cracking furnace according to any claim 1 , wherein the heater tube is based on ceramics.6. The cracking furnace according to any one claim 1 , wherein at least one of the inside walls of the enclosure ...

Atomic layer deposition coatings for high temperature heaters

Embodiments of the disclosure relate to articles, coated chamber components and methods of coating chamber components with a low volatile coating. The low volatile coating can include a rare earth metal-containing layer that coats all surfaces of a component (e.g., a high temperature heater).

INTEGRAL CERAMIC MATRIX COMPOSITE FASTENER WITH NON-POLYMER RIGIDIZATION

A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed. 1. A gas turbine engine component comprising: a fiber preform with an opening that has a wide portion at one surface of the fiber preform and a narrow portion at an opposite surface of the fiber preform,', 'a fiber fastener having a fastener body extending from a first end to a second end, the fastener body defined by a first dimension and having an enlarged head at the first end of the fastener body that is defined by a second dimension that is greater than the first dimension,', 'wherein the fiber fastener is inserted into the opening to form a dry fiber preform and fiber fastener assembly, the fastener body extending through the dry fiber preform such that the enlarged head portion is received within the wide portion of the opening, and', 'wherein a matrix material is infiltrated into the dry fiber preform and fiber fastener assembly to provide the single-piece structure; and, 'a gas turbine engine component body formed of a ceramic matrix composite material having at least one fastener integrally formed with the gas turbine engine component body as a single-piece structure, wherein the single-piece structure initially comprises'}an engine support structure, wherein the at least one fastener of the single-piece structure connects the gas turbine engine component body to the engine support structure.2. The gas turbine engine component according to wherein the fiber preform comprises a rigidized preform structure having the opening to receive the fiber fastener claim 1 , and wherein the fiber fastener comprises a woven fastener formed from a fiber based material ...

MANAGEMENT OF HEAT CONDUCTION USING PHONONIC REGIONS HAVING DOPED NANOSTRUCTURES

A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of doped nanostructures. The phononic regions modify the behavior of the phonons and control heat conduction. 120-. (canceled)21. A gas turbine engine component comprising:a first region of a first material and a phononic region, wherein the phononic region comprises doped nanostructures;wherein phononic transmittal of phonons through the first material forms a first phononic wave; andwherein, upon transmittal of the first phononic wave to the phononic region, the phononic region is configured to modify a behavior of the phonons of the first phononic wave.22. The gas turbine engine component of claim 21 , wherein the first phononic wave has a first property claim 21 , wherein the phononic region modifies the behavior of the phonons of the first phononic wave to form a second phononic wave having a second property different than the first property of the first phononic wave.23. The gas turbine engine component of claim 22 , wherein the first property and the second property are frequency.24. The gas turbine engine component of claim 22 , wherein the first property and the second property are modes of propagation.25. The gas turbine engine component of claim 21 , wherein the phononic region modifies the behavior of the phonons of the first phononic wave so that the phonons of the first phononic wave change direction of propagation.26. The gas turbine engine component of claim 21 , wherein the phononic region modifies the behavior of the phonons of the first phononic wave so that the phonons of the first phononic wave scatter.27. The gas turbine engine component of claim 21 , wherein the phononic region modifies the behavior of the phonons of the first phononic wave so that the phonons of the first phononic wave are reflected.28. The gas turbine engine component of claim 21 , the phononic region modifies the behavior of the phonons of the first phononic wave so ...

Management of Heat Conduction using Phononic Regions Having Anisotropic Nanostructures

A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of anisotropic nanostructures that are oriented in different directions than the bulk of the material forming the gas turbine engine component. The phononic regions modify the behavior of the phonons and manage heat conduction. 118-. (canceled)19. A gas turbine engine component comprising:a first region of a first material having a plurality of structures oriented in a first direction; anda phononic region of a same material as the first material, the phononic region comprising anisotropic nanostrcutures within the first material, the anisotropic nanostructures oriented in at least a second direction different from the first direction;wherein phononic transmittal of phonons through the first material forms a first phononic wave having the phonons; andwherein, upon transmittal of the first phononic wave to the phononic region, the phononic region is configured to modify a behavior of the phonons of the first phononic wave.20. The gas turbine engine component of claim 19 , wherein the first phononic wave has a first property claim 19 , wherein the phononic region is configured to the behavior of the phonons of the first phononic wave to form a second phononic wave having a second property different than the first property of the first phononic wave.21. The gas turbine engine component of claim 20 , wherein the first property and the second property are frequency.22. The gas turbine engine component of claim 20 , wherein the first property and the second property are modes of propagation.23. The gas turbine engine component of claim 19 , wherein the phononic region modifies the behavior of the phonons of the first phononic wave so that the phonons of the first phononic wave change direction of propagation.24. The gas turbine engine component of claim 19 , wherein the phononic region modifies the behavior of the phonons of the first phononic wave so that the ...

Management of heat conduction using phononic regions having non-metallic nanostructures

A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of non-metallic nanostructures. The phononic regions modify the behavior of the phonons and control heat conduction.

MANAGEMENT OF HEAT CONDUCTION USING PHONONIC REGIONS HAVING METALLIC GLASS NANOSTRUCTURES

A gas turbine engine component formed of material having phononic regions. The phononic regions are formed of metallic glass nanostructures. The phononic regions modify the behavior of the phonons and control heat conduction. 120-. (canceled)21. A gas turbine engine component comprising:a first region of a first material; anda phononic region comprising metallic glass nanostructures within the first material;wherein phononic transmittal of phonons through the first material forms a first phononic wave comprising the phonons; andwherein, upon transmittal of the first phononic wave to the phononic region, the phononic region is configured to modify a behavior of the phonons of the first phononic wave.22. The gas turbine engine component of claim 21 , wherein the first phononic wave has a first property claim 21 , wherein the phononic region modifies the behavior of the phonons of the first phononic wave to form a second phononic wave having a second property different than the first property of the first phononic wave.23. The gas turbine engine component of claim 22 , wherein the first property and the second property are frequency.24. The gas turbine engine component of claim 22 , wherein the first property and the second property are modes of propagation.25. The gas turbine engine component of claim 21 , wherein the phononic region modifies the behavior of the phonons of the first phononic wave so that the phonons of the first phononic wave change direction of propagation.26. The gas turbine engine component of claim 21 , wherein the phononic region modifies the behavior of the phonons of the first phononic wave so that the phonons of the first phononic wave scatter.27. The gas turbine engine component of claim 21 , wherein the phononic region modifies the behavior of the phonons of the first phononic wave so that the phonons of the first phononic wave are reflected.28. The gas turbine engine component of claim 21 , the phononic region modifies the behavior of the ...

SYSTEMS AND METHODS FOR OPTIMAL SOURCE MATERIAL DEPOSITION ALONG HOLE EDGES

A method for depositing a coating of a source material onto a panel is disclosed. The method includes providing a cathodic arc, the cathodic arc including a target surface, the target surface disposed along a target deposition axis and able to emit the source material as a generally cloud of source material vapor and a generally conical stream of liquid particles of the source material. The method further includes positioning the panel relative to the target surface based on a deposition angle, the deposition angle being between the target surface and an outer limit of the generally conical stream of liquid particles o the source material. The method may further include emitting the source material from the target surface as the generally conical cloud of source material vapor and coating the edge with the cloud of source material vapor to provide an edge coating. 1. A system for depositing a coating of a source material onto at least one panel , the at least one panel defining an edge and a front panel surface , the system comprising:a cathodic arc including a target surface, the target surface disposed along a target deposition axis, and able to emit the source material as both a cloud of source material vapor and a generally conical stream of liquid particles of the source material, the cloud of source material vapor used to coat the edge with the source material to provide an edge coating; anda coating deposition structure, the coating deposition structure positioning one or both of the cathodic arc and the panel, such that the panel is positioned relative to the target surface based on a deposition plane, the deposition plane being defined by the target deposition axis, wherein the entire panel is positioned above or below the deposition plane and within the generally conical stream of liquid particles.2. The system of claim 1 , wherein the coating deposition structure positions the panel substantially perpendicular to the target deposition axis.3. The system ...

METALLIC COATING PROCESS FOR COMBUSTOR PANELS USING A BARREL CONFIGURATION

A method of coating a component includes attaching the component to a support that is configured to hold a plurality of components and placing a base of the support in a holder that is attached to rotatable member of a fixture, wherein an axis of the holder is parallel to an axis of rotation of the rotatable member. The method also includes transporting the fixture into a coating chamber wherein a direction of an exit stream of a coater in oriented perpendicularly to the axis of rotation, exposing the fixture and the component to a reverse transfer arc cleaning/pre-heating procedure, and exposing the fixture and the component to a coating procedure during which a coating is directed at the component in a direction perpendicular to the axis of rotation while the rotatable member is rotating. The method further includes transporting the fixture and removing the component from the support fixture. 1. A method of coating a component comprising:attaching the component to a support that is configured to hold a plurality of components attached lengthwise along the support;placing a base of the support in a holder that is attached to a rotatable member of a fixture, wherein an axis of the holder is parallel to an axis of rotation of the rotatable member;transporting the fixture with the component into a coating chamber wherein a direction of an exit stream of a coater is oriented perpendicularly to the axis of rotation of the rotatable member;exposing the fixture and the component to a reverse transfer arc cleaning procedure while the rotatable member is rotating at a first rotational angular velocity for a first time period during which the component is heated to a first temperature;exposing the fixture and the component to a coating procedure during which a coating is directed at the component in a direction perpendicular to the axis of the rotatable member while the rotatable member is rotating at a second angular velocity and is maintained at a second temperature for a ...

Oven wall compositions and/or structures

Techniques regarding the composition and/or structure of oven walls are provided. For example, one or more embodiments described herein can comprise an oven with a heat source configured to heat a hollow space within the oven. The oven further can comprise an oven body that can define the hollow space. Also, the oven body can comprising a plurality of connected sides, wherein one or more of the connected sides comprise a plurality of carbon nanotubes.

Panel burn through tolerant shell design

A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path.

Backside coating cooling passage

A component is provided for a gas turbine engine includes a substrate with an aperture. The component also includes a backside coating on a backside of the substrate and at least partially onto an inner boundary of the aperture, where the backside coating forms a passage with the aperture. A method of forming a shaped aperture in a component of a gas turbine engine is provided. The method includes applying a backside coating on a backside of a substrate and at least partially onto an inner boundary of an aperture. The backside coating forms a passage with the aperture including a convergent section, a divergent section and a throat therebetween.

Systems and Methods for Optimal Source Material Deposition Along Hole Edges

A method for depositing a coating of a source material onto a panel is disclosed. The method includes providing a cathodic arc, the cathodic arc including a target surface, the target surface disposed along a target deposition axis and able to emit the source material as a generally cloud of source material vapor and a generally conical stream of liquid particles of the source material. The method further includes positioning the panel relative to the target surface based on a deposition angle, the deposition angle being between the target surface and an outer limit of the generally conical stream of liquid particles o the source material. The method may further include emitting the source material from the target surface as the generally conical cloud of source material vapor and coating the edge with the cloud of source material vapor to provide an edge coating.

PANEL BURN THROUGH TOLERANT SHELL DESIGN

A dual wall liner for a gas turbine engine may comprise a shell having a first side and a second side, a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel, wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell. The TBC may thermally protect the shell from heat from a hot gas path. 1. A gas turbine engine combustor , comprising:a shell having a first side and a second side;a panel contacting the shell, the panel at least partially defining a hot gas path through which a hot gas flows, wherein the first side of the shell faces the panel;wherein the shell includes a thermal barrier coating (TBC) disposed on the first side of the shell.2. The gas turbine engine combustor of claim 1 , wherein the panel is coupled to the shell.3. The gas turbine engine combustor of claim 2 , further comprising a metallic layer in contact with the TBC.4. The gas turbine engine combustor of claim 3 , wherein:the shell is comprised of a shell material;the metallic layer is at least twice as resistant to oxidation as the shell material;the TBC comprises a lower thermal conductivity than that of the shell material; andthe TBC is disposed over the metallic layer.5. The gas turbine engine combustor of claim 2 , further comprising a heat transfer augmentation feature disposed on the second side of the shell claim 2 , wherein the heat transfer augmentation feature is configured to at least one of increase a surface area of the second side or disturb a flow of cooling air flowing across the second side.6. The gas turbine engine combustor of claim 2 , further comprising a panel stud coupling the panel to the shell claim 2 , wherein the TBC surrounds the panel stud.7. The gas turbine engine combustor of claim 2 , further comprising a plurality of holes extending through the shell and the TBC claim 2 , wherein the plurality of holes are ...

METHOD OF MANUFACTURING S-GLASS FIBERS IN A DIRECT MELT OPERATION AND PRODUCTS FORMED THEREFROM

A method of forming high strength glass fibers in a refractory-lined glass melter, products made there from and batch compositions suited for use in the method are disclosed. The glass composition for use in the method of the present invention is up to about 64-75 weight percent SiO, 16-24 weight percent AlO, 8-12 weight percent MgO and 0.25-3 weight percent RO, where RO equals the sum of LiO and NaO, has a fiberizing temperature less than about 2650° F., and a ΔT of at least 80° F. By using oxide-based refractory-lined furnaces the cost of production of glass fibers is substantially reduced in comparison with the cost of fibers produced using a platinum-lined melting furnace. High strength composite articles including the high strength glass fibers are also disclosed. 129-. (canceled)30. A high strength article comprising: [{'sub': '2', '64-75 weight percent SiO;'}, {'sub': 2', '3, '16-24 weight percent AlO;'}, '8-11 weight percent MgO;', {'sub': '2', '0.25-3 weight percent LiO; and'}, 'no more than 2.0 weight percent CaO; and, 'glass fibers formed from a glass batch composition comprisinga polymer matrix material, wherein said glass fibers have a strength of greater than about 700 KPsi.31. The high strength article of claim 30 , wherein the glass batch composition comprises:{'sub': 2', '3, '17-22 weight percent AlO;'}9-11 weight percent MgO; and{'sub': '2', '1.75-3 weight percent LiO.'}32. The high strength article of claim 30 , wherein the glass batch composition comprises:{'sub': '2', '68-69 weight percent SiO;'}{'sub': 2', '3, '20-22 weight percent AlO;'}9-10 weight percent MgO;{'sub': '2', '1-3 weight percent LiO; and'}no more than 2.0 weight percent CaO.33. The high strength article of claim 30 , wherein the glass batch comprises:{'sub': 2', '3', '2', '3', '2', '2', '3', '2', '2', '3, 'less than 5 weight percent total of compounds selected from the group consisting of PO, ZnO, ZrO, SrO, BaO, SO, F, BO, TiOand FeO.'}34. The high strength article of claim 30 , ...

ELECTRICAL AND THERMAL INSULATION FOR A COMBUSTION SYSTEM

An electrically enhanced combustor includes bilayer insulation. A thermal insulator protects an electrical insulator from high temperatures that could cause the electrical insulator to become at least somewhat electrically conductive. 1. A combustor , comprising:a furnace wall defining a combustion chamber configured to enclose a combustion reaction;a power supply configured to output a high voltage; anda charger operatively coupled to the power supply and to the combustion chamber and configured to receive the high voltage from the power supply and to cause the combustion reaction to carry a charge;wherein the furnace wall includes a conductive wall adjacent to an outside volume, a thermal insulator adjacent to the combustion chamber, and an electrical insulator disposed between the thermal insulator and the conductive wall.2. The combustor of claim 1 , wherein the thermal insulator is configured to thermally insulate the electrical insulator from the combustion volume; andwherein the electrical insulator is configured to electrically insulate the conductive wall from the thermal insulator and the combustion volume.3. The combustor of claim 1 , wherein the conductive wall defines a water jacket.4. The combustor of claim 1 , wherein the outside volume is accessible to a human during normal operation of the combustor.5. The combustor of claim 1 , wherein the electrical insulator includes steatite.6. The combustor of claim 1 , wherein the electrical insulator is configured as a plurality of continuous planes respectively held by gravity adjacent to the conductive wall.7. The combustor of claim 1 , wherein the electrical insulator is configured as a plurality of tiles.8. The combustor of claim 7 , wherein the electrical insulator is configured as a plurality of tiles with air gaps therebetween.9. The combustor of claim 1 , wherein the electrical insulator includes a vacuum.10. The combustor of claim 1 , wherein the electrical insulator includes air.11. The combustor of ...

Burn pit flare tip structure

A robust, thermally and structurally sound burn pit flare tip structure is disclosed of refractory brick construction capable of resisting the high temperature of 1800° C. and associated fluctuations. The burn pit is capable of prolonged continuous operation and reduces the previously experienced downtime and frequent failures.

SYSTEM AND METHOD FOR HIGH EFFICIENCY POWER GENERATION USING A CARBON DIOXIDE CIRCULATING WORKING FLUID

The present invention provides methods and system for power generation using a high efficiency combustor in combination with a COcirculating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle COcirculating fluid. Fuel derived COcan be captured and delivered at pipeline pressure. Other impurities can be captured. 14-. (canceled)5. A method of power generation comprising:{'sub': '2', 'expanding a compressed recycle COstream at a pressure of at least about 12 MPa across a series of a first turbine and a last turbine over a pressure ratio of at least about 20 so as to output from the last turbine a last turbine discharge stream;'}heating a discharge stream from the first turbine prior to passage into the last turbine in a combustor by combusting a hydrocarbon or carbonaceous fuel in the presence of an oxidant and the first turbine discharge stream so as to form a combustor exhaust stream at a pressure of at least about 10 MPa and a temperature of at least about 800° C.;cooling the last turbine discharge stream in a recuperator heat exchanger;{'sub': 2', '2, 'isolating at least a portion of COfrom the cooled turbine discharge stream to form the recycle COstream;'}{'sub': '2', 'compressing the recycle COstream; and'}{'sub': '2', 'passing the recycle COstream to the series of turbines.'}6. The method of claim 5 , wherein last turbine discharge stream is at a pressure of less than about 0.15 MPa.7. The method of claim 5 , wherein the compressing comprises passing the recycle COstream through a multistage compressor that compresses the recycle COstream to a pressure of at least about 5.75 MPa and then through a pump that increases the pressure to at least about 12 MPa.8. The method of claim 7 , wherein multistage compressor comprises a first ...

COMBUSTOR PANEL MOUNTING SYSTEMS AND METHODS

Combustors of gas turbine engines having a combustor shell having a first end and a second end opposite the first end, a first securing element positioned at the first end of the combustor shell, a second securing element positioned at the second end of the combustor shell, a plurality of high temperature material panels fixedly secured by the first securing element at the first end and the second securing element at the second, wherein a panel gap is formed between edges of adjacent high temperature material panels of the plurality of high temperature material panels, and a seal divider extending from the first end to the second end and positioned on the combustor shell and arranged to seal the panel gap between adjacent first and second high temperature material panels. 1. A combustor of a gas turbine engine comprising:a combustor shell having a first end and a second end opposite the first end;a first securing element positioned at the first end of the combustor shell;a second securing element positioned at the second end of the combustor shell;a plurality of high temperature material panels fixedly secured by the first securing element at the first end and the second securing element at the second, wherein a panel gap is formed between edges of adjacent high temperature material panels of the plurality of high temperature material panels; anda seal divider extending from the first end to the second end and positioned on the combustor shell and arranged to seal the panel gap between adjacent first and second high temperature material panels.2. The combustor of claim 1 , further comprising a plurality of biasing elements located away from the edges of the high temperature material panels claim 1 , the biasing elements biasing the high temperature material panels to secure engagement with the first and second securing elements.3. The combustor of claim 2 , wherein the biasing elements are integrally formed from the combustor shell.4. The combustor of claim 2 , ...

Calcium-magnesium alumino-silicate (cmas) resistant thermal barrier coatings, systems, and methods of production thereof

The thermal barrier coating includes reactive gadolinia in its microstructures and the embedded gadolinia effectively reacts with CMAS contaminant reducing the damage from CMAS. Moreover, a method to produce a CMAS resistant thermal barrier coating can include a post-treatment to the thermal barrier coating with the reactive gadolinia suspension in sol-gel state.

METHOD FOR OBTAINING A CONFIGURATION FOR JOINING A CERAMIC MATERIAL TO A METALLIC STRUCTURE

A configuration for joining a ceramic layer has a thermal insulating material to a metallic layer. The configuration includes an interface layer made of metallic material located between the ceramic layer and the metallic layer, which includes a plurality of interlocking elements on one of its sides, facing the ceramic layer, the ceramic layer comprising a plurality of cavities aimed at connecting with the corresponding interlocking elements of the interface layer. The configuration also includes a brazing layer by means of which the interface layer is joint to the metallic layer. The invention also refers to a method for obtaining such a configuration. 1. A material for joining a ceramic layer comprising a thermal insulating material to a metallic layer , an interface layer made of metallic material located between the ceramic layer and the metallic layer , having a plurality of interlocking elements on one of its sides , facing the ceramic layer , the ceramic layer including a plurality of cavities aimed at connecting with the corresponding interlocking elements of the interface layer , and a brazing layer by means of which the interface layer is joint to the metallic layer.2. The material according to claim 1 , wherein the plurality of cavities in the ceramic layer are filled with metallic filler claim 1 , protruding from the ceramic layer claim 1 , such that metallic struts are formed.3. The material according to claim 2 , further comprising a defined gap between the ceramic layer together with the interface layer claim 2 , with respect to the metallic layer claim 2 , the cited gap being defined by selecting the length of the interlocking elements to define the metallic struts between the ceramic layer and the interface layer.4. The material according to claim 1 , wherein the interface layer comprises a plurality of near wall cooling channels claim 1 , the ceramic layer and the interface layer with the cooling channels being further brazed to the metallic layer. ...

SYSTEM AND METHOD FOR HIGH EFFICIENCY POWER GENERATION USING A CARBON DIOXIDE CIRCULATING WORKING FLUID

The present invention provides methods and system for power generation using a high efficiency combustor in combination with a COcirculating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle COcirculating fluid. Fuel derived COcan be captured and delivered at pipeline pressure. Other impurities can be captured. 1107-. (canceled)108. A method comprising:compressing a stream comprising carbon dioxide to a pressure of at least about 8 MPa to form a stream of compressed carbon dioxide;delivering at least a portion of the compressed carbon dioxide to a combustor;delivering an oxidant to the combustor;delivering a fuel to the combustor;combusting the fuel in the combustor with the oxidant in the presence of the compressed carbon dioxide to form a combustion exhaust stream at a pressure of at least about 8 MPa; andexpanding the combustion exhaust stream across a turbine to generate power and form an expanded combustion exhaust stream;wherein the compressed carbon dioxide, the oxidant, and the fuel are delivered to the combustor in ratios such that the combustion exhaust stream comprises an excess of oxygen.109. The method of claim 108 , wherein the oxidant and the fuel are delivered to the combustor in a ratio so that the amount of oxygen is in excess of the stoichiometric amount necessary to achieve complete combustion of the fuel.110. The method of claim 109 , wherein the amount of oxygen is in excess of the stoichiometric amount by at least about 0.25% molar.111. The method of claim 109 , wherein the amount of oxygen is in excess of the stoichiometric amount by at least about 1% molar.112. The method of claim 109 , wherein the amount of oxygen is in excess of the stoichiometric amount by at least about 5% molar.113. The method of claim 108 ...

Coated susceptor for a high-temperature furnace and furnace comprising such a susceptor

A high-temperature furnace (10) with a wall (1) or chamber defining an inner zone (8), said wall (1) or chamber comprising a refractory material, characterized in that said refractory material comprises molybdenum or a molybdenum compound being protected against oxygen in said inner zone (8) by means of a protective Silicon-Boron (Si-B) coating. Preferably the molybdenum has a purity of at least 99% and acts as a susceptor during induction heating. The furnace can be used for the treatment of waste, biomass, the roasting of ores or minerals, or the conversion of organic materials into synthetic gas.

High-temperature furnace with an oxygen-free infeed section and use of such a furnace

High-temperature furnace (10) for processing carbon-containing material such as biomass or waste in an inner zone (8) at a high-temperature. The furnace (10) comprises an in-feed side (20) for continuously feeding said carbon-containing material into said inner zone (8) and an output side (30) where a Syngas is provided. The infeed side (20) comprises an infeed section (23) providing for an atmosphere being essentially oxygen-free. There is gas inlet (22.1) at the infeed section (23) which is connected to the output side (30) with a feedback pipe for feeding some of said Syngas into said infeed section (23). The syngas provides preheating of the material and reduces corrosion risk in the high temperature zone.

Integral ceramic matrix composite fastener with non-polymer rigidization

A method of forming an integral fastener for a ceramic matrix composite component comprises the steps of forming a fiber preform with an opening, forming a fiber fastener, inserting the fiber fastener into the opening, and infiltrating a matrix material into the fiber preform and fiber fastener to form a ceramic matrix composite component with an integral fastener. A gas turbine engine is also disclosed.

Теплоизолированный высокотемпературный реактор

Изобретение может быть использовано в химической промышленности. Высокотемпературный реактор имеет кожух 1, внутри которого находится слой внешней теплоизоляции 2 и внутренней теплоизоляции 3, образованной высокотемпературным теплоизоляционным материалом, свободно уложенным слоями. Внутренняя теплоизоляция 3 рассчитана на теплопроводность от 0,14 до 0,5 Вт/мК при температурах до 1600°С. Для компенсации теплового расширения предусмотрены зазор 5 вверху и зазор 7 между внутренним и внешним слоями теплоизоляции. 16 з.п. ф-лы, 2 ил. ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß RU (19) (11) 2 346 737 (13) C2 (51) ÌÏÊ B01J 19/02 (2006.01) ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÎÏÈÑÀÍÈÅ ÈÇÎÁÐÅÒÅÍÈß Ê ÏÀÒÅÍÒÓ (21), (22) Çà âêà: 2005138146/15, 22.04.2004 (30) Êîíâåíöèîííûé ïðèîðèòåò: 09.05.2003 DE 10320966.2 (73) Ïàòåíòîîáëàäàòåëü(è): ËÈÍÄÅ ÀÊÖÈÅÍÃÅÇÅËÜØÀÔÒ (DE) (43) Äàòà ïóáëèêàöèè çà âêè: 20.06.2007 R U (24) Äàòà íà÷àëà îòñ÷åòà ñðîêà äåéñòâè ïàòåíòà: 22.04.2004 (72) Àâòîð(û): ÌÓØÅËÜÊÍÀÓÒÖ Çåáàñòèàí (DE), ÐÀÍÊÅ Õàðàëüä (DE), ÒÀÓÒÖ Õàííî (DE) (45) Îïóáëèêîâàíî: 20.02.2009 Áþë. ¹ 5 2 3 4 6 7 3 7 2 3 4 6 7 3 7 R U (85) Äàòà ïåðåâîäà çà âêè PCT íà íàöèîíàëüíóþ ôàçó: 09.12.2005 C 2 C 2 (56) Ñïèñîê äîêóìåíòîâ, öèòèðîâàííûõ â îò÷åòå î ïîèñêå: US 2002182132 A1, 05.12.2002. US 5407455 A, 18.04.1995. US 4770930 A, 13.09.1988. US 2002129751 A1, 19.09.2002. US 1888039 A, 15.11.1932. RU 2091352 C1, 29.09.1997. SU 351247 A1, 13.09.1972. ÊÅÐÀÌÈÊÀ È ÎÃÍÅÓÏÎÐÛ. Ñáîðíèê ïåðåâîäîâ èç èíîñòðàííîé ïåðèîäè÷åñêîé ëèòåðàòóðû/ Ïîä ðåä. Áóäíèêîâà Ï.Ï. è ×åðåïàíîâà A.M. - Ì.: Èíîñòðàííà ëèòåðàòóðà, 1963, ñ.191-199. (86) Çà âêà PCT: EP 2004/004282 (22.04.2004) (87) Ïóáëèêàöè PCT: WO 2004/098770 (18.11.2004) Àäðåñ äë ïåðåïèñêè: 101000, Ìîñêâà, Ì.Çëàòîóñòèíñêèé ïåð., 10, êâ.15, "ÅÂÐÎÌÀÐÊÏÀÒ", ïàò.ïîâ. Ð.À.Êàêñèñó, ðåã.¹ 899 (54) ÒÅÏËÎÈÇÎËÈÐÎÂÀÍÍÛÉ ÂÛÑÎÊÎÒÅÌÏÅÐÀÒÓÐÍÛÉ ÐÅÀÊÒÎÐ (57) Ðåôåðàò: Èçîáðåòåíèå ìîæåò áûòü èñïîëüçîâàíî â õèìè÷åñêîé ïðîìûøëåííîñòè. Âûñîêîòåìïåðàòóðíûé ðåàêòîð ...

裂解炉

本发明涉及裂解炉(1)，所述裂解炉(1)包括垂直管状封闭体(2)，所述封闭体(2)包括用于引入待处理气体的入口(4)和用于从腔体去除所述气体的出口(5)；所述器件包括在腔室内垂直延伸并与腔室同轴的加热管(9)，所述加热管(9)形状设置为具有封闭的底端，并且对所述加热管(9)进行设置以使得其底端设置在腔室中并且其顶端连接到加热器件的燃烧器(13)，所述燃烧器(13)设置在腔体的外部。本发明还涉及包括该裂解炉以及用于对生物质和/或废料进行热处理且其出口连接到所述裂解炉的入口的装置的组件。

Cracking furnace

Ring combustion chamber

FIELD: combustion. SUBSTANCE: ring combustion chamber comprises two heads shifted one with respect to the other, starting head provided with nozzle systems, and launching head provided with nozzle systems. The launching head is shifted radially and axially with respect to the starting head. The starting head is provided with at least N identical nozzle systems. The total flow through the starting fuel nozzle ranges from 10% to 40% of the total flow of air entering the combustion chamber. The total flow through the launching nozzles ranges from 30% to 70% of the total flow of air entering the combustion chamber. EFFECT: expanded functional capabilities. 13 cl, 3 dwg ÐÎÑÑÈÉÑÊÀß ÔÅÄÅÐÀÖÈß (19) RU (11) 2 296 917 (13) C2 (51) ÌÏÊ F23R 3/28 (2006.01) ÔÅÄÅÐÀËÜÍÀß ÑËÓÆÁÀ ÏÎ ÈÍÒÅËËÅÊÒÓÀËÜÍÎÉ ÑÎÁÑÒÂÅÍÍÎÑÒÈ, ÏÀÒÅÍÒÀÌ È ÒÎÂÀÐÍÛÌ ÇÍÀÊÀÌ (12) ÎÏÈÑÀÍÈÅ ÈÇÎÁÐÅÒÅÍÈß Ê ÏÀÒÅÍÒÓ (21), (22) Çà âêà: 2002123305/06, 27.08.2002 (72) Àâòîð(û): ÁÎÄÓÀÍ Êðèñòîô (FR), ÊÎÌÌÀÐÅ Ïàòðèñ-Àíäðå (FR), ËÅ ËÅÒÒÈ Ýðèê (FR), ÂÈÃÜÅ Êðèñòîô (FR) (24) Äàòà íà÷àëà îòñ÷åòà ñðîêà äåéñòâè ïàòåíòà: 27.08.2002 (73) Ïàòåíòîîáëàäàòåëü(è): ÑÍÅÊÌÀ ÌÎÒÎÐÑ (FR) (43) Äàòà ïóáëèêàöèè çà âêè: 10.03.2004 R U (30) Êîíâåíöèîííûé ïðèîðèòåò: 28.08.2001 FR 0111190 (45) Îïóáëèêîâàíî: 10.04.2007 Áþë. ¹ 10 2 2 9 6 9 1 7 (56) Ñïèñîê äîêóìåíòîâ, öèòèðîâàííûõ â îò÷åòå î ïîèñêå: FR 2727193 A1, 24.05.1996. US 5642621 A, 01.07.1997. US 4498288 A, 12.02.1985. EP 04554871 A1, 06.11.1991. RU 2083926 C1, 10.07.1997. RU 1002736 A2, 10.05.1996. ÎÒÍÎØÅÍÈÞ ÄÐÓÃ Ê ÄÐÓÃÓ (57) Ðåôåðàò: Êîëüöåâà êàìåðà ñãîðàíè àâèàöèîííîãî ãàçîòóðáèííîãî äâèãàòåë îñíàùåíà äâóì ãîëîâêàìè, êîòîðûå ñìåùåíû ïî îòíîøåíèþ äðóã ê äðóãó, è ñîäåðæèò ïóñêîâóþ ãîëîâêó, èìåþùóþ íåñêîëüêî ôîðñóíî÷íûõ ñèñòåì, è âçëåòíóþ ãîëîâêó, òàêæå èìåþùóþ íåñêîëüêî ôîðñóíî÷íûõ ñèñòåì. Âçëåòíà ãîëîâêà ñìåùåíà ðàäèàëüíî è ïî îñè îò ïóñêîâîé ãîëîâêè. Ïóñêîâà ãîëîâêà ñíàáæåíà, ïî ìåíüøåé ìåðå, êîëè÷åñòâîì N ïî ñóùåñòâó èäåíòè÷íûõ ôîðñóíî÷íûõ ñèñòåì ñóììàðíîé ïðîïóñêíîé ñïîñîáíîñòüþ ÐÀ è ...

Burner component and burner with aluminium oxide coating and method of component coating application

FIELD: power industry. SUBSTANCE: burner component (10, 12, 18) is characterised by the fact that its surface contacting fuel (23) is coated with aluminium oxide coating (21), at that aluminium oxide coating (21) contains α-Al 2 O 3 , and this aluminium oxide coating (21) is a layer of aluminium oxide. Coating contains the first layer (20) rich with aluminium and the second layer containing aluminium oxide (21) which is located above the first layer (20). Coating has layer thickness (22) from 50 mcm up to 100 mcm. Burner component (10, 12, 18) contains steel of 16Mo3 grade as basic material. Burner component (10, 12, 18) is used for fuel delivery or distribution. EFFECT: invention allows quality improvement of fuel combustion, improvement of burner operating reliability. 19 cl, 7 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 447 361 (13) C2 (51) МПК F23D 11/36 (2006.01) F23M 5/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2010125614/06, 03.03.2008 (24) Дата начала отсчета срока действия патента: 03.03.2008 (73) Патентообладатель(и): СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) (43) Дата публикации заявки: 27.12.2011 Бюл. № 36 2 4 4 7 3 6 1 (45) Опубликовано: 10.04.2012 Бюл. № 10 (56) Список документов, цитированных в отчете о поиске: SU 1477932 A1, 07.05.1989. EP 1217095 A1, 26.06.2002. WO 2006/058629 A1, 08.06.2006. RU 2178530 C2, 20.01.2002. RU 2228389 C2, 10.05.2004. 2 4 4 7 3 6 1 R U (86) Заявка PCT: EP 2008/052556 (03.03.2008) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 23.06.2010 (87) Публикация заявки РСТ: WO 2009/065625 (28.05.2009) Адрес для переписки: 129090, Москва, ул. Б.Спасская, 25, стр.3, ООО "Юридическая фирма Городисский и Партнеры", пат.пов. Ю.Д.Кузнецову, рег.№ 595 (54) ЭЛЕМЕНТ ГОРЕЛКИ И ГОРЕЛКА С ПОКРЫТИЕМ ИЗ ОКСИДА АЛЮМИНИЯ И СПОСОБ ПОКРЫТИЯ ЭЛЕМЕНТА ГОРЕЛКИ содержащее оксид алюминия покрытие является слоем (21) оксида алюминия. Покрытие содержит богатый алюминием ...

Reactor design to reduce particle deposition during process abatement

本发明提供当减少不希望的反应产物在处理系统中沉积时，一种用于气态污染物的控制燃烧与分解的系统与方法。典型的系统包含一个新颖的热反应室设计，其具有堆栈的有孔陶瓷环，例如气体的流体可以被导入堆栈的有孔陶瓷环以沿着此热反应室的内壁而形成一边界层，借此减少颗粒物在其上的累积。系统可还包含导入来自中央喷口的流体以改变此热反应室内部的空气动力学。

Patent JPH0531236B2

Two-level layer system with pyrochlore phase and oxides

There is described a two-Level Layer System with Pyrochlore Phase and Oxides. Besides a good thermal insulation property, thermal insulation layer systems must also have a long lifetime of the thermal insulation layer. The layer system has a layer sequence of a metallic bonding layer, an inner ceramic layer and an outer ceramic layer, which are specially matched to one another.

Ceramic compositions for thermal barrier coatings with improved mechanical properties

Zirconia-containing ceramic compositions useful for thermal barrier coatings having improved mechanical properties, especially improved fracture toughness. These compositions comprise: (1) at least about 93 mole % zirconia; (2) a stabilizing amount up to about 5 mole % of a stabilizer metal oxide selected from the group consisting of yttria, calcia, ceria, scandia, magnesia, india, gadolinia, neodymia, samaria, dysprosia, erbia, ytterbia, europia, praseodymia, and mixtures thereof, and a fracture toughness improving amount up to about 2 mole % lanthana. These ceramic compositions can be used to prepare thermal barrier coatings to provide a thermally protected article having a substrate and optionally a bond coat layer adjacent to and overlaying the substrate. The thermal barrier coating can be prepared by depositing the ceramic composition on the bond coat layer or the substrate in the absence of a bond coat layer.

Single crystal articles having controlled crystallographic orientation

An article has a characteristic thermal-mechanical stress principal direction. The article has a single crystal substrate having a lowest modulus direction within a target alignment with the principal direction.

Burner Element and Burner Having Aluminum Oxide Coating and Method for Coating a Burner Element

A burner element is provided. The burner element includes a surface that potentially comes into contact with a fuel. The surface potentially coming into contact with the fuel has a coating including aluminum oxide. A burner including the burner element is also provided. Further, a method for coating a surface of a burner element potentially coming into contact with a fuel is described, wherein the surface potentially coming into contact with the fuel is coated with aluminum oxide.

Calcium-magnesium alumino-silicate (cmas) resistant thermal barrier coatings, systems, and methods of production thereof

The thermal barrier coating includes reactive gadolinia in its microstructures and the embedded gadolinia effectively reacts with CMAS contaminant reducing the damage from CMAS. Moreover, a method to produce a CMAS resistant thermal barrier coating can include a post-treatment to the thermal barrier coating with the reactive gadolinia suspension in sol-gel state.

Single crystal articles having controlled crystallographic orientation

An article has a characteristic thermal-mechanical stress principal direction. The article has a single crystal substrate having a lowest modulus direction within a target alignment with the principal direction.

Ceramic layer having high porosity, use of this layer and component comprising such a layer

Ceramic layer (10) with a pore exhibits a pore cross-section of greater than 6000 mu m 2>to 9000 mu m 2>. An independent claim is included for a device (1) comprising the ceramic layer.

Process for in situ coating of turbo-machine components

A method for coating a component of a turbo-machine. The method allows arranging a turbine rotor in the turbo-machine and introducing a coating material into the interior of the turbo-machine such that the rotor is coated. The rotor is rotated while it is being coated.

Layer system, use and process for producing a layer system

Layered systems, which are used at high temperatures, often degrade rapidly when a layer has been lost, leading to the damage or loss of the component that consists of said layered system. A described layered system comprises at least one cooling safety orifice, which is e.g. covered by an intermediate layer and an outer layer. The cooling safety orifice opens if the layers are damaged, in such a way that the layered system is additionally cooled by a coolant that flows through the cooling safety orifice.

Surface with specially formed depressions and component

The surface (19) has elongated recesses (4) including a longitudinal direction and present under an angle of about 110 degree or 70 degree. The recesses are arranged at an overtopping direction over the surface. The recesses are partially enlarged transverse to the longitudinal direction in an area of the surface opposite to a base (16). Each recess includes a front edge (25) and a rear edge (28), where the enlargement is formed at an outflow-sided end of the rear edge. The enlargement exhibits larger cross-section against the base. An independent claim is also included for a massive component.

Ceramic thermal insulation coating on structured surface and production method

The layer system comprises a substrate (4), and a ceramic layer (16) that is applied on a structured surface. The structured surface is formed by elongated recesses that form a honeycomb structure, and a stitch structure in quadratic or rectangular shape and have a breadth of 10-30 mu m and a depth of 10-30%. The ceramic layer has a thickness of 10-30 mu m. A distance of the opposite recesses is 100-300 mu m. The layer system further comprises an interfacial layer (10) such as a metallic layer made of chromium-aluminum (MCrAlX) alloy, where the interfacial layer is introduced into the recesses. An independent claim is included for a method for preparing a layer system.

Non-flaking ceramic coat and coating system

The ceramic layer (17) has longitudinal coating tracks (4',4",44",7',7",77") that are provided with several coating layers (22',22",22). The coating layers are made of different materials such as zirconium oxide, yttria, pyrochlore, and gadolinium.

Ceramic heat shields with infiltration coating

Die Erfindung führt einen verbesserten keramischen Hitzeschild (155) für eine Gasturbine (100) ein. Der keramische Hitzeschild (155) verfügt über einen porösen Keramikkörper (11) und weist erfindungsgemäß ein Infiltrationscoating (12) auf, das in einer Oberflächenschicht (12) des porösen Keramikkörpers (11) angeordnet ist und ein Infiltrationscoatingmaterial enthält, das dazu ausgebildet ist, Poren des Keramikkörpers (11) gasdicht zu verschließen. The invention introduces an improved ceramic heat shield (155) for a gas turbine (100). The ceramic heat shield (155) has a porous ceramic body (11) and, according to the invention, has an infiltration coating (12) disposed in a surface layer (12) of the porous ceramic body (11) and containing an infiltration coating material adapted to form pores of the ceramic body (11) to close gas-tight.

Ceramic element or ceramic layer having high porosity, their use and ceramic element comprising said layer

The ceramic massive component or ceramic layer useful for the application at high temperature of >= 1200[deg] C for the component of steam turbine or gas turbine, where the massive component or ceramic layer has a porosity of 26 vol.%, a hardness of 630 HV(0.3), a pore cross-section of 9000-12000 mu m 2>, and a layer thickness of greater than 1500 mu m, is claimed. An independent claim is included for a component such as steam turbine or gas turbine.

Surface having specially formed recesses and component

Due to the special asymmetrical shape in a recess (4) of a ceramic surface (19), thermomechanically induced stresses in the ceramic can be better reduced during the operation of a component, and thus the crack propagation and the subsequent flaking of the ceramic layer from the component can be reduced and even prevented. The aerodynamics of the cooling air flow in the area of said geometries of the recesses proposed herein are likewise improved.

Process for producing a layer system

A process for producing a layer system is provided wherein the layer system has at least a substrate, a ceramic layer, which is applied to a surface structured in a targeted manner, in which process the intermediate layer, in particular the metallic layer, is applied in such a way that the recesses form during the coating. By introducing recesses into a surface, the stresses in the ceramic layer on the metallic substrate are reduced in such a manner that a longer lifespan for the ceramic layer is achieved.

Production method for a coating system

Durch die Einbringung von Vertiefungen (19', 19'',...) in eine Oberfläche (7, 13) werden die Spannungen in der keramischen Schicht (16) an den metallischen Untergrund reduziert, so dass eine längere Lebensdauer für die keramische Schicht erzielt wird.

Ceramic heat shields having surface infiltration for preventing corrosion and erosion attacks

The invention relates to an improved ceramic heat shield (155) for a gas turbine (100). The ceramic heat shield (155) has a porous ceramic body (11) and according to the invention an infiltration coating (12) that is provided in a surface layer (12) of the porous ceramic body (11) and contains an infiltration coating material designed to gas-tightly seal pores of the ceramic body (11).

Ceramic heat shields having surface infiltration for preventing corrosion and erosion attacks

An improved ceramic heat shield for a gas turbine is provided. The ceramic heat shield has a porous ceramic body and according to the embodiments an infiltration coating that is provided in a surface layer of the porous ceramic body and contains an infiltration coating material designed to gas-tightly seal pores of the ceramic body.

Method of coating a component inside an apparatus

Method for coating a component (10) of a device (1) with a turbo-engine comprises feeding the coating material (13) into the inside of the device whilst the component to be coated is located inside the device to coat the inside of the component.

Coating system, use and method of manufacturing such a coating system

A layer system (1) comprises a substrate (4) and at least one layer (10). A safety cooling hole (13) is located in the substrate and is blocked at one end by the layer. The layer is a ceramic heat insulating layer.

Alloy, protective coating to protect a part against corrosion and/or oxidation at high temperatures and component

Nickel alloy containing the following elements (wt.%) is new: chromium (27-29), aluminum (7-16), yttrium, scandium or rare earth metal (0.5-0.7), rhenium (0-11) and silicon (0-2). Independent claims are also included for: (a) protective layer for protecting a component against corrosion and/or oxidation, comprising an alloy as above; (b) component with a protective layer as above for protection against corrosion and/or oxidation at high temperatures.

Composition to make fire-resistant material

FIELD: construction. SUBSTANCE: composition to make a fire-resistant material contains coarse grain in amount of more than 50 wt % and fine grain. Coarse grain contains grains with size of more than 20 mcm, and fine grain contains grains with size of less than 20 mcm. Fine grain contains magnesia-aluminious spinel and/or baked spinel and/or molten spinel and zirconium oxide. Amount of magnesia-aluminous spinel in fine grain makes from 70 to 88 wt %, and the amount of zirconium oxide in fine grain makes from more than 12 to 30 wt %. EFFECT: invention will make it possible to increase durability of a fire-resistant item. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 478 874 (13) C2 (51) МПК F23M 5/00 (2006.01) F23R 3/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2011117311/06, 21.09.2009 (24) Дата начала отсчета срока действия патента: 21.09.2009 (73) Патентообладатель(и): СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) (43) Дата публикации заявки: 10.11.2012 Бюл. № 31 2 4 7 8 8 7 4 (45) Опубликовано: 10.04.2013 Бюл. № 10 (56) Список документов, цитированных в отчете о поиске: DE 10054125 A1, 23.05.2002. EP 1072573 A1, 31.01.2001. DE 2745461 B1, 29.03.1979. SU 687048 A1, 25.09.1979. SU 900089 A1, 23.01.1982. RU 2178530 C2, 20.01.2002. 2 4 7 8 8 7 4 R U (86) Заявка PCT: EP 2009/062172 (21.09.2009) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 29.04.2011 (87) Публикация заявки РСТ: WO 2010/034680 (01.04.2010) Адрес для переписки: 109012, Москва, ул. Ильинка, 5/2, ООО "Союзпатент", пат.пов. О.И.Воль, рег.№ 1101 (54) КОМПОЗИЦИЯ ДЛЯ ПОЛУЧЕНИЯ ОГНЕУПОРНОГО МАТЕРИАЛА (57) Реферат: Композиция для получения огнеупорного материала содержит крупную фракцию в количестве более 50 мас.% и мелкую фракцию. Крупная фракция состоит из зерен размером более 20 мкм, а мелкая фракция состоит из зерен размером менее 20 мкм. Мелкая фракция содержит магнезиально-глиноземистую шпинель и/или спеченную шпинель и/или плавленую ...

Method of producing high-strength glass fibre and articles moulded therefrom

FIELD: chemistry. SUBSTANCE: fibre is obtained in a glass-melting furnace which is free of platinum or other noble metal-based materials. One of the compositions for making fibre includes, wt %: 50 to 75 SiO 2 ; 15 to 30 Al 2 O 3 ; 5 to 20 MgO; 0 to 10 CaO; and 0 to 5 R 2 O, where R 2 O equals the sum of Li 2 O, Na 2 O and K 2 O. The composition has a higher fibre formation temperature of 2400°F (1316°C) to 2900°F (1593°C), and/or a liquid phase temperature lower than the fibre formation temperature of 45°F (25°C). Another composition includes, wt %: 64 to 75 SiO 2 ; 16 to 24 Al 2 O 3 ; 8 to 12 MgO; and 0.25 to 3 R 2 O, where R 2 O equals the sum of Li 2 O, Na 2 O and K 2 O, and has fibre formation temperature lower than 2650°F (1454°C) and °ΔT of not less than 80°F (45°C). EFFECT: producing high-quality fibres in furnaces and feed channels free of platinum and other noble metal-based materials, and low cost of producing glass fibres. 18 cl, 7 dwg, 4 tbl РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК C03C 3/087 (13) 2 531 950 C2 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2011126891/03, 21.12.2009 (24) Дата начала отсчета срока действия патента: 21.12.2009 Приоритет(ы): (30) Конвенционный приоритет: (43) Дата публикации заявки: 27.01.2013 Бюл. № 3 (73) Патентообладатель(и): ОСВ ИНТЕЛЛЕКЧУАЛ КЭПИТАЛ, ЭлЭлСи (US) (56) Список документов, цитированных в отчете о поиске: US 2007/105701 A1, 10.05.2007 . US 2003/188554 A1, 09.10.2003. US 5851932 A, 22.12.1998. WO 2007/055968 A2, 18.05.2007. WO 99/31021 A1, 24.06.1999 . RU 2167835 C1, 27.05.2001 (86) Заявка PCT: C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 22.07.2011 US 2009/068965 (21.12.2009) (87) Публикация заявки PCT: 2 5 3 1 9 5 0 WO 2010/075267 (01.07.2010) R U 2 5 3 1 9 5 0 (45) Опубликовано: 27.10.2014 Бюл. № 30 R U 22.12.2008 US 12/341,985; 13.03.2009 US 12/403,955 (72) Автор(ы): МАКГИННИС Питер Бернард (US), ХОФМАНН ...

Combustion liner

本发明涉及一种燃烧器衬套。提供了一种其内限定了燃烧区的燃烧器，且该燃烧器包括：环形衬套，其具有在第一轴向位置处限定于其中的第一混合孔；流动套管，其具有在第二轴向位置处限定于其中的第二混合孔，该流动套管包围衬套，以在该衬套的外部形成第一流动空间；端口，其在第二轴向位置处联接到流动套管上，该端口构造成经由第二混合孔从第一流动空间移除空气；以及罩，其具有在第二轴向位置处限定于其中的第三混合孔，该罩设置成防护衬套且在该衬套内形成第二流动空间，第二流动空间可经由第三混合孔与燃烧区连通且可经由第一混合孔与第一流动空间连通。

Material and system of layers

FIELD: metallurgy. ^ SUBSTANCE: invention can be implemented at high temperature installations, for example in turbine blades, thermo-protecting components, gas or steam turbine case elements and also in blades of gas turbine compressor. Material for a structure component or for a layer consists of material of a matrix and particle (1) with nucleus (7) containing the first element or the first compound, and of at least one shell (4) around nucleus (7) containing the second element or the second compound. Material of the matrix corresponds to an alloy of MCrAlX type, the first element or the first composition of which consists of metal, metal oxide, non-metal oxide, glass or Si-O-C-compound or their mixture and of at least one shell (4', 4", 4'") made of ceramic, in particular of metal oxide. ^ EFFECT: more long-term protection against oxidation and corrosion. ^ 36 cl, 1 tbl, 9 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 395 624 (13) C2 (51) МПК C23C 28/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21), (22) Заявка: 2007140252/02, 30.01.2006 (24) Дата начала отсчета срока действия патента: 30.01.2006 (43) Дата публикации заявки: 10.05.2009 2 3 9 5 6 2 4 R U (85) Дата перевода заявки PCT на национальную фазу: 31.10.2007 C 2 C 2 (56) Список документов, цитированных в отчете о поиске: WO 02/081868 A1, 17.10.2002. EP 0499656 A1, 26.08.1992. JP 10-195547 A, 28.07.1998. АБРАИМОВ Н.В. и др. Химико-термическая обработка жаропрочных сталей и сплавов. М.: Интермет Инжиниринг, 2001, с.266, 273274. (86) Заявка PCT: EP 2006/050506 (30.01.2006) (87) Публикация PCT: WO 2006/103127 (05.10.2006) Адрес для переписки: 129090, Москва, ул.Б.Спасская, 25, стр.3, ООО "Юридическая фирма Городисский и Партнеры", пат.пов. А.В.Мицу, рег.№ 364 (54) МАТЕРИАЛ И СИСТЕМА СЛОЕВ (57) Реферат: Изобретение может быть использовано в высокотемпературных установках, например в лопатках турбины, теплозащитных ...

Indirect-fired, all ceramic pyrochemical reactor

The present invention is directed to an indirect-fired, stationary tube, gas/solids or solids/solids, full ceramic pyroprocessing furnace-reactor that uses heat-resistant conveyors to propel solids through the stationary tube.

Slurry for casting under pressure and made of refractory ceramics for gas-turbine plants

FIELD: metallurgy. SUBSTANCE: invention relates to slurry for casting under pressure for production of refractory ceramics for use as thermal protection shield in gas turbine plants high temperature loop. Slurry contains mixture of grains of at least two materials with different thermal expansion factors, as well as xanthan as organic binder and thickener. Grain mixture has multimodal grains distribution by size, which looks as follows: 10–20 wt% of large-size grains with diameter of 1–5 mm, 10–20 wt% of average size grains with diameter of 0.5–1 mm and 60–80 wt% of small-sized grains with diameter of up to 0.5 mm. Distribution of grains by weight is selected such that total quantity of grains in mixture makes 100 wt%, and average size grains fraction at least by 20% consists of material with much low expansion factor. EFFECT: technical effect consists in making refractory ceramics with high resistance to thermal shock. 6 cl, 1 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 606 739 C2 (51) МПК C04B 35/636 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ФОРМУЛА (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ 2014109925, 01.08.2012 (24) Дата начала отсчета срока действия патента: 01.08.2012 Дата регистрации: Приоритет(ы): (30) Конвенционный приоритет: 16.08.2011 EP 11177668.8 (73) Патентообладатель(и): СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) (56) Список документов, цитированных в отчете о поиске: EP 2168935 A1, 31.03.2010. SU (45) Опубликовано: 10.01.2017 Бюл. № 1 749816 A, 23.07.1980. EP 2329195 A1, 08.06.2011. RU 2267469 C1, 10.01.2006. RU 2122534 C1, 27.11.1998. (85) Дата начала рассмотрения заявки PCT на национальной фазе: 17.03.2014 (86) Заявка PCT: EP 2012/065002 (01.08.2012) (87) Публикация заявки PCT: 2 6 0 6 7 3 9 (43) Дата публикации заявки: 27.09.2015 Бюл. № 27 R U 19.12.2016 (72) Автор(ы): АНЕЗИРИС Христос (DE), ГРОТЕ Хольгер (DE), ЛАНГЕ Фридерике (DE), ГЕРЛАХ Нора (DE), КЛИППЕЛЬ Уве (FR), ШАФФЁНЕР Стефан (DE), ШПАЙХЕР Харм (DE) 2 6 0 6 ...

Annular combustion chamber with two heads offset from each other

Apparatus and method for combusting fuel at high pressure and high temperature, and associated system and device

提供了一种燃烧设备，包括用于使碳质燃料与富氧和工作流体相混合以形成燃料混合物的混合装置。燃烧室至少部分地由蒸发构件定义出。蒸发构件至少部分地由耐压构件包围。燃烧室具有相对的入口和出口部。燃烧室的入口部被配置成接收燃料混合物，以便在燃烧温度下燃烧所述燃料混合物。燃烧室进一步被配置成将所产生的燃烧产物引导向出口部。蒸发构件朝向燃烧室引导蒸发物质穿过蒸发构件，以对燃烧产物和蒸发构件之间的相互作用进行缓冲。还提供了相关的系统、设备和方法。

Combustor liner

【課題】内部で燃焼帯が形成される燃焼器を提供する。 【解決手段】第１軸方向位置１４でそこに形成された第１混合穴１１を有する環状ライナー１０と、第２軸方向位置２４でそこに形成された第２混合穴２１を有し、ライナー１０の外部に第１流れ空間３０を形成する流れスリーブ２０と、第２軸方向位置２４で流れスリーブ２０に連結され、第２混合穴２１を介して第１流れ空間３０からの空気を除去するポート４０と、第２軸方向位置２４でそこに形成された第３混合穴５１を有し、ライナー１０を保護し、第３混合穴５１を介して燃焼帯２と通じ、且つ第１混合穴１１を介して第１流れ空間３０と通じる第２流れ空間６０をライナー１０内に形成するように配置されるシールド５０とを含んでいる。 【選択図】図１

Refractory product having improved flow

本发明涉及一种不定形制品，其包括由以下组成的颗粒混合物：‑粗部分，其按重量百分比计占颗粒混合物的大于50％且小于91％、且由尺寸大于或等于50μm的称为“粗颗粒”的颗粒组成；和‑基质部分，其形成颗粒混合物的至100％的余量、且由尺寸小于50μm的称为“基质颗粒”的颗粒组成，基于所述制品的氧化物按重量百分比计，所述制品具有的化学分析是：‑45％<Al 2 O 3 ，‑7.5％<SiO 2 <35％、‑0％≤ZrO 2 <33％，条件是10％<SiO 2 +ZrO 2 <54％，‑0.15％<B 2 O 3 <8％，‑其他氧化物：<6％，Al 2 O 3 构成至100％的余量，基于颗粒混合物的重量百分比计，所述粗部分包括大于15％的尺寸大于1mm的粗颗粒，基于基质部分的氧化物按重量百分比计，所述基质部分具有的化学分析是：‑Al 2 O 3 +SiO 2 +ZrO 2 >86％，条件是35％<Al 2 O 3 。将其应用至玻璃熔炉。

Ceramic tiles for lining of combustion chambers, in particular, gas turbines, and its production method

Изобретение относится к керамической плитке для футеровки камеры сгорания, в частности газовых турбин. Керамическая плитка для футеровки камер сгорания, в частности газовых турбин, содержит слой основания, изготовленный из керамического материала, например глинозема или глинозема-муллита, и покрытие, наносимое, по меньшей мере, на одну сторону слоя основания; покрытие представляет собой многослойное керамическое покрытие, содержащее, по меньшей мере, один внешний слой, изготовленный из глинозема или керамического материала, содержащего глинозем, и, по меньшей мере, один промежуточный слой, расположенный между внешним слоем и слоем основания и изготовленный из керамического материала, содержащегося муллит и предпочтительно муллит или глинозем-муллит. Изобретение обеспечивает повышение устойчивости плитки к высоким температурам, коррозии и механическим нагрузкам. 2 н. и 9 з.п. ф-лы, 1 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 606 288 C2 (51) МПК F23R 3/00 (2006.01) F23M 5/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ФОРМУЛА (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ 2014108988, 08.08.2012 (24) Дата начала отсчета срока действия патента: 08.08.2012 Дата регистрации: (72) Автор(ы): ПЕРО Филиппо (IT), ГУАЛЬКО Джузеппе Карло (IT), ВАККАРЕЦЦА Аттилио (IT) Приоритет(ы): (30) Конвенционный приоритет: (56) Список документов, цитированных в отчете о поиске: US 2008/090005 A1, 17.04.2008. RU 08.08.2011 IT MI2011A001519 2178530 C2, 20.01.2002. US 4336276 A, 22.06.1982. US 4810677 A, 07.03.1989. (45) Опубликовано: 10.01.2017 Бюл. № 1 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 11.03.2014 (86) Заявка PCT: IB 2012/054038 (08.08.2012) (87) Публикация заявки PCT: 2 6 0 6 2 8 8 (43) Дата публикации заявки: 20.09.2015 Бюл. № 26 R U (73) Патентообладатель(и): АНСАЛЬДО ЭНЕРГИЯ С.П.А. (IT) 13.12.2016 2 6 0 6 2 8 8 R U Адрес для переписки: 129090, Москва, ул. Б. Спасская, 25, строение 3, ООО "Юридическая фирма Городисский и ...

BURNER ELEMENT AND BURNER WITH ALUMINUM OXIDE COATING AND METHOD FOR COATING THE BURNER ELEMENT

1. Элемент (10, 12, 18) горелки, который содержит поверхность, которая возможно приходит в контакт с топливом, отличающийся тем, что возможно приходящая в контакт с топливом поверхность (23) имеет содержащее оксид алюминия покрытие (21), при этом содержащее оксид алюминия покрытие (21) содержит α-Al2O3, и при этом содержащее оксид алюминия покрытие является слоем (21) оксида алюминия. ! 2. Элемент (10, 12, 18) горелки по п.1, отличающийся тем, что покрытие содержит богатый алюминием первый слой (20) и расположенный над первым слоем (20), содержащий оксид алюминия второй слой (21). ! 3. Элемент (10, 12, 18) горелки по п.1, отличающийся тем, что покрытие имеет толщину (22) слоя от 50 мкм до 100 мкм. ! 4. Элемент (10, 12, 18) горелки по п.1, отличающийся тем, что элемент (10, 12, 18) горелки содержит сталь в качестве основного материала. ! 5. Элемент (10, 12, 18) горелки по п.4, отличающийся тем, что элемент (10, 12, 18) горелки содержит сталь сорта 16Мо3 в качестве основного материала. ! 6. Элемент (10, 12, 18) горелки по любому из пп.1-5, отличающийся тем, что элемент (10, 12, 18) горелки является подводом топлива или распределителем топлива. ! 7. Горелка (1, 107), которая содержит элемент (10, 12, 18) горелки по любому из пп.1-6. ! 8. Горелка (1, 107) по п.7, отличающаяся тем, что горелка (1, 107) является пилотной горелкой. ! 9. Способ покрытия возможно приходящей в контакт с топливом поверхности элемента (10, 12, 18) горелки, в котором возможно приходящую в контакт с топливом поверхность (23) покрывают содержащим оксид алюминия слоем (21). ! 10. Способ по п.9, в котором слой (21) оксида алюминия наносят на поверхность (23) посредством химического осаждения из газовой фазы (CVD). ! 11. Способ по п.10, в котором в рамках химического осаждения из га РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2010 125 614 (13) A (51) МПК F23D 11/36 (2006.01) F23M 5/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (71) Заявитель(и): СИМЕНС ...

Sandwich Thermal Insulation Layer System and Method for Production

A method produces thermal barrier coatings that adhere to components even at high temperatures and temperatures that change frequently. A gas-tight glass-metal composite coating is applied to the component and annealed. The corroded part of the gas-tight coating is then removed, and a second, porous coating is applied. The second coating can comprise a ceramic, in particular yttrium-stabilized zirconium oxide. A thermal barrier coating is provided that is a composite made of a gas-tight glass-metal composite coating and another porous coating disposed thereover. Because the boundary volume of the composite coating is partly crystallized to the other coating, superior adhesion within the composite is achieved. Thus, it is in particular possible to produce a composite made of silicate glass-metal composite coatings and yttrium-stabilized zirconium oxide that are temperature-stable for extended periods of time. Such a composite is particularly advantageous for use as a thermal barrier coating because it combines good protection against oxidation with low heat conductivity and susceptibility to aging.

For producing the device of methane gas and the purposes of the device

本发明涉及用于生产甲烷气体(G)的装置，其包括：封闭体(1)；用于输送封闭体中产物的器件，所述器件包括安装为沿着旋转几何轴线在封闭体中转动的螺杆(10)；螺杆的焦耳效应加热器件；用于去除存在于来自产物热处理的气体中的杂质的去除单元(12)，所述单元连接到封闭体的顶部出口；以及用于对去除单元出口处的气体进行净化的净化系统(21)。

Refractory wall with anti-corrosive layer

SLIDING FOR PRESSURE CASTING AND FIRE-RESISTANT CERAMICS PRODUCED FROM IT FOR GAS TURBINE INSTALLATIONS

1. Шликер для литья под давлением для изготовления огнеупорной керамики, применяемой в качестве теплозащитного экрана в контуре высокотемпературного газа газотурбинных установок, содержащий смесь зерен, по меньшей мере, из двух материалов с различными коэффициентами теплового расширения, а также органическое и/или неорганическое связующее вещество и загуститель, причем смесь зерен имеет мультимодальное распределение зерен по размеру, отличающийся тем, что мультимодальное распределение зерен по размеру выглядит следующим образом:- 10-20 вес. процентов - зерна большого размера диаметром 1-5 мм,- 10-20 вес. процентов - зерна среднего размера диаметром 0,5-1 мм и- 60-80 вес. процентов - зерна малого размера диаметром до 0,5 мм, и причем- распределение зерен по весу выбирается таким образом, что суммарное количество зерен в смеси составляет 100 весовых процентов.2. Шликер по п. 1, отличающийся тем, что доля зерен среднего размера предпочтительно состоит, по меньшей мере, на 20 весовых процентов из материала с более низким коэффициентом теплового расширения.3. Шликер по п. 1 или 2, отличающийся тем, что в качестве связующего вещества и загустителя предусмотрен ксантан, в особенности, ксантан в концентрации макс. 0,05 весового процента от шликера для литья под давлением.4. Шликер по п. 1 или 2, отличающийся тем, что в качестве связующего вещества предусмотрена система связующих веществ из двух полисахаридов.5. Шликер по п. 4, отличающийся тем, что система связующих веществ состоит из ксантана и раствора гуаровой камеди.6. Шликер по п. 1 или 2, отличающийся тем, что в качестве связующего вещества предусмотрено силикатное связующее вещество или ко� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК C04B 35/505 (13) 2014 109 925 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2014109925/03, 01.08.2012 (71) Заявитель(и): СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) Приоритет(ы): (30) Конвенционный приоритет: 16.08.2011 EP 11177668.8 (85) ...

Refractory wall and refractory bricks for building said wall

본 발명은 무기물의 생성물, 예를 들어, 시멘트, 석회(lime), 마그네사이트(magnesite), 백운석(dolomite) 또는 그 유사한 것이 700℃ 이상의 온도에서 실질적으로 산화 오븐 분위기에서 소성되는 대용량의 산업 오븐에 있는 내화성 벽에 관한 것으로서, 여기서 상기 벽은 내화성 물질의 비소성 벽돌들로 구성되고 탄소는 불 또는 열에 노출된 상기 벽의 벽돌 표면에 함유된다. 본 발명은 또한 상기 벽을 세우는데 있어서의 내화성 벽돌에 관한 것이다. 석회, 마그네사이트, 백운석, 내화성물질, 석공, 소결 The present invention relates to a high volume industrial oven in which the product of an inorganic material, such as cement, lime, magnesite, dolomite or the like, is fired in a substantially oxidizing oven atmosphere at temperatures above 700 ° C. Regarding a fire resistant wall, wherein the wall consists of non-fired bricks of refractory material and carbon is contained in the brick surface of the wall exposed to fire or heat. The invention also relates to a fire resistant brick in laying the wall. Lime, Magnesite, Dolomite, Refractory, Mason, Sinter

Component, method for coating a component, and powder

Coatings which are applied to a component have to be removed again in a complex way in certain regions, since a coating was not desired to be present in those regions. The subsequent removal of this layer adversely affects the component, for example its geometry. The method according to the invention for coating a component includes a masking which at least partially comprises a ceramic powder and can therefore easily be removed after the component has been coated.

Furnace operation involves using catalysts to prevent unwanted recombinations of molecular and atomic units at start and during cooling

Smokeless charcoal stove

Heating radiator tube

The radiant heating pipe (1) has a tubular body (2) having a central portion (8) and a recycle portion (19) that is arranged next to the central portion, where a free longitudinal end (9), opposite to another longitudinal end (3) of the radiant heating pipe is arranged in a wall (4) of an industrial furnace. The free longitudinal end has an opening (7), where an inner wall (21) of the radiant heating pipe is partially covered at the free longitudinal end with a thermal insulation (22).

Porous structures with repeating elongated-aperture pattern

Пористая структура для использования в ауксетичном материале содержит жесткое или полужесткое тело с первым множеством первых продолговатых отверстий и вторым множеством вторых продолговатых отверстий. Каждое из продолговатых отверстий имеет большую ось и малую ось. Большие оси первых продолговатых отверстий перпендикулярны большим осям вторых продолговатых отверстий. Первое и второе множества продолговатых отверстий расположены в массиве рядов и столбцов. Каждый из рядов и каждый из столбцов выполнены чередующимися между первыми и вторыми продолговатыми отверстиями. Продолговатые отверстия совместно сконфигурированы для достижения поведения с отрицательным коэффициентом Пуассона при воздействии напряжения или деформации или и того и другого. Каждое из первых и вторых продолговатых отверстий включает в себя отверстия, расположенные на расстоянии друг от друга и соединенные прямым щелевым отверстием. Продолговатые отверстия расположены в жестком или полужестком теле в ненапряженном состоянии и имеют заданную пористость 1-4%. Изобретение направлено на уменьшение деформации материала. 3 н. и 8 з.п. ф-лы, 10 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 682 461 C2 (51) МПК F23R 3/06 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F23R 3/06 (2018.08) (21)(22) Заявка: 2015141564, 13.03.2014 (24) Дата начала отсчета срока действия патента: Дата регистрации: 19.03.2019 15.03.2013 US 61/790,175 (43) Дата публикации заявки: 24.04.2017 Бюл. № 12 (56) Список документов, цитированных в отчете о поиске: US 2010/009120 A1, 14.01.2010. US (45) Опубликовано: 19.03.2019 Бюл. № 8 2009/041978 A1, 12.02.2009. FR 2941287 A1, 23.07.2010. RU 2162194 C1, 20.01.2001. RU 2443943 С2, 27.02.2012. RU 121347 U1, 20.10.2012. (85) Дата начала рассмотрения заявки PCT на национальной фазе: 15.10.2015 (86) Заявка PCT: C 2 C 2 (73) Патентообладатель(и): ПРЕЗИДЕНТ ЭНД ФЕЛЛОУЗ ОФ ГАРВАРД КОЛЛЕДЖ (US), РОЛЛС-РОЙС КАНАДА, ЛТД. (CA) US 2014/025324 ( ...

Composite part of machine and gas turbine

FIELD: machine building. SUBSTANCE: composite part of machine for a gas turbine with the main part made of an initial material, which in a partial area of its surface is equipped with lining from applied material with higher hardness and/or viscosity compared to the initial material. The lining is formed by certain number of lining elements, which in their longitudinal direction are applied onto the main part with an inclination towards the main flow of hot gas passing via the main part, so that lining elements cover the main body in a spiral manner. The gas turbine is made with a certain number of composite parts of the machine, namely, a fire tube, a combustion chamber, a mixing chamber of the combustion chamber and/or an inner body of the combustion chamber are arranged as composite parts of the machine. EFFECT: invention makes it possible to increase transverse stability and torsional rigidity of rings that form the main part, and especially preferable direction of cooling air with simultaneous flexibility of the main part during further treatment. 11 cl, 7 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 492 327 (13) C2 (51) МПК F01D 1/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2010127346/06, 31.10.2008 (24) Дата начала отсчета срока действия патента: 31.10.2008 (73) Патентообладатель(и): СИМЕНС АКЦИЕНГЕЗЕЛЛЬШАФТ (DE) (43) Дата публикации заявки: 10.01.2012 Бюл. № 1 2 4 9 2 3 2 7 (45) Опубликовано: 10.09.2013 Бюл. № 25 (56) Список документов, цитированных в отчете о поиске: DE 102004001722 A1, 04.08.2005. WO 02/081868 A1, 17.10.2002. EP 1283278 A2, 12.02.2003. WO 96/044511 A1, 15.02.1996. RU 2088764 C1, 27.08.1997. RU 2229031 C2, 20.05.2004. RU 2088836 C1, 27.08.1997. 2 4 9 2 3 2 7 R U (86) Заявка PCT: EP 2008/064768 (31.10.2008) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 05.07.2010 (87) Публикация заявки РСТ: WO 2009/071395 (11.06.2009) Адрес для переписки: 109012, ...

Use of unfired refractory products as a lining in large-volume industrial furnaces, as well as an industrial furnace lined with said unfired refractory products

본 발명은 하기의 제조를 위한 비소성 내화물의 용도에 관한 것으로, 탄소 운반체가 없고, 특히 압력을 이용하여 성형되거나 비성형되며, 결합제를 포함하고, 각각의 경우, 내화성 물질의 과립물이 900℃ 초과의 온도에서 세라믹 결합이 시작된다: 마그네시아 크로마이트 벽돌, 마그네시아 스피넬 및 스피넬 벽돌, 마그네시아 지르코니아 및 마그네시아 지르콘 벽돌, 마그네시아 허시나이트 및 마그네시아 갈락사이트 벽돌, 돌로마이트, 돌로마이트-마그네시아, 및 석회 벽돌, 고토감람석 및 감람석 벽돌, 마그네시아 고토감람석 벽돌, 마그네시아 플레오나스트 벽돌, 마그네시아 벽돌, 압축된 벽돌 또는 비성형된 덩어리 형태의 시멘트, 석회, 마그네시아, 및 돌로마의 제조를 위한, 산화 또는 기본적 산화 분위기로 작동되는 소성변(fire-side)으로서, 대용량 공업용 로(industrial furnaces)의 내화성 라이닝으로, 상기 벽돌은 20 MPa 초과의 냉각 압력 강도를 가지며, 생성물은 실온 내지 500℃의 온도 범위에서 과립 입자의 결합을 보장하는 최소한 제1의 임시 결합제, 및 300 내지 1000의 온도 범위에서 과립 입자의 결합을 보장하는 최소한 제2의 임시 결합제를 포함한다. The present invention relates to the use of non-calcined refractories for the production of the following, which are free of carbon carriers, in particular molded or unformed using pressure, and comprise binders, in each case the granules of refractory material having a temperature Ceramic bonding begins at temperatures above: Magnesia chromite bricks, Magnesia spinel and spinel brick, Magnesia zirconia and magnesia zircon bricks, Magnesia Hersheyite and magnesia galactic site bricks, Dolomite, dolomite-magnesia, and lime brick, Goto olivine and olivine brick, Magnesia goto olivine brick, Magnesia flonast brick, Magnesia brick, As a fire-side operating in an oxidizing or basic oxidizing atmosphere, for the production of cement, lime, magnesia, and stone Rome in the form of pressed bricks or unformed lumps, the fire resistance of large industrial furnaces Wherein the brick has a cooling pressure strength of greater than 20 MPa and the product has at least a first temporary binder to ensure bonding of the granular particles at a temperature ranging from room temperature to 500 DEG C, Lt; RTI ID = 0.0 &gt; a &lt; / RTI &gt; second temporary binder.

System and method for high efficiency power generation using a carbon dioxide circulating working fluid

The present invention provides methods and system for power generation using a high efficiency combustor (220) in combination with a C02 circulating fluid (236). The methods and systems advantageously can make use of a low pressure ratio power turbine (320) and an economizer heat exchanger (420) in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle C02 circulating fluid. Fuel derived C02 can be captured and delivered at pipeline pressure. Other impurities can be captured.

Apparatus and method for combusting a fuel at high pressure and high temperature, and associated system and device

A combustor apparatus is provided, comprising a mixing arrangement for mixing a carbonaceous fuel with enriched oxygen and a working fluid to form a fuel mixture. A combustion chamber is at least partially defined by a transpiration member. The transpiration member is at least partially surrounded by a pressure containment member. The combustion chamber has opposed inlet and outlet portions. The inlet portion of the combustion chamber is configured to receive the fuel mixture for the fuel mixture to be combusted at a combustion temperature. The combustion chamber is further configured to direct the resulting combustion product toward the outlet portion. The transpiration member directs a transpiration substance therethrough toward the combustion chamber for buffering interaction between the combustion product and the transpiration member. Associated systems, apparatuses, and methods are also provided.

System and method for high efficiency power generation using a carbon dioxide circulating working fluid

The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO 2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO 2 circulating fluid. Fuel derived CO 2 can be captured and delivered at pipeline pressure. Other impurities can be captured.

Method for high efficiency power generation using a carbon dioxide circulating working fluid

The present invention provides methods and system for expanding a heated and pressurized stream comprising recycled CO2 across at least one turbine so as to generate power and output from the at least one turbine a turbine discharge stream comprising CO2; treating the turbine discharge stream comprising CO2 to form the recycled CO2; compressing the recycled CO2; and heating the compressed, recycled CO2 using at least two different sources of heat prior to passing the recycled CO2 into a combustor.

System and method for high efficiency power generation using a carbon dioxide circulating working fluid

The present invention provides methods and system for power generation using a high efficiency combustor (220) in combination with a CO 2 circulating fluid (236). The methods and systems advantageously can make use of a low pressure ratio power turbine (320) and an economizer heat exchanger (420) and additional low grade heat from an external source (Q) can be used to provide part of an amount of heat needed for heating the recycle CO 2 circulating fluid. Fuel derived CO 2 can be captured and delivered at pipeline pressure while other impurities can be captured.

System for high efficiency power generation using a carbon dioxide circulating working fluid

The present invention provides methods and system for power generation using a high efficiency combustor in combination with a CO 2 circulating fluid. The methods and systems advantageously can make use of a low pressure ratio power turbine and an economizer heat exchanger in specific embodiments. Additional low grade heat from an external source can be used to provide part of an amount of heat needed for heating the recycle CO 2 circulating fluid. Fuel derived CO 2 can be captured and delivered at pipeline pressure. Other impurities can be captured.

Ceramic tile for combustion chambers lining, in particular of gas turbines, and manufacturing method thereof

用于燃烧室衬里特别是燃气轮机的燃烧室衬里的陶瓷砖（1），包括由例如氧化铝或者氧化铝-莫来石的陶瓷材料制成的基体（2），以及施用于基体（2）的至少一个面（4）的涂层（3）；所述涂层（3）为多层陶瓷涂层，包括至少一个外层（6）和至少一个中间层（5），所述至少一个外层（6）由氧化铝或者包括氧化铝的陶瓷材料制成，所述至少一个中间层（5）布置于外层（6）与基体（2）之间并且由包括莫来石的陶瓷材料制成，优选地由莫来石或者由氧化铝-莫来石制成。

Apparatus for waste gasification

A gasification system that includes a gasification reactor chamber having perforated conduits or an inner lining that increases the exposed surface area of waste materials to gasification conditions, thereby decreasing gasification temperature, time, and cooling period between subsequent gasification procedures. After an aspirator withdraws and oxidizes fuel gas from the gasification reactor chamber, a flare assembly combusts the mixed fuel gas to provide power or heat to at least one heat recovery device. The at least one heat recovery device recaptures thermal energy entrained in the exhaust, thereby reducing exhaust temperature and eliminating the need for an exhaust stack. An absorber purifies the exhaust and an extractor removes carbon dioxide. A portion of the removed carbon dioxide may be used for industrial purposes or for supporting vegetation. At least a portion of the remaining exhaust is returned to the gasification reactor chamber as recycled process gas, thereby completing a closed-loop system.

Improved apparatus for waste gasification

A gasification system that includes a gasification reactor chamber (101) having perforated conduits or an inner lining that increases the exposed surface area of waste materials to gasification conditions, thereby decreasing gasification temperature, time, and cooling period between subsequent gasification procedures. After an aspirator withdraws and oxidizes fuel gas from the reactor chamber, a flare assembly (229b) combusts the mixed fuel gas to provide power or heat to at least one heat recovery device (111). The at least one heat recovery device recaptures thermal energy entrained in the exhaust, thereby reducing exhaust temperature and eliminating the need for an exhaust stack. An absorber purifies the exhaust and an extractor (117) removes carbon dioxide. A portion of the removed carbon dioxide may be used for industrial purposes or for supporting vegetation. At least a portion of the remaining exhaust is returned to the reactor chamber as recycled process gas, thereby completing a closed-loop process.

Combustion assembly for a vehicle heater

Eine Brennkammerbaugruppe für ein Fahrzeugheizgerät umfasst ein Brennkammergehäuse (12) mit einer Umfangswandung (14) und einem Bodenbereich (16), welche eine Brennkammer (24) umgeben, an der Umfangswandung (14) wenigstens zwei zur Brennkammer offene Zündorganaufnahmeansätze (26), an einer Innenseite der Umfangswandung (14) und von wenigstens einem der Brennkammeransätze (26) ein poröses Verdampfermedium (28, 30), eine Brennstoffzuführleitungsanordnung (32) zum Zuführen von Brennstoff zu dem porösen Verdampfermedium (30) in dem wenigstens einen der Brennstoffaufnahmeansätze (26), an dessen Innenseite ein poröses Verdampfermedium (30) vorgesehen ist, in wenigstens einem der Zündorganaufnahmeansätze (26) ein elektrisch erregbares Zündorgan (34). A combustion chamber assembly for a vehicle heater comprises a combustion chamber housing (12) having a peripheral wall (14) and a bottom portion (16) surrounding a combustion chamber (24) at the peripheral wall (14) at least two Zündorganaufnahmeanätze (26) open to the combustion chamber, at one Inside the peripheral wall (14) and at least one of the combustion chamber lugs (26), a porous evaporator medium (28, 30), a fuel feed line arrangement (32) for supplying fuel to the porous evaporator medium (30) in the at least one of the fuel receiving lugs (26), on the inside of which a porous evaporator medium (30) is provided, in at least one of the ignition element receiving lugs (26) an electrically energizable ignition element (34).

Combustion chamber system for a vehicle heater