ЦЕНТРОБЕЖНОЕ РАБОЧЕЕ КОЛЕСО И ТУРБОМАШИНА

1. Центробежная турбомашина (1), содержащаякорпус (2),роторный узел (3), содержащий по меньшей мере одно центробежное рабочее колесо (10) для текучей среды, проходящей от впускной стороны (11) рабочего колеса (10) к его выпускной стороне (12),уплотнение (20) входного отверстия рабочего колеса, проходящее между входным отверстием (15) центробежного рабочего колеса (10) и корпусом (2) и предназначенное для предотвращения протечки текучей среды от стороны высокого давления к стороне низкого давления рабочего колеса (10),при этом указанное уплотнение (20) имеет по меньшей мере первую часть (21а), расположенную с впускной стороны (11), и последнюю часть (21е), расположенную с выпускной стороны (12) рабочего колеса (10), причем диаметр последней части (21е) меньше диаметра первой части (21а).2. Центробежная турбомашина (1) по п. 1, в которой уплотнение (20) входного отверстия представляет собой уплотнение лабиринтного типа с набором зубцов (21а-е), проходящих в радиальном направлении к оси (X) вращения рабочего колеса (10).3. Центробежная турбомашина (1) по п. 1, в которой уплотнение (20) входного отверстия установлено на впускном кольце (4) корпуса (2), обращенном к области (16) входного отверстия (15), имеющей по меньшей мере первую часть (17а), расположенную со стороны нагнетания, и последнюю часть (17е), расположенную с выпускной стороны рабочего колеса (10), причем диаметр последней части (17е) меньше диаметра первой части (17а).4. Центробежная турбомашина (1) по п. 2, в которой лабиринтное уплотнение (20) входного отверстия установлено на впускном кольце (4) корпуса (2), обращенном к ступенчатой области (16) входного отверстия (15), содержащей по меньшей мере первый уступ (17а), располож� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (51) МПК F01D 5/04 (13) 2014 100 858 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2014100858/06, 20.07.2012 (71) Заявитель(и): Нуово Пиньоне С.п.А. (IT) Приоритет(ы): (30) ...

Turboladerrad und Verfahren zum Auswuchten desselben

Ein Rad (70) eines Turboladers (10) weist ein erstes Ende, das einem zweiten Ende gegenüberliegt, und eine Drehachse (50), die sich zwischen dem ersten Ende und dem zweiten Ende erstreckt, auf. Das Rad (70) weist ferner eine Rückwand (58), die sich an dem zweiten Ende befindet, und eine Auswuchtnut (72), die in der Rückwand (58) ausgebildet ist, auf. Die Auswuchtnut (72) weist mehrere Seitenwände (76, 78, 80, 82) und eine Bodenfläche (74) auf. Die Seitenwände (76, 78, 80, 82) und die Bodenfläche (74) der Auswuchtnut (72) sind gefräste Flächen.

Verbessertes Einlasssystem für einen Radialverdichter

Ein Radialverdichter nutzt ein Verdichterrad (102) mit einem Inducer (103). Ein Lufteinlasskanal (108) weist einen ersten Bereich (109) und einen durch eine Abteilwand (111) vom ersten Bereich getrennten zweiten Bereich (110) auf. Die Abteilwand erstreckt sich ausgehend von einer Einlass-Ebene (112) des Inducers und verbindet den ersten Bereich mit einem ersten Luftfilter (115) und den zweiten Bereich mit einem zweiten Luftfilter (118).

Stroemungsmaschine mit ueberwiegend tangentialem Stroemungsverlauf im UEbergangsbereich des Laufrads an dessen Aussendurchmesser und in dem anschliessenden Bereich der zugehoerigen Leitelemente

IMPROVEMENTS RELATING TO FLUID-FLOW MACHINES

... 1301002 Turbines; gas turbine plant; centrifugal compressors H BACHL 30 June 1970 [30 June 1969 15 July 1969 30 April 1970] 31726/70 Headings F1C F1G and F1T A rotor for a fluid-flow machine, e.g. a compressor or turbine, includes a series of flow ducts each extending between radially outer and inner ports and consisting of an outer region adjacent the outer port where the flow passage is shaped for predominantly tangential flow with a small axial component, an inner region adjacent the inner port where the passage is shaped for predominantly axial or axial and tangential flow, and an intermediate region in which the passage is shaped for predominantly radial flow, the outer port having a radially inner rounded-over edge formed by part of a circumferentially extending rim of the rotor whereby there is a direct transition adjacent the edge between the outer and intermediate regions. In one arrangement, Figs. 2, 3, the rotor is of centripetal type, having partition walls or vanes 3, the driving ...

CERAMIC RADIAL TURBINE ROTOR

Inward flow radial turbine

Inward flow radial turbine

An inward flow radial turbine 1, rotating as per arrow 2 within a housing 5, associated with an annular vessel formed by co-axial cylinders 6 and 7, and an annular piston 11 operating on a two stroke cycle. On the outward stroke of the piston, energised fluid is admitted via a valve 15 and nozzle 16 to the vessel to form a swirl. On the inward stroke of the piston, valve 15 is closed, and the fluid swirl is displaced through an annular array of vanes 9 to the inducer 3 of the rotating turbine rotor and forced inwards between the turbine blades to exit at the exducer 4, whereby fluid kinetic energy is transferred to the turbine.

Double-sided radial flow rotor in or for a centripetal turbine or centrifugal compressor

... 1,036,486. Centrifugal compressors; turbines. BRISTOL SIDDELEY ENGINES Ltd. May 28, 1965 [June 5, 1964], No. 23377/64. Headings F1C and F1T. A rotor in or for a centrifugal compressor or centrifugal turbine has oppositely facing and staggered flow channels arranged to avoid flutter in the flow channel walls. The crosssectional area of each flow channel in planes perpendicular to the direction of flow is substantially constant along the length of the channel. When used in a centripetal turbine the direction of rotation of the rotor may be reversed by reversing the direction of the working fluid as by pivotally-mounted guide vanes or nozzles.

Silicon carbide reinforced aluminium alloy turbocharger impeller

A turbocharger impeller 1, for connection to a shaft 2, is formed from a metal matrix composite material having an aluminium alloy matrix and silicon carbide particulate reinforcement. The average particle diameter of the particulate reinforcement may be 2 microns or less. The particulate reinforcement may be from 10% to 30% of the composite by volume. The impeller may be fitted with a connector 3. The connector may frictionally engage an inner or outer surface of a shaft-side hub extension H of the impeller. The connector may have a threaded portion 12 which screws onto a corresponding threaded portion 7 of the shaft. The material of the connector may have a coefficient of thermal expansion which is equal to or greater than that of the composite material of the impeller. The material of the connector may have a greater strength than the composite material of the impeller.

CERAMIC RADIAL TURBINE ROTOR

Centrifugal impeller and turbomachine

A centrifugal turbomachine (1) comprises a casing (2); a rotor assembly (3) including at least one centrifugal impeller (10) for a fluid flowing from an inlet side (11) to an outlet side (12) of the impeller (10 and an eye seal (20) extending between an impeller eye (15) of the centrifugal impeller (10) and the casing (2) for preventing the fluid from leaking between the casing (2) and the centrifugal impeller (10); wherein the eye seal (20) comprises at least a first portion (21a) toward the inlet side (11) and a last portion (21e) toward the outlet side (12) of the impeller (10), the last portion (21e) being smaller in diameter than the first portion (21a).

RADIAL TURBINE WHEEL

RADIAL TURBINE WHEEL Apparatus and method for extending the thermal fatigue life and/or improving the performance of radial-flow turbine wheels in gas turbine engines by providing a thickened reinforcing pad on the wheel backface and cooling air passages in the surrounding case structure to direct high velocity cooling air onto the pad.

Läufer für Turbomaschinen.

Gasturbinengetriebenes Gebläse.

Zentrifugalkompressor.

Turbogebläserotor

Radial durchströmte Turbomaschine.

Laufrad für Turbomaschinen

Strömungsmaschine

Turbocharger.

Turbolader, mit einer Turbine zur Entspannung eines ersten Mediums, mit einem Verdichter zur Verdichtung eines zweiten Mediums unter Nutzung von in der Turbine bei der Entspannung des ersten Mediums gewonnener Energie, wobei die Turbine ein Turbinengehäuse (2) und einen Turbinenrotor (3) aufweist, wobei der Verdichter ein Verdichtergehäuse und einen mit dem Turbinenrotor über eine Welle (4) gekoppelten Verdichterrotor aufweist, wobei das Turbinengehäuse und das Verdichtergehäuse jeweils mit einem zwischen denselben angeordneten Lagergehäuse (1), in welchem die Welle (4) gelagert ist, verbunden sind, und wobei das Lagergehäuse (1) mit einem Turbinenzuströmgehäuse (2) des Turbinengehäuses über ein Kompensationselement (7) verbunden ist.

Turbocharger.

Turbolader, mit einer Turbine (1) zur Entspannung eines ersten Mediums, mit einem Verdichter zur Verdichtung eines zweiten Mediums unter Nutzung von in der Turbine bei Entspannung des ersten Mediums gewonnener Energie, wobei die Turbine (1) ein Turbinengehäuse (3) mit einem Turbinenzuströmgehäuse (4) und einen Turbinenrotor (6) aufweist, wobei der Verdichter ein Verdichtergehäuse und einen mit dem Turbinenrotor (6) über eine Welle (7) gekoppelten Verdichterrotor aufweist, wobei das Turbinengehäuse (3) und das Verdichtergehäuse jeweils mit einem zwischen denselben angeordneten Lagergehäuse (2), in welchem die Welle (7) gelagert ist, verbunden sind, und wobei das Turbinenzuströmgehäuse (4) derart spiralartig, einstückig und doppelwandig ausgebildet ist, dass zwischen einer äusseren Wand (15) des Turbinenzuströmgehäuses (4) und einer inneren Wand (16) des Turbinenzuströmgehäuses (4) ein Wasserkanal (17) zur Führung von Kühlwasser ausgebildet ist, und dass sich an die den Wasserkanal (17) begrenzende ...

Turbolader-Turbinenrotor und Turbolader.

Turbolader-Turbinenrotor, mit einem Rotorgrundkörper (2), mit integral am Rotorgrundkörper (2) ausgebildeten Laufschaufeln (3), wobei die Laufschaufeln (3) außendeckbandlos ausgebildet sind, wobei die Laufschaufeln (3) unter Ausbildung eines definierten Krümmungsbereichs (4) mit einem definierten, konstanten oder variablen Krümmungsradius rf in den Rotorgrundkörper (2) übergehen. An einer ersten Gruppe erster Laufschaufeln (3) gilt für den Krümmungsradius des Krümmungsbereichs (4) der ersten Laufschaufeln (3) folgende Beziehung: 2,5% ≤ r f1 *100/l ≤ 10%, wobei r f1 der konstante oder variable Krümmungsradius des Krümmungsbereichs der ersten Laufschaufeln und I die Länge der ersten Laufschaufeln an einer Strömungsaustrittskante ist. An einer zweiten Gruppe zweiter Laufschaufeln (3) weicht der Krümmungsradius r f2 des Krümmungsbereichs (4) der zweiten Laufschaufeln (3) vom Krümmungsradius r f1 des Krümmungsbereichs (4) der ersten Laufschaufeln (3) dämpfungsseitig definiert ab. Fig. 5 ...

IMPROVED DAMPING DEVICE FOR TURBOMACHINE COMPRESSOR

Device for separating an air/oil mixture

IMPROVED DAMPING DEVICE FOR TURBOMACHINE COMPRESSOR

Compresseur centrifuge de turbomachine comprenant un rotor (40) présentant une base (42) annulaire et une pluralité d'aubes (44) aménagées sur une face amont (42a) de la base (42), caractérisé en ce que le rotor (40) comprend un jonc (50) d'amortissement disposé sur la périphérie radiale externe de la base (42) Centrifugal turbomachine compressor comprising a rotor (40) having an annular base (42) and a plurality of vanes (44) provided on an upstream face (42a) of the base (42), characterized in that the rotor (40) comprises a damping ring (50) disposed on the outer radial periphery of the base (42)

Rotor

A ROTOR

A rotor (18) for use with a fluid flow generator or reactor, the rotor being intended to rotate about a central axis (19) and having a surface which defines an arcuate fluid pathway for fluid flow about the central axis about which the rotor is able to rotate, wherein the surface has the configuration of a logarithmic curve substantially conforming to the mathematical progression known as the Golden Section or the Fibonacci Progression.

Diffuser in wastegate turbine housings

A number of variations may include a turbine housing comprising a turbine body; an inlet passage and an outlet passage connected to the turbine body; a wastegate passage operatively connected to the outlet passage; a diffuser positioned within the outlet passage comprising at least one radial opening; wherein the first flow passage accepts fluid flow from the wastegate passage and the second flow passage accepts fluid flow from the turbine wheel; wherein a first end of the diffuser is attached to a first end of the turbine outlet and a second end of the diffuser is attached to a second end of the turbine outlet so that fluid flow from the first flow passage is directed into the second flow passage through the at least one radial opening before exiting the outlet passage, and wherein the at least one radial opening minimizes turbulence of fluid flow exiting the turbine housing.

TURBINE ROTOR

A turbine rotor of a turbine includes a hub that serves as an axis of rotation, and a plurality of turbine blades that are arranged on a peripheral surface of the hub and receive and direct working fluid flowing into from an inlet toward an outlet. The turbine blades each have a line extending along a shroud-side edge of the turbine blade from the inlet to the outlet as a shroud line. The shroud line includes an entrance-side shroud line La that makes a small change from the inlet toward the outlet in a blade angle with respect to the axis of rotation, a center shroud line Lb that extends from the outlet side of the entrance-side shroud line La and makes a greater change than that of the entrance-side shroud line La, and an exit-side shroud line Lc that extends from the outlet side of the center shroud line Lb to the outlet and makes a smaller change than that of the center shroud line Lb.

Partition for sealing the rear section of a radial compressor

Die Zwischenwand (40) zur Abdichtung des Rückraums des Verdichterrades (71) eines Radialverdichters bezüglich eines von einem Lagergehäuse (30) umschlossenen Lagerraums weist einen umlaufenden, rotationssymmetrisch geformten Befestigungsflansch (41) auf, welcher zur Befestigung der Zwischenwand an dem benachbarten Lagergehäuse vorgesehen ist und welcher eine plane Kontaktfläche zur Auflage auf einer Kontaktfläche des Lagergehäuses aufweist. Dabei sind in den Befestigungsflansch mehrere Bohrungen (42, 43) auf einer virtuellen Kreislinie eingelassen, wobei die Bohrungen mindestens einen Sperrluftkanal (42) sowie mehrere, in Umfangsrichtung auf der virtuellen Kreislinie verteilt angeordnete Bohrungen (43) zur Aufnahme von Befestigungsmitteln (50) umfassen. Die Zwischenwand ist erfindungsgemäss als eine rotationssymmetrische Scheibe ausgebildet, welche in der Herstellung durch das Bearbeitungsverfahren Drehen und ohne weitere Fräsbearbeitung in ihre endgültige Form gebracht werden kann. Für ...

МНОГОСТУПЕНЧАТАЯ ТУРБИНА, ПРЕДПОЧТИТЕЛЬНО ДЛЯ ЭЛЕКТРОСТАНЦИЙ, РАБОТАЮЩИХ ПО ОРГАНИЧЕСКОМУ ЦИКЛУ РЕНКИНА

Настоящее изобретение относится турбине, предназначенной для работы по органическому циклу Ренкина (ОЦР). Турбина содержит вал, установленный по меньшей мере в двух подшипниках, и множество осевых ступеней расширения, заданных рядами статорных лопаток, чередующимися с рядами роторных лопаток. Роторные лопатки удерживаются на соответствующих опорных дисках. Главный опорный диск напрямую соединен с валом в наружном положении относительно подшипников, при этом остальные опорные диски закреплены на главном опорном диске, последовательно друг за другом, а не напрямую с валом. Предлагаемое техническое решение обеспечивает получение консольной конфигурации турбины с множеством ступеней, при необходимости даже больше трех. Турбина позволяет расширять рабочую текучую среду с резким ростом энтальпии, по аналогии с тем, что получают с помощью традиционных многоступенчатых осевых турбин, которые не имеют консольную конфигурацию, или с помощью двух соединенных осевых турбин, при неизменных остальных условиях. Некоторые из остальных опорных дисков закреплены на главном опорном диске и консольно проходят с одной и той же стороны подшипников, в которых установлен вал, так что центр тяжести роторной части турбины дальше смещен к подшипникам. Консольная конфигурация согласно настоящему изобретению позволяет собирать и разбирать турбину довольно простым способом, как на этапе конструирования, так и во время обслуживания. 2 н. и 18 з.п. ф-лы, 17 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 716 932 C2 (51) МПК F01D 5/06 (2006.01) F01K 25/08 (2006.01) F01D 25/16 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F01D 5/06 (2020.01); F01K 25/08 (2020.01); F01D 25/16 (2020.01) (21)(22) Заявка: 2017131761, 21.03.2016 (24) Дата начала отсчета срока действия патента: Дата регистрации: (73) Патентообладатель(и): ТУРБОДЕН СПА (IT) 17.03.2020 03.04.2015 IT 102015902342533 (43) Дата публикации заявки: 07.05.2019 Бюл. № 13 (56) Список ...

Измерение полного давления текучей среды в турбомашине

Turbomaschine

Die Erfindung betrifft eine Turbomaschine mit einem um eine Drehachse (A) drehbar gelagerten Laufrad (1), das vorderseitig einen Einströmbereich (2) und einen Ausströmbereich (3) definiert und rückseitig mit einem Gehäuseteil (4) einen Axialspalt (5) ausbildend zusammenwirkt. Erfindungsgemäß bildet das Gehäuseteil (4) ein Axiallager für das Laufrad (1) aus. Zum Ausgleich einer Schrägstellung des Laufrads (1) ist das Gehäuseteil gegenüber einem weiteren Gehäuseteil (6) kippbeweglich gelagert.

SELBSTREGELNDE TURBINE

Verminderung der Thermoschockempfindlichkeit eines Radialturbinenrades

Impeller with circumferential thickness variation

A radial flow impeller comprises an impeller body 34 and a plurality of vanes 32 depending there from, wherein the impeller body 34 varies in thickness in a circumferential direction. The impeller body 34 may have a hub portion and a radially outer circumferential rim arranged about a common axis, the vanes 32 extending from the hub portion towards the rim, and the sectional thickness profile of the impeller body 34 varying in a cyclic manner. Alternatively, a method of manufacturing the impeller may comprise determining or predicting a stress distribution within the impeller body 34, determining a desired sectional thickness profile for the impeller body 34 based upon the stress distribution, and producing the impeller according to the sectional thickness profile. The number of cycles of variation in the thickness of the impeller body 34 may be dependent upon, and preferably equal to, the number and spacing of the vanes 32. The impeller body 34 may comprise one or more circumferential ...

SHEET METAL TURBINE HOUSING WITH CONTAINMENT DAMPERS

Rotor of turboblower

VANE WHEEL COMPRISING DAMPING MEANS AND A METHOD FOR COATING A VANE WHEEL

L'invention concerne une roue à aubes (1) comprenant un disque (2) d'axe de rotation (C) et une pluralité d'aubes solidaires du disque (2), ledit disque (2) étant réalisé dans un premier matériau métallique et comprenant des moyens d'amortissement des vibrations, lesdits moyens d'amortissement comprenant au moins un revêtement (7) disposé par projection thermique sur une zone annulaire (9) du disque (2), le revêtement (7) étant réalisé dans un deuxième matériau métallique différent du premier matériau de manière à permettre un déplacement entre les premier et deuxième matériaux pour amortir les vibrations.

CENTRIPETAL TURBINE ENGINE WITH DUAL TURBINE

Turbomachine, comportant au moins deux turbines centripètes (40, 42), chaque turbine centripète comportant un aubage de rotor (49, 51), caractérisée en ce que les aubages de rotor des turbines centripètes sont superposés radialement.

TURBINE ROTOR

DEVICE FOR POWER GENERATION ACCORDING TO A RANKINE CYCLE

A device for power generation according to a Rankine cycle, in particular according to an organic Rankine cycle (ORC), comprises a turbine (16), for expanding a vapour of a working fluid, and at least one heat exchanger (18, 20, 22), through which the expanded vapour has to flow. The turbine (16) and the heat exchanger(s) (18, 20, 22) are contained in a vapour tight container (10). The turbine (16) is a radial-outward-flow type turbine having a shaft that is led in a sealed manner out of said container (10), an axial vapour inlet port arranged opposite the shaft and located inside the container (10), and a stator exhaust ring with stator exhaust blades defining peripheral vapour exhaust openings for discharging the expanded vapour directly into the vapour tight container (10), in which the expanded vapour flows through the heat exchanger(s) (18, 20, 22).

High temperature radially fed axial steam turbine

The disclosure relates to a radially fed axial steam turbine with a cold inlet duct, axially displaced from a hot inlet duct such that is it further away from a first blade row than the hot inlet duct. The cold inlet duct receives a cold steam from a cold inlet spiral and directs it into the hot inlet duct in such a way that a boundary layer of cold steam is formed over the rotor circumferential surface between the outlet end of the cold inlet duct and the blade and vane rows. The rotor circumferential surface is also adapted to promote and maintain the boundary layer. In this way, a maximum temperature to which the rotor is exposed can be reduced.

Exhaust gas turbocharger for an internal-combustion engine and method of operating same

An exhaust gas turbocharger for an internal-combustion engine, whose exhaust gas turbine has a rotor disk with at least one semiaxial and one radial flow inlet cross-section, and is provided with a variable turbine geometry for the variable adjustment of at least one flow inlet cross-section. Furthermore, a compressor is provided in the intake system of the internal-combustion engine. In order to improve the efficiency of the exhaust gas turbocharger in a wide operating range, the ratio of the compressor outlet diameter to the average turbine inlet diameter can be variably adjusted according to the adjustment of the variable turbine geometry between a minimal value and a maximal value, the minimal value being lower than 1.1.

Rotor for an electric drive machine for driving a compressor, a turbine or a charger shaft of a turbocharger, and turbocharger comprising an electric drive machine and such a rotor

An exhaust-gas turbocharger having an electric drive unit for driving a compressor, a turbine, or a turbocharger shaft of the exhaust-gas turbocharger. The electric drive unit has a rotor and a stator. The rotor is equipped with a rotor body embodied around a rotation axis of the rotor. A receptacle for at least one permanent magnet is embodied on the rotor body. A permanent magnet is disposed in the receptacle of the rotor body. The rotor body is mountable using a threaded bushing on a turbocharger shaft of the exhaust-gas turbocharger. The rotor body has a further receptacle which extends in the direction of the rotation axis and in which the threaded bushing is disposed inside the rotor body. The further receptacle is disposed in the rotor body with an offset in the direction of the rotation axis relative to the receptacle.

METHOD FOR MANUFACTURING SHAFT FOR TURBINE ROTOR

PROBLEM TO BE SOLVED: To provide a method for manufacturing a shaft for a turbine rotor, which makes it possible to ensure that the dimensions of a flange, the dimensions of a shaft part, the squareness of the flange with respect to the shaft part, circular runout, and circularity are within a desired accuracy, without the need for a cutting operation. SOLUTION: With respect to target values of a final product, flanges (3a, 3b) have an outer diameter tolerance ranging from +0.0% to +0.6%, and a thickness tolerance ranging from -8% to -0.0%, a shaft part (2) has a diameter tolerance ranging from +0.0% to +0.6%, the circular runout tolerance is 0.5 mm or less, and the squareness tolerance of the flanges with respect to the shaft part is 0.5 mm or less. The method includes a step of pressing a sintered compact having sintered density that is equal to or greater than a relative density of 95%. In the pressing step, the sintered compact is pressed using an upper mold and lower mold having the ...

РОТОР, УСТРОЙСТВО, ПРЕОБРАЗУЮЩЕЕ ЭНЕРГИЮ ПОТОКА ТЕКУЧЕЙ СРЕДЫ, УСТРОЙСТВО, СОЗДАЮЩЕЕ ПОТОК ТЕКУЧЕЙ СРЕДЫ (ВАРИАНТЫ) И НАСОС

FIELD: pumps and turbines. SUBSTANCE: rotor used in device forming fluid medium flow or converting energy of fluid medium flow is mounted for rotation relative to central axis and is provided with working surface whose directrix sets bow-shaped line of motion of fluid medium flow located around central axis of rotation of rotor. This directrix of working surface has form of logarithmic curve which corresponds to mathematical progression known as golden section or Fibonaci progression. EFFECT: reduction of wear; enhanced efficiency. 33 cl, 17 dwg 95908 91сС ПЫ с» (19) РОССИЙСКОЕ АГЕНТСТВО ПО ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ ВИ `” 2 168 066 (51) МПК” (13) С2 Е 040 1/04, 17/06, 29/18, 29/28, 29/66, Е 03 В 3/00, Е 01 0 1/34 (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ РОССИЙСКОЙ ФЕДЕРАЦИИ (21), (22) Заявка: 98102415/06, 08.07.1996 (24) Дата начала действия патента: 08.07.1996 (30) Приоритет: 10.07.1995 АЧ РМ 4072 05.09.1995 АЧ РМ 5249 11.03.1996 АЧ РМ 8580 (43) Дата публикации заявки: 20.12.1999 (46) Дата публикации: 27.05.2001 (56) Ссылки: 4$ 3082695 А, 26.03.1963. 4$ 4540334 А, 10.09.1985. КУ 2013662 СЛ, 30.05.1994. 9$ 2165808 А, 11.09.1939. КУ 2130 (1, 05.05.1996. 5Ц 4793398 А, 19.01.1983. 0$ 4708585 А, 24.11.1987. (85) Дата перевода заявки РСТ на национальную фазу: 10.02.1998 (86) Заявка РСТ: АЦ 96/00427 (08.07.1996) (87) Публикация РСТ: М/О 97/03291 (30.01.1997) (98) Адрес для переписки: 103055, Москва, а/я 11, Попеленскому Н.К. (71) Заявитель: ХАРМЭН Джейден Дэвид (АЦ) (72) Изобретатель: ХАРМЭН Джейден Дэвид (АЦ) (73) Патентообладатель: ХАРМЭН Джейден Дэвид (АЦ) (74) Патентный поверенный: Попеленский Николай Константинович (54) РОТОР, УСТРОЙСТВО, ПРЕОБРАЗУЮЩЕЕ ЭНЕРГИЮ ПОТОКА ТЕКУЧЕЙ СРЕДЫ, УСТРОЙСТВО, СОЗДАЮЩЕЕ ПОТОК ТЕКУЧЕИ СРЕДЫ (ВАРИАНТЫ) И НАСОС (57) Изобретения могут быть использованы в насосах и турбинах. Ротор для использования в устройстве, создающем поток текучей среды или преобразующем энергию потока текучей среды, установлен с возможностью вращения относительно ...

МНОГОСТУПЕНЧАТАЯ ТУРБИНА, ПРЕДПОЧТИТЕЛЬНО ДЛЯ ЭЛЕКТРОСТАНЦИЙ, РАБОТАЮЩИХ ПО ОРГАНИЧЕСКОМУ ЦИКЛУ РЕНКИНА

ЦЕНТРОСТРЕМИТЕЛЬНАЯ ТУРБИНА

FIELD: engines and pumps. SUBSTANCE: invention relates to power, transport and aircraft engine building and can be used in technical facilities, where as energy source it is expedient to use high-temperature high-speed centripetal turbine with low volume flow of working medium, including turbo-compressors for pressurization of internal combustion engines and micro-power engineering. Centripetal turbine comprises a guiding device, a bod case y and a radial-axial impeller with a blading apparatus. At that ledge is made on outlet part of every blade of blades, while annular ledge is made on inner surface of the case opposite ledges at outlet parts of working blades. Value of gap between periphery of vane apparatus and case is constant. EFFECT: improving turbine efficiency by 2–3 %. 1 cl, 2 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 694 560 C1 (51) МПК F01D 1/08 (2006.01) F01D 5/14 (2006.01) F01D 5/04 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (52) СПК F01D 5/143 (2019.05); F01D 5/043 (2019.05); F01D 1/08 (2019.05) (21)(22) Заявка: 2018132431, 12.09.2018 (24) Дата начала отсчета срока действия патента: Дата регистрации: 16.07.2019 (54) ЦЕНТРОСТРЕМИТЕЛЬНАЯ ТУРБИНА (57) Реферат: Изобретение относится к энергетическому, транспортному и авиационному двигателестроению и может быть использовано в технических объектах, где в качестве источника энергии целесообразно использовать высокотемпературную высокооборотную центростремительную турбину с низким объемным расходом рабочего тела, включая турбокомпрессоры для наддува двигателей внутреннего сгорания и микроэнергетику. Центростремительная турбина содержит R U 2 6 9 4 5 6 0 Адрес для переписки: 125438, Москва, ул. Онежская, 8, Государственный научный центр Российской Федерации - федеральное государственное унитарное предприятие "Исследовательский центр имени М.В. Келдыша", Самойловой Наталье Александровне Стр.: 1 (56) Список документов, цитированных в отчете о поиске: RU ...

Verdichterrad mit welligen Radrücken

Die Erfindung betrifft ein Verdichterrad (1) einer Ladeeinrichtung (2) mit einer Nabe (4) und Schaufeln (5) sowie mit einem Radrücken (6). Erfindungswesentlich ist dabei, dass der Radrücken (6) einen von der Nabe (4) in Radialrichtung (7) ausgehenden wellenförmigen Verlauf (13) aufweist mit sich von der Nabe (4) in Radialrichtung (7) ausgehenden und aneinander anschließenden Bereichen (8, 9, 10, 11), nämlich – einem ersten konkaven Bereich (8), – einem sich an den ersten konkaven Bereich (8) anschließenden zweiten konvexen Bereich (9), – einem sich an den zweiten konvexen Bereich (9) anschließenden dritten konkaven Bereich (10), – einem sich an den dritten konkaven Bereich (10) anschließenden vierten konvexen Bereich (11). Hierdurch kann die Rissneigung erheblich reduziert werden. The invention relates to a compressor wheel (1) of a loading device (2) with a hub (4) and blades (5) and with a wheel back (6). Essential to the invention is that the Radrücken (6) from the hub (4) in the radial direction (7) outgoing wave-shaped course (13) with the hub (4) in the radial direction (7) outgoing and adjoining areas (8, 9, 10, 11), namely - a first concave area (8), - a second convex area (9) adjoining the first concave area (8), - a third concave adjoining the second convex area (9) Area (10), - a subsequent to the third concave area (10) fourth convex area (11). As a result, the tendency to crack can be significantly reduced.

Aufgeladene Brennkraftmaschine mit in Reihe angeordneten Abgasturboladern

Die Erfindung betrifft eine aufgeladene Brennkraftmaschine mit – einem Ansaugsystem zum Zuführen von Ladeluft, – einem Abgasabführsystem (1) zum Abführen des Abgases, – mindestens einer Abgasrückführung, und – mindestens zwei in Reihe geschalteten Abgasturboladern (2, 4), die jeweils eine im Abgasabführsystem (1) angeordnete Turbine (2a, 4a) und einen im Ansaugsystem angeordneten Verdichter (3, 5) umfassen und von denen ein erster Abgasturbolader (2) als Niederdruckstufe (2) und ein zweiter Abgasturbolader (4) als Hochdruckstufe (4) dient, wobei die zweite Turbine (4a) des zweiten Abgasturboladers (4) stromaufwärts der ersten Turbine (2a) des ersten Abgasturboladers (2) angeordnet ist. Es soll eine aufgeladene Brennkraftmaschine der oben genannten Art bereitgestellt werden, mit der die aus dem Stand der Technik bekannten Nachteile überwunden werden und deren Aufladeverhalten verbessert ist. Erreicht wird dies durch eine Brennkraftmaschine der oben genannten Art, die dadurch gekennzeichnet ist, dass – die zweite Turbine (4a) eine Radialturbine (4a) ist, deren Austrittsbereich (4f) koaxial zur Welle (4c) der Radialturbine (4a) verläuft und ausgebildet ist, so dass die Abströmung des Abgases aus der Radialturbine (4a) im Wesentlichen axial erfolgt, und – die erste Turbine (2a) eine Axialturbine (2a) ist, deren Eintrittsbereich (2e) koaxial zur Welle (2c) der Axialturbine (2a) und koaxial zum Austrittsbereich (4f) der zweiten Turbine (4a) verläuft und ausgebildet ist, so dass die Zuströmung des Abgases zur Axialturbine (2a) im Wesentlichen axial erfolgt. The invention relates to a supercharged internal combustion engine having - an intake system for supplying charge air, - an exhaust gas removal system (1) for discharging the exhaust gas, - at least one exhaust gas recirculation, and - at least two exhaust gas turbochargers (2, 4) connected in series, each one in the Abgasabführsystem (1) arranged turbine (2a, 4a) and arranged in the intake compressor (3, 5) comprise ...

Laufradseitenräume mit Resonatoren bei radialen Strömungsmaschinen

Die Erfindung betrifft eine Strömungsmaschine (100), insbesondere eine radiale Strömungsmaschine, wie einen Radialverdichter oder eine Radialturbine, mit einem Laufrad (10) mit einem Scheibenelement (14, 19) und einem Laufradseitenraum (4, 5), welcher zumindest zum Teil durch das Scheibenelement (14, 19) des Laufrads (10) und durch eine Laufradseitenraumwand (6, 7) begrenzt wird. In der Laufradseitenraumwand (6, 7) ist mindestens ein zu dem Laufradseitenraum (4, 5) hin offener, als Resonator wirkender Hohlraum (1) ausgebildet.

Turbolader-Turbinenrotor und Turbolader

Turbolader-Turbinenrotor, mit einem Rotorgrundkörper (2), mit integral am Rotorgrundkörper (2) ausgebildeten Laufschaufeln (3), wobei die Laufschaufeln (3) außendeckbandlos ausgebildet sind, wobei die Laufschaufeln (3) unter Ausbildung eines definierten Krümmungsbereichs (4) mit einem definierten, konstanten oder variablen Krümmungsradius rf in den Rotorgrundkörper (2) übergehen. An einer ersten Gruppe erster Laufschaufeln (3) gilt für den Krümmungsradius des Krümmungsbereichs (4) der ersten Laufschaufeln (3) folgende Beziehung: 2,5% ≤ rf1*100/l ≤ 10%, wobei rf1der konstante oder variable Krümmungsradius des Krümmungsbereichs der ersten Laufschaufeln und I die Länge der ersten Laufschaufeln an einer Strömungsaustrittskante (6) ist. An einer zweiten Gruppe zweiter Laufschaufeln (3) weicht der Krümmungsradius rf2des Krümmungsbereichs (4) der zweiten Laufschaufeln (3) vom Krümmungsradius rf1des Krümmungsbereichs (4) der ersten Laufschaufeln (3) dämpfungsseitig definiert ab.

ROTOR

INNERER VTG- BYPASS

Mehrere Variationen können ein Verfahren zum Verstärken eines Spitzenstroms in einem Turbolader mit einer Turbine mit variabler Geometrie enthalten, das Folgendes umfasst: Umleiten eines Fluidstroms zu einem Turbinenläufer durch Bilden mindestens eines inneren Bypasskanals durch einen unteren Schaufelring einer Schaufelpaketanordnung und/oder ein Turbinengehäuse unter dem unteren Schaufelring; Bereitstellen eines ersten Endes einer Schaufelkomponente in dem mindestens einen inneren Bypasskanal; und Verwenden des ersten Endes der Schaufelkomponente als Drehventil zum Steuern von Fluidstrom durch den mindestens einen inneren Bypasskanal.

Abgasturbolader

Abgasturbolader für eine Brennkraftmaschine, mit einem Turbinengehäuse, in dem ein Turbinenrad mit einem Schaft drehbar angeordnet ist, wobei der Schaft in einem Lagergehäuse mittels zumindest einem Kolbenring benachbart zu dem Turbinenrad drehbar gelagert ist und das Lagergehäuse zur Schmierung des Schafts einen Schmiermittelzufluss und einen drucklosen Schmiermittelabfluss aufweist, wobei zwischen dem Turbinenrad und dem Lagergehäuse eine von dem Turbinengehäuse und dem Lagergehäuse eingespannte Thermoscheibe vorgesehen ist, die eine Öffnung aufweist, die Schmiermittel führend mit dem Schmiermittelabfluss verbunden ist. Durch die erfindungsgemäße Ausgestaltung wird ein Übertreten von Schmiermittel aus dem Lagergehäuse in das Turbinengehäuse vermieden.

Blade clearance control for turbomachinery

A system includes a gas turbine engine (30) having a shroud (130) and a rotor (120) with one or more blades (126, 127). The rotor rotates within the shroud to pressurize a fluid during operation of the engine. An electromagnetic actuator (50) is also included that is operable to move the shroud relative to the rotor to adjust clearance between the shroud and blades. A controller (40) is included in this system to determine a desired amount of clearance in accordance with an operating mode of the engine. The controller generates an actuation signal to change the clearance in correspondence with the desired amount. The electromagnetic actuator responds to the actuation signal to provide the desired amount of clearance.

HOUSING ARRANGEMENT OF A TURBINE

Blade clearance control for turbomachinery

WELDING SHIELDING DAM FOR AUTOMATED WELDING OF IMPELLORS AND BLISKS

A dam (270) is provided for localizing gas around an outer periphery of an impeller (220). In one embodiment, by way of example only, the dam (270) includes a skirt (275), a flange (280), and a fastener (283). The skirt (275) includes an inner section (305), an outer section (310), and an outer peripheral edge (315). The inner section (305) is configured to be placed under the impeller (220), and the outer section (310) extends radially outwardly of the impeller outer periphery to the skirt outer peripheral edge (315). The flange (280) extends substantially perpendicular from the skirt outer peripheral edge (315). The fastener (283) is coupled to the skirt (275) and configured to couple the dam (270) to the impeller (220).

THERMAL AND EXTERNAL LOAD ISOLATING IMPELLER SHROUD

A gas turbine engine has a compressor assembly (22) and a turbine assembly (24) rotationally mounted on a shaft (25), the turbine assembly (24) being driven by hot gases discharged from a combustion chamber (28) disposed between the compressor and turbine assemblies (22, 24), the compressor (22) having a centrifugal impeller (50) for pressurizing and impelling air into the combustion chamber (28). The engine also includes an impeller shroud (40) covering the bladed portion of the centrifugal impeller (50), the impeller shroud (40) having a support bracket (60) having a thin and curved load-isolating profile for supporting a strut (72) that secures the impeller shroud (40) to a case (70) of the engine.

Radial centrifugal turbomachine

CENTRIPETAL TURBINE ENGINE WITH DUAL TURBINE

Turbomachine, comportant au moins deux turbines centripètes (40, 42), chaque turbine centripète comportant un aubage de rotor (49, 51), caractérisée en ce que les aubages de rotor des turbines centripètes sont superposés radialement. Turbomachine, comprising at least two centripetal turbines (40, 42), each centripetal turbine comprising a rotor blade (49, 51), characterized in that the rotor blades of the centripetal turbines are superimposed radially.

Paddle wheel for blowers, compressors, etc and its manufactoring process

TURBINE WHEEL CONTAINMENT DEVICE

TURBINES

Steam turbine for very low pressures

BLADE CLEARANCE CONTROL FOR GAS TURBINE ENGINE

An apparatus and method for controlling a clearance between the blades of a turbomachinery component and flow forming surface are disclosed herein, and includes controlling the clearance by moving the surface axially relative to the turbomachinery component. In one embodiment the apparatus includes an impeller rotatable about a first axis, a shroud encircling the impeller, and a first ring encircling the first axis. An actuator is operably engaged with the first ring to pivot the first ring about the first axis. The apparatus also includes at least one cam engaged with the first ring and at least one cam follower engaged with the shroud. Pivoting movement of the first ring about the first axis results in the at least one cam urging the at least one cam follower and the shroud along the first axis to vary a distance between the plurality of blades and the shroud.

Supercharger with new impeller and improved drive assembly

An impeller for a supercharger is described. The impeller comprises a body having a base and an air intake end wherein the body is adapted to mount to a drive assembly of the supercharger. Further, the drive assembly is able to drive and rotate the body. Precision made air vanes are attached to the body wherein the precision made air vanes and the body are able to be positioned within a volute chamber housing creating precision sealing gaps.

RADIAL TURBINE

Provided is a radial turbine in which fluids having a plurality of pressures are handled with a single or integrated turbine wheel and whose cost is reduced by decreasing the number of parts. A radial turbine (100) includes a radial turbine wheel (15) that is provided with a main pathway (26) in which blade height progressively increases while curving toward an axial direction from a radial direction, that converts swirling energy from a fluid that flows into the main pathway (26) from a main inlet (21) on an outer circumferential side and having a flow in the radial direction as the main component thereof into rotational motive power, and that expels the fluid in the axial direction, wherein a sub-inlet (29) into which flows a fluid whose pressure (P2) differs from pressure (P1) of the fluid supplied from the main inlet (21) is formed on a shroud side of the radial turbine wheel (15) at a position separated from the main inlet (21) in the radial direction and the axial direction; and a ...

A ROTOR

A rotor (18) for use with a fluid flow generator or reactor, the rotor being intended to rotate about a central axis (19) and having a surface which defines an arcuate fluid pathway for fluid flow about the central axis about which the rotor is able to rotate, wherein the surface has the configuration of a logarithmic curve substantially conforming to the mathematical progression known as the Golden Section or the Fibonacci Progression.

Turbinenlaufrad

Laeufer fuer Radialturbine

SELF-REGULATING TURBINE

Storage facility for gas turbine-driven blowers

TURBINENROTOR FROM TI-AL AND PROCEDURE FOR THE PRODUCTION OF THIS ROTOR

ROTOR

Improvements brought to the paddle wheels, in particular to the rotors of compressor or analogues

Rotor assembled cantilever, for turbo-compressor

Rotor with double face and radial flow for an inward-flow turbine or a centrifugal compressor

Solid turbine wheel with guided discharge

A solid wheel turbine including a series of spaced overlapping buckets suitable for use in high quality and wet steam applications is disclosed. Complex flow passageways for buckets in a turbine wheel are utilized to achieve both high erosion resistance and improved performance by guiding the discharge from the bucket. The solid turbine wheel has a reduced diameter rim portion and a full diameter rim portion such that the flow passageway may change in the relative radial displacement between the inlet and the discharge. An L-shaped passageway extending from the reduced diameter portion to the full diameter portion is utilized to obtain additional guidance of the flow as it is discharged from the turbine wheel to obtain improved performance.

VTG internal by-pass

A number of variations may include a method for increasing peak flow in a variable geometry turbine turbocharger comprising: by-passing fluid flow to a turbine impeller by forming at least one internal by-pass passage through at least one of a lower vane ring of a vane pack assembly or a turbine housing below the lower vane ring; providing a first end of a vane component within the at least one internal by-pass passage; and using the first end of the vane component as a rotary valve to control fluid flow through the at least one internal by-pass passage.

SHEET METAL TURBINE HOUSING WITH CAST CORE

Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes a core structure having a voided inner region defining an axial outlet and an outer surface defining an inner contour of a volute and an inner sheet metal shell having an inner base portion defining an inlet in fluid communication with the volute and a volute portion defining an outer contour of the volute, wherein at least a portion of the core structure defining the axial outlet extends in an axial direction through an opening in the inner sheet metal shell defined by the volute portion. The turbine housing assembly also includes an outer sheet metal shell surrounding the volute portion and including an outer base portion circumscribing the inner base portion. 1. A turbine housing assembly comprising:a core structure having a voided inner region defining an axial outlet and an outer surface defining an inner contour of a volute;an inner sheet metal shell comprising an inner base portion defining an inlet in fluid communication with the volute and a volute portion defining an outer contour of the volute, wherein at least a portion of the core structure defining the axial outlet extends in an axial direction through an opening in the inner sheet metal shell defined by the volute portion; andan outer sheet metal shell surrounding the volute portion and including an outer base portion circumscribing the inner base portion.2. The turbine housing assembly of claim 1 , wherein the core structure includes a tongue portion proximate the inner base portion claim 1 , the tongue portion separating the inlet and the volute.3. The turbine housing assembly of claim 1 , wherein the core structure comprises a cast metal structure joined to the inner sheet metal shell.4. The turbine housing assembly of claim 1 , wherein:the inner sheet metal shell comprises a plurality of sheet metal structures; andone of the plurality of sheet metal structures is welded to the ...

STEAM TURBINE

Dual-entry centrifugal compressor

Patent RU2017131761A3

7 ВУ"? 2017131761`” АЗ Дата публикации: 17.10.2019 Форма № 18 ИЗ,ПМ-2011 Федеральная служба по интеллектуальной собственности Федеральное государственное бюджетное учреждение ж 5 «Федеральный институт промышленной собственности» (ФИПС) ОТЧЕТ О ПОИСКЕ 1. . ИДЕНТИФИКАЦИЯ ЗАЯВКИ Регистрационный номер Дата подачи 2017131761/06(055749) 21.03.2016 РСТЛВ2016/051581 21.03.2016 Приоритет установлен по дате: [ ] подачи заявки [ ] поступления дополнительных материалов от к ранее поданной заявке № [ ] приоритета по первоначальной заявке № из которой данная заявка выделена [ ] подачи первоначальной заявки № из которой данная заявка выделена [ ] подачи ранее поданной заявки № [Х] подачи первой(ых) заявки(ок) в государстве-участнике Парижской конвенции (31) Номер первой(ых) заявки(ок) (32) Дата подачи первой(ых) заявки(ок) (33) Код страны 1. 1092015902342533 03.04.2015 | Название изобретения (полезной модели): [Х] - как заявлено; [ ] - уточненное (см. Примечания) МНОГОСТУПЕНЧАТАЯ ТУРБИНА, ПРЕДПОЧТИТЕЛЬНО ДЛЯ ЭЛЕКТРОСТАНЦИЙ, РАБОТАЮЩИХ ПО ОРГАНИЧЕСКОМУ ЦИКЛУ РЕНКИНА Заявитель: ТУРБОДЕН СПА, [Т 2. ЕДИНСТВО ИЗОБРЕТЕНИЯ [Х] соблюдено [ ] не соблюдено. Пояснения: см. Примечания 3. ФОРМУЛА ИЗОБРЕТЕНИЯ: [Х] приняты во внимание все пункты (см. Примечания) [ ] приняты во внимание следующие пункты: [ ] принята во внимание измененная формула изобретения (см. Примечания) 4. КЛАССИФИКАЦИЯ ОБЪЕКТА ИЗОБРЕТЕНИЯ (ПОЛЕЗНОЙ МОДЕЛИ) (Указываются индексы МПК и индикатор текущей версии) Е01О 5/06 (2006.01) ЕОТК 25/08 (2006.01) ЕОТО 25/16 (2006.01) 5. ОБЛАСТЬ ПОИСКА 5.1 Проверенный минимум документации РСТ (указывается индексами МПК) [ОТО 25/00-ВОТО 25/16, ВОР 5/00-ЕОТО 5/06 5.2 Другая проверенная документация в той мере, в какой она включена в поисковые подборки: 5.3 Электронные базы данных, использованные при поиске (название базы, и если, возможно, поисковые термины): РУ\У/РТ, Ебрасепес, Рабеагсв, ОЗРТО 6. ДОКУМЕНТЫ, ОТНОСЯЩИЕСЯ К ПРЕДМЕТУ ПОИСКА Кате- Наименование документа с указанием (где ...

KERAMISCHER RADIALTURBINENROTOR

Verfahren zur Herstellung eines keramischen Turboladerotors.

ROTARY TURBINE HAVING AN ARRANGEMENT TO CONTAIN A RUPTURED TURBINE WHEEL

... 1342966 Radial flow turbines SUNDSTRAND CORP 19 April 1971 [20 April 1970] 25146/71 Heading FIT To assist containment of the turbine wheel 16 on rupture an annular shoulder 91 on the wheel hub 72 projects into a recess 90 in the backplate 30, the shoulder having surfaces at an acute angle and the recess having a flat bottom surface and a peripheral surface 93 which increases in diameter away from the mouth of the recess. Three radial slots 88 in the wheel hub 72 provide for rupture into three pieces. A sealing ring 65 is supported by a ring 75 having projections 89 in the slots 88.

TURBOMACHINE

TURBOMACHINE Abstract of the Disclosure A turbomachine, operable as a compressor or a turbine, for a compressible fluid is provided which includes a wheel having a plurality of vanes extending from a generally axial flow section to a generally radial flow section. Adjacent vanes define fluid passageways having a generally axially oriented section and a generally radially oriented section. Located substantially within the generally radially oriented sections of a predetermined number of passageways is a reference station which has a configuration such that the mean tangential dimension of said passageway at said reference station is no more than about 60% of the circum-ference of the rotor at that mean radius divided by the number of vanes at that radius. Each reference station serves to effect substantial attachment of the flowing fluid to the surfaces defining said passageway, particularly at low mass flow, and, thus, broaden the usable flow range of the turbomachine. A rounded vane end at the wheel periphery further serves to enhance said attachment.

MULTISTAGE TURBINE PREFERABLY FOR ORGANIC RANKINE CYCLE ORC PLANTS

A turbine of an organic Ranking cycle ORC is described. The turbine comprises a shaft supported by at least two bearings and a plurality of axial stages of expansion, defined by arrays of stator blades alternated with arrays or rotor blades. The rotor blades are sustained by corresponding supporting disks. A main supporting disk is directly coupled to the shaft in an outer position with respect to the bearings, and the remaining supporting disks are constrained to the main supporting disk, and one to the other in succession, but not directly to the shaft. The proposed solution allows a cantilevered configuration of the turbine to be obtained while still having a plurality of stages, even more than three if desired. The turbine allows to expand the working fluid with high enthalpy jump similar to that obtainable by the conventional multistage axial turbines, which are not cantilevered, or by two coupled axial turbines, other conditions being unchanged. Some of the remaining supporting disks ...

TURBOMACHINE

Self-regulating turbine

BLADE WHEEL COMPRISING DAMPING MEANS AND A METHOD FOR LINING A BLADED WHEEL

L'invention concerne une roue à aubes (1) comprenant un disque (2) d'axe de rotation (C) et une pluralité d'aubes solidaires du disque (2), ledit disque (2) étant réalisé dans un premier matériau métallique et comprenant des moyens d'amortissement des vibrations, lesdits moyens d'amortissement comprenant au moins un revêtement (7) disposé par projection thermique sur une zone annulaire (9) du disque (2), le revêtement (7) étant réalisé dans un deuxième matériau métallique différent du premier matériau de manière à permettre un déplacement entre les premier et deuxième matériaux pour amortir les vibrations. The invention relates to a paddle wheel (1) comprising a disk (2) with an axis of rotation (C) and a plurality of vanes integral with the disk (2), said disk (2) being made of a first metallic material. and comprising means for damping vibrations, said damping means comprising at least one coating (7) arranged by thermal spraying on an annular zone (9) of the disc (2), the coating (7) being produced in a second metallic material different from the first material so as to allow movement between the first and second materials to dampen vibrations.

THERMAL COMPENSATING SUPPORT FOR TURBOCHARGER SHAFTS

Ceramic radial turbine rotor

A ceramic radial turbine rotor made of a ceramic material having a strength s (kg/mm2) includes blade tips having a thickness t (mm). A product st2 of strength s and t2 (square of t) is representative of resistance to breakage of the rotor to foreign objects colliding against blades of the rotor. The product st2 fulfills a relation st2>/=5x104 vm+33. In this case, v is a circumferential speed of tip ends of inducers of blades of the rotating rotor when the blades are damaged by steel balls having a mass m (kg) colliding against the blades in a steel ball collision test of blades of a ceramic radial turbine rotor, and vm is a product of v and m.

INLET SYSTEM FOR A RADIAL COMPRESSOR WITH A WIDE FLOW RANGE REQUIREMENT

A radial compressor employs a compressor wheel having an inducer. An inlet air passage has a first region and a second region separated from the first region by a divider wall. The divider wall extends from an inlet plane of the inducer and connects the first region to a first air filter and said second region to a second air filter. 1. A radial compressor comprising:a compressor wheel having an inducer; a first region and', 'a second region separated from the first region by a divider wall, said divider wall extending from an inlet plane of the inducer and connecting said first region to a first air filter and said second region to a second air filter., 'an inlet air passage having'}2. The radial compressor as defined in claim 1 , wherein the first and second inlet air regions are concentric claim 1 , said first region comprising an outer air inlet passage and the second region comprising an inner air inlet passage.3. The radial compressor as defined in claim 2 , further comprising an additional passage from the outer inlet air passage to a to a compressor shroud line through a slot in the compressor shroud line.4. The radial compressor as defined in claim 2 , wherein at least one of the inner and outer inlet passages comprise subdivided passages that are constructed with a positive or negative swirl angle.5. The radial compressor as defined in claim 1 , wherein the first and second regions have an axial inflow.6. The radial compressor as defined in claim 1 , wherein the first region has an axial inflow and the second region has a radial inflow.7. The radial compressor as defined in claim 1 , wherein one of first or second regions has a radial inflow.8. The radial compressor as defined in claim 1 , wherein at least one of the inner and outer regions comprises one or more passages that are subdivided into multiple passages for at least a portion thereof.9. The radial compressor as defined in claim 1 , wherein at least one of the first and second regions include a ...

METHOD FOR MANUFACTURING AN IMPELLER OF A ROTARY MACHINE AND AN IMPELLER MANUFACTURED USING SUCH A METHOD

A method for manufacturing an impeller of a rotary machine, the impeller including at least one vane limiting an inner channel, which is at least partly closed, the method includes successively manufactured the impeller of several material layers by a build-up process from a powder. The powder is applied in each case to a processing plane for the production of each material layer, and then a solid material layer is produced from the powder by a selective energy input, and structural orientation is determined for the impeller, according to which the impeller is built up in layers, and the structural orientation is defined by a first and a second angle, which angles describe the relative position of the impeller to the processing plane. 1. A method for manufacturing an impeller of a rotary machine , the impeller comprising at least one vane limiting an inner channel which is at least partly closed , the method comprising:successively manufactured the impeller from several material layers by a build-up process from a powder, by applying the powder in each case to a processing plane for the production of each material layer;producing a material layer from the powder by a selective energy input; anddetermining a structural orientation for the impeller, according to which the impeller is built up in layers, the structural orientation being defined by a first angle and a second angle, the first and second angles defining the relative position of the impeller to the processing plane.2. The method according to claim 1 , further comprising producing support structures from the powder together with the material layers by the build-up process claim 1 , removing the support structures after completion of the build-up process and optimizing the first and the second angle claim 1 , so that the support structures are minimized.3. The method according to claim 1 , wherein the first angle indicates the angle between an axis of rotation of the impeller to be manufactured and a w-axis ...

ROTOR FOR AN ELECTRIC DRIVE MACHINE FOR DRIVING A COMPRESSOR, A TURBINE OR A CHARGER SHAFT OF A TURBOCHARGER, AND TURBOCHARGER COMPRISING AN ELECTRIC DRIVE MACHINE AND SUCH A ROTOR

An exhaust-gas turbocharger having an electric drive unit for driving a compressor, a turbine, or a turbocharger shaft of the exhaust-gas turbocharger. The electric drive unit has a rotor and a stator. The rotor is equipped with a rotor body embodied around a rotation axis of the rotor. A receptacle for at least one permanent magnet is embodied on the rotor body. A permanent magnet is disposed in the receptacle of the rotor body. The rotor body is mountable using a threaded bushing on a turbocharger shaft of the exhaust-gas turbocharger. The rotor body has a further receptacle which extends in the direction of the rotation axis and in which the threaded bushing is disposed inside the rotor body. The further receptacle is disposed in the rotor body with an offset in the direction of the rotation axis relative to the receptacle. 111-. (canceled)12. A rotor for an electric drive unit for driving a compressor , or a turbine , or a turbocharger shaft of an exhaust-gas turbocharger , comprising:a rotor body embodied around a rotation axis of the rotor and being mountable using a threaded bushing on a turbocharger shaft of the exhaust-gas turbocharger;a receptacle for at least one permanent magnet embodied on the rotor body;at least one permanent magnet disposed in the receptacle of the rotor body;wherein the rotor body has a further receptacle which extends in a direction of the rotation axis and in which the threaded bushing is disposed inside the rotor body, the further receptacle being disposed in the rotor body with an offset in a direction of the rotation axis relative to the receptacle of the at least one permanent magnet.13. The rotor as recited in claim 12 , wherein the threaded bushing has an internal thread and an outer envelope claim 12 , wherein the outer envelope of the threaded bushing comes into abutment against an inner wall of the further receptacle upon a rotation around the rotation axis relative to the rotor body.14. The rotor as recited in claim 12 , ...

TURBOCHARGER

A turbocharger includes: a turbine wheel; a turbine housing; a bearing housing; a shroud having a facing surface which faces a tip of a blade of the turbine wheel and being configured to surround the turbine wheel, the shroud comprising a separate member from the turbine housing and being disposed inside the turbine housing via a gap with respect to the turbine housing; a mount supported to at least one of the turbine housing or the bearing housing, at a position closer to the bearing housing than a scroll flow path in an axial direction of the turbine wheel; and at least one connection part connecting the mount and the shroud. 114-. (canceled)15. A turbocharger , comprising:a turbine wheel configured to be rotated by exhaust gas of an engine;a turbine housing which accommodates the turbine housing and forms at least a part of a scroll flow path through which exhaust gas to be supplied to the turbine wheel flows;a bearing housing which accommodates a bearing supporting a shaft of the turbine wheel rotatably, the bearing housing being coupled to the turbine housing;a shroud having a facing surface which faces a tip of a blade of the turbine wheel and being configured to surround the turbine wheel, the shroud comprising a separate member from the turbine housing and being disposed inside the turbine housing via a gap with respect to the turbine housing;a mount supported to at least one of the turbine housing or the bearing housing, at a position closer to the bearing housing than the scroll flow path in an axial direction of the turbine wheel; andat least one connection part connecting the mount and the shroud,wherein the turbine housing includes a first housing formed of sheet metal, the first housing accommodating the turbine wheel and forming at least a part of the scroll flow path, andwherein the shroud is disposed inside the first housing via the gap with respect to the first housing.16. The turbocharger according to claim 15 , wherein each of the connection part ...

RADIAL CENTRIFUGAL TURBOMACHINE

A radial centrifugal turbomachine with an adjusting device operatively active at the axial inlet of the turbomachine fixed casing, including: an annular member delimiting at least one radially inner passage at the axial inlet, wherein the member front surface and abutment surface of the casing delimit a radial annular passage. An actuator is connected to the member and to move axially and/or rotate according to a predefined angle to vary the radial annular passage and/or passage sections delimited between stator blades of the turbomachine first radial stage. A transmission shaft coaxial with the rotation axis and integral with the member is operatively connected to the actuator. The adjusting device allows adjusting the mass flow rate at the inlet to better adapt the performances of the turbomachine to the loading of the process/cycle and to implement a safety system dedicated to stopping the turbomachine in case of an urgent stop request. 118-. (canceled)19. A radial centrifugal turbomachine , comprising:a fixed casing;a rotor disc installed in the casing and rotatable in the casing around a respective rotation axis;a ring of rotor blades mounted on a front face of the rotor disc and coaxial with the rotation axis, in which the rotor blades project axially from the front face of the rotor disc;a ring of stator blades, radially inner and concentric with respect to the ring of rotor blades, in which the stator blades extend axially between the casing and the front face of the rotor disc, in which the stator blades delimit between them passage sections;wherein the casing has an axial inlet that is radially inner with respect to the ring of stator blades;an adjusting device operatively active at the axial inlet; an annular member delimiting at least one radially inner passage for the fluid, the annular member being located at the axial inlet, in which a front surface of the annular member and an abutment surface of the casing delimit between them a radial annular ...

Compressor impeller with partially swept leading edge surface

An impeller associated with a compressor of a gas turbine engine includes a plurality of impeller blades. Each impeller blade of the plurality of impeller blades has a leading edge and a trailing edge opposite the leading edge in a streamwise direction. Each impeller blade of the plurality of impeller blades extends in a spanwise direction from a hub at 0% span to a tip at 100% span, and each impeller blade of the plurality of impeller blades has a plurality of mean camber lines that each extend from the leading edge to the trailing edge at a respective spanwise location. The leading edge includes a partially swept leading edge surface defined between 70% span to 100% span that extends in the streamwise direction between 3% to 15% of a mean camber line at 100% span.

VARIABLE-NOZZLE TURBINE WITH MEANS FOR RADIAL LOCATING OF VARIABLE-NOZZLE CARTRIDGE

A turbocharger having a variable-nozzle turbine formed by pivotable vanes supported by a nozzle ring includes an elastically deformable locator disposed between a radially outwardly facing surface of the center housing and an opposing surface of the nozzle ring. In one embodiment the locator is a metallic ring having a radially undulating waveform shape that repeats a plurality of times about a circumference of the locator. In another embodiment the locator is a metallic ring having a C-shaped cross-section in a radial-axial plane. In still another embodiment the locator is a metallic ring having an S-shaped cross-section in a radial-axial plane. In a further embodiment the locator is a plurality of circumferentially spaced, radial locator pins affixed in the center housing and received in radial slots formed in the nozzle ring, the pins restraining the nozzle ring circumferentially and axially but allowing thermal expansion of the nozzle ring. 1. A turbocharger having a variable-nozzle turbine , comprising:a turbine comprising a turbine housing and a turbine wheel mounted in the turbine housing and connected to a rotatable shaft for rotation therewith, the turbine housing defining a chamber surrounding the turbine wheel for receiving exhaust gas, and an axially extending bore through which exhaust gas is discharged after passing through the turbine wheel;a nozzle leading from the chamber generally radially inwardly to the turbine wheel;a compressor comprising a compressor housing and a compressor wheel mounted in the compressor housing and connected to the rotatable shaft for rotation therewith;a center housing connected between the compressor housing and the turbine housing and having a nose portion adjacent the turbine wheel defining a generally radially outwardly facing first surface and a second surface that faces generally axially toward the turbine wheel;a generally annular nozzle ring having a first face comprising one wall of the nozzle and axially spaced ...

Centrifuge turbine

A centrifuge type turbine. The turbine has a circular hollow rotor having a centrally located air and fuel inlet and an outer periphery. A stationary exhaust shroud surrounds the outer periphery of the rotor. The rotor has at least two spiral shaped swirl channels located therein extending from the air and fuel inlet to an outlet located at its outer periphery. The swirl channels are formed by stationary spiral walls. The air and fuel inlet has a plurality of stationary curved blades located therein and adapted to rotate with the rotor and to swirl and admix fuel and air introduced thereinto. An ignition source located in the exhaust shroud ignites the air/fuel mixture. A plurality of stationary push point members are located within the exhaust shroud. 1. A centrifuge type turbine comprising:a circular hollow rotor, said rotor having a centrally located air and fuel inlet and an outer periphery;a stationary exhaust shroud surrounding said outer periphery of said rotor;said rotor having at least two swirl channels located therein, each said swirl channel extending from said inlet to an outlet located in said outer periphery, said swirl channels being formed of stationary spiral walls;said air and fuel inlet having a plurality of stationary curved blades located therein and adapted to rotate with said rotor and to swirl and admix fuel and air introduced thereinto;a shroud inlet located in said stationary exhaust shroud and configured to receive the air and fuel mixture from each of said swirl channels as their respective outlets come into alignment therewith;an ignition source located in said exhaust shroud for igniting said air and fuel mixture; anda plurality of stationary push point members located within said exhaust shroud.2. The centrifuge type turbine of wherein said curved blades of said air and fuel inlet effect a change of direction of substantially 180 degrees.3. The centrifuge type turbine of wherein each of said swirl channels forms a substantially 385 ...

Methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities

Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor.

AXIAL TURBINE WHEEL WITH CURVED LEADING EDGE

A turbocharger including a turbine wheel having a hub-to-tip ratio of no more than 60% and blades with a high turning angle and a curved leading edge, a turbine housing forming an inwardly spiraling primary-scroll passageway that significantly converges to produce highly accelerated airflow into the turbine at high circumferential angles, and a two-sided parallel compressor. The compressor and turbine each produce substantially no axial force, allowing the use of minimal axial thrust bearings. 1. A turbocharger configured to receive an exhaust gas stream from an engine configured to operate over a range of standard operating conditions , and to compress input air into a pressurized air stream , comprising:a turbocharger housing including a turbine housing; anda rotor configured to rotate within the turbocharger housing along an axis of rotation, the rotor including an axial turbine wheel, a compressor wheel, and a shaft extending along the axis of rotation and connecting the turbine wheel to the compressor wheel;wherein the turbine wheel is configured with a hub, and with a plurality of axial turbine blades configured to drive the rotor in rotation around the axis of rotation when the turbocharger receives the exhaust gas stream from the engine, each blade having an axial leading edge, an axial trailing edge, a hub end, and a tip end opposite the hub end;wherein the axial leading edge of each blade is characterized by a leading edge curvature near the hub end, the leading edge curvature including a downstream curvature component.2. The turbocharger of claim 1 , wherein the leading edge curvature includes a circumferential curvature component.3. The turbocharger of claim 2 , wherein each blade's leading edge curvature is configured to provide adequate clearance between the blade and adjacent blades such that casting molds configured to cast the blades can be pulled from between the blades without deforming the casting molds.4. The turbocharger of claim 3 , wherein ...

Vaneless space guide ring spacers for turbocharger

Variable geometry turbine turbochargers with rotating guide vane members and spacer members. The spacer members are positioned in the space on the guide ring members between the ring of guide vane members and the turbine wheel.

Turbocharger Heat Shield

A heat shield for a turbocharger has a disc-like configuration. The heat shield includes an outer radial portion, an outer wall, a connecting wall, and an inner wall. The outer radial portion is disposed circumferentially around an axis of the heat shield. The outer wall extends from the outer radial portion in a first axial direction. The connecting wall extends radially inward substantially perpendicularly from the outer wall. The inner wall extends substantially perpendicularly from the connecting wall in a second axial direction opposite the first axial direction. 1. A heat shield for a turbocharger , the heat shield having a disc-like configuration comprising:an outer radial portion disposed circumferentially around an axis of the heat shield;an outer wall extending from the outer radial portion in a first axial direction;a connecting wall extending radially inward substantially perpendicularly from the outer wall; andan inner wall extending substantially perpendicularly from the connecting wall in a second axial direction opposite the first axial direction.2. The heat shield of claim 1 , the outer wall originates extends in the first axial direction from a first plane to a second plane claim 1 , and the inner wall extends in the second axial direction to terminate in a third plane that is parallel with and between the first plane and the second plane.3. The heat shield of claim 2 , wherein the outer wall originates in the first plane and terminates in the second plane.4. The heat shield of claim 3 , wherein the connecting wall extends radially inward in the second plane.5. The heat shield of claim 1 , wherein the outer wall and the inner wall have different axial dimensions.6. The heat shield of claim 1 , wherein the outer wall claim 1 , the connecting wall claim 1 , and the inner wall form an intermediate radial portion that extends radially between the outer radial portion and an inner radial portion.7. The heat shield of claim 6 , wherein the intermediate ...

HOUSING FOR A CENTRIFUGAL COMPRESSOR

A centrifugal compressor, has: an impeller; and a housing including: a shroud extending between a first end and a second end; a structural member having an outer end securable to a casing of the gas turbine engine, an inner end of the structural member intersecting the rear side of the shroud; and a reinforced region at the location where the structural member and the rear side of the shroud intersect, a thickness of the reinforced region in a direction normal to the gaspath side greater than a nominal thickness of the shroud, the reinforced region defining a curved surface extending from a first location on the structural member to a second location on the rear side of the shroud, a portion of the curved surface having a radius that increases from a first radius to a second radius at the second location. 1. A centrifugal compressor for a gas turbine engine , comprising:an impeller having blades extending from a hub to blade tips, the impeller having an inlet and an outlet; and a shroud annularly extending around the blade tips of the impeller and extending in a streamwise direction between a first end proximate the inlet of the impeller and a second end proximate the outlet of the impeller, the shroud having a gaspath side facing the impeller and a rear side opposed to the gaspath side;', 'a structural member supporting the shroud, the structural member having an outer end securable to a casing of the gas turbine engine, an inner end of the structural member intersecting the rear side of the shroud at a location between the first end and the second end; and', 'a reinforced region at the location where the structural member and the rear side of the shroud intersect, a thickness of the reinforced region in a direction normal to the gaspath side being greater than a nominal thickness of the shroud outside the reinforced region, the reinforced region defining a curved surface extending from a first location on the structural member to a second location on the rear side ...

TURBINE SHROUD CONTOUR EXDUCER RELIEF

A turbocharger turbine having a blade-gap zone between the blades and the shroud wall. The blade-gap zone is larger at and near the exducer than at an upstream location where the shroud wall is at its minimum radius. Also disclosed is a method of customizing and manufacturing a turbine by establishing an optimized blade-gap zone at the exducer, and machining it into a turbine housing. 1. A method of designing and manufacturing a turbine to meet design requirements including one or more metrics from the group of metrics including flow , efficiency , and outlet temperature , comprising:providing a base turbine design;establishing the one or more metrics for the base turbine design;providing a database of modification effects for a plurality of sets of turbine housing machining parameters, each set of turbine housing machining parameters including one or more turbine housing parameters from the group of turbine housing parameters including an extension distance, a radial increase, and a corner geometric configuration;selecting an initial set of turbine housing machining parameters for the base turbine design to create a modified turbine design;establishing the one or more metrics for the modified turbine design;iteratively reselecting the set of turbine housing machining parameters and reestablishing the one or more metrics for the modified turbine design until the one or more metrics are optimized to establish an optimum set of turbine housing machining parameters for the design requirements; andmanufacturing a turbine of the base turbine design and manufacturing the turbine housing to meet the optimum set of turbine housing machining parameters.2. The method of claim 1 , wherein the step of providing a database comprises the steps of:establishing an experimental turbine design;establishing a plurality of sets of turbine housing machining parameters to be tested;making one or more test models of the experimental turbine design;machining the one or more test models to ...

VARIABLE GEOMETRY TURBOCHARGER

A variable geometry turbocharger includes: a turbine rotor; and a variable nozzle mechanism for adjusting a flow of exhaust gas to the turbine rotor from a scroll flow passage formed on a radially outer side of the turbine rotor. The variable nozzle mechanism includes: a nozzle vane disposed in an exhaust gas flow passage for guiding the exhaust gas to the turbine rotor from the scroll flow passage; a support wall forming a flow passage wall on a first side of the exhaust gas flow passage with respect to an axial direction of the turbine rotor and supporting the nozzle vane rotatably in a cantilever fashion; and a non-support wall forming a flow passage wall on a second side of the exhaust gas flow passage with respect to the axial direction. Of an end surface of the nozzle vane on a side of the non-support wall, an edge portion on a side of a pressure surface includes a non-support-wall side linear portion formed to have a linear shape. 114-. (canceled)15. A variable geometry turbocharger , comprising:a turbine rotor; anda variable nozzle mechanism for adjusting a flow of exhaust gas to the turbine rotor from a scroll flow passage formed on a radially outer side of the turbine rotor, a nozzle vane disposed in an exhaust gas flow passage for guiding the exhaust gas to the turbine rotor from the scroll flow passage;', 'a support wall forming a flow passage wall on a first side of the exhaust gas flow passage with respect to an axial direction of the turbine rotor and supporting the nozzle vane rotatable in a cantilever fashion; and', 'a non-support wall forming a flow passage wall on a second side of the exhaust gas flow passage with respect to the axial direction, and, 'wherein the variable nozzle mechanism includeswherein, of an end surface of the nozzle vane on a side of the non-support wall, an edge portion on a side of a pressure surface includes a non-support-wall side linear portion formed to have a linear shape.16. The variable geometry turbocharger according ...

SHEET METAL TURBINE HOUSING WITH CAST CORE

Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes a core structure having a voided inner region defining an axial outlet and an outer surface defining an inner contour of a volute and an inner sheet metal shell having an inner base portion defining an inlet in fluid communication with the volute and a volute portion defining an outer contour of the volute, wherein at least a portion of the core structure defining the axial outlet extends in an axial direction through an opening in the inner sheet metal shell defined by the volute portion. The turbine housing assembly also includes an outer sheet metal shell surrounding the volute portion and including an outer base portion circumscribing the inner base portion. 1. A turbine housing assembly comprising:a cast core structure having a voided inner region defining an axial outlet and an outer surface defining an inner contour of a volute;an inner sheet metal shell comprising an inner base portion defining an inlet in fluid communication with the volute and a volute portion defining an outer contour of the volute, wherein at least a portion of the cast core structure defining the axial outlet extends in an axial direction through an opening in the inner sheet metal shell defined by the volute portion; andan outer sheet metal shell surrounding the volute portion and including an outer base portion circumscribing the inner base portion.2. The turbine housing assembly of claim 1 , further comprising a cast bypass valve assembly structure claim 1 , wherein the outer sheet metal shell is joined to the cast bypass valve assembly structure and the inner sheet metal shell is freestanding with respect to the cast bypass valve assembly structure.3. The turbine housing assembly of claim 1 , further comprising a cast bypass valve assembly structure claim 1 , wherein the outer sheet metal shell is joined to the cast bypass valve assembly structure and the inner ...

Abrasive flow media fixture with end contour

A fixture assembly includes an inner diameter wall displaced from a main body by a first end wall with a convex surface and a second end wall with a concave surface. A method of machining a gas turbine engine component with an Abrasive Flow Media (AFM) process includes restricting a flow of media adjacent to an outer sidewall of an outer airfoil to be generally equal between each of a multiple of airfoils of the component.

Turbocharger Having Thrust Bearing Oil Retainer

A turbocharger includes a turbine wheel, a compressor wheel, and a shaft coupled to the turbine wheel and the compressor wheel. The turbocharger additionally includes a bearing housing containing a thrust bearing through which the shaft extends. The bearing housing receives oil and drains the oil therefrom. The bearing housing includes a reservoir that maintains a retained portion of the oil received in the bearing housing after the oil is drained from the bearing housing. The retained portion of the oil lubricates the thrust bearing. 1. A turbocharger comprising:a turbine wheel, a compressor wheel, and a shaft coupled to the turbine wheel and the compressor wheel; anda bearing housing containing a thrust bearing through which the shaft extends, wherein the bearing housing receives oil and drains the oil therefrom;wherein the bearing housing includes a reservoir that maintains a retained portion of the oil received in the bearing housing after the oil is drained from the bearing housing, the retained portion of the oil lubricating the thrust bearing.2. The turbocharger according to claim 1 , wherein the thrust bearing is arranged in the reservoir in contact with the retained portion of the oil.3. The turbocharger according to claim 1 , wherein the thrust bearing has a lower portion that protrudes into the reservoir. The turbocharger according to claim 1 , wherein the thrust bearing has an outer periphery that includes a truncated portion with a central region claim 1 , wherein the central region defines the lower portion.54. The turbocharger according to claim claim 1 , wherein the central region has a constant radius that is concentric with an axis of rotation of the shaft.64. The turbocharger according to claim claim 1 , wherein the reservoir includes a lower wall having ends at an elevation above the lower portion of the thrust bearing.74. The turbocharger according to claim claim 1 , wherein the truncated portion of the outer periphery of the thrust bearing ...

Fluid recirculation turbine system

A rotor rotatably mounted within a turbocharger housing includes a turbine wheel and a shaft. The shaft connects the turbine wheel. The hub defines a turbine-wheel back-disk surface facing the portion of the housing containing the bearings, and the hub defines a blade-side surface. The turbine hub and the housing define a turbine-wheel back-disk cavity. The turbine hub forms a ring-shaped primary axial protrusion extending circularly around the turbine-wheel back-disk surface into a circular channel in the housing. The circular channel leads into a bypass that bypasses the turbine blades. A relief flow valve is placed in the bypass. The relief control valve is controlled to open when the bypass pressure is above a cutoff pressure, and close when it is below the cutoff pressure.

PNEUMATIC MOTOR FOR PNEUMATIC TOOLS

A pneumatic motor for pneumatic tools includes a cylinder provided therein with a vane wheel. A rotating shaft inserted in the vane wheel is provided with a withstanding member and a tightening member, which can push the withstanding member to move toward the vane wheel and tighten the vane wheel with the rotating shaft for avoiding gap between the vane wheel and the rotating shaft. Thus, when outside driving air pushes the vane wheel to rotate, the vane wheel can synchronously drive the rotating shaft to rotate immediately and truly. By so designing, this invention can solve the problems of the conventional pneumatic motor that is likely to cause starting delay, untrue in power transmission and easy to wear. 1. A pneumatic motor for pneumatic tools comprising a cylinder , said cylinder provided with an air chamber , said air chamber installed therein with a vane wheel , said vane wheel formed with a shaft hole for receiving a rotating shaft therein , said vane wheel having a circumferential side provided with a plurality of blades spaced apart , said cylinder having two sealing covers respectively covered at opposite openings of said air chamber , said sealing covers respectively provided with a pivot joint portion to be respectively and pivotally connected with two ends of said rotating shaft to enable said rotating shaft to rotate relative to said cylinder , and characterized bysaid rotating shaft having one end bored with a tightening hole and said rotating shaft having one side radially bored with a withstanding hole communicating with said tightening hole at a location corresponding to said shaft hole of said vane wheel;a withstanding member slidably received in said withstanding hole, said withstanding member formed with a driven portion at one side facing said tightening hole, said withstanding member provided with a withstanding portion at one side facing said vane wheel; anda tightening member inserted in said tightening hole, said tightening member ...

SHEET METAL TURBINE HOUSING WITH BIAXIAL VOLUTE CONFIGURATION

Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes and inner shell and an outer shell. The inner shell includes an inner base portion defining an inlet and a volute portion defining an outer contour of a volute in fluid communication with the inlet. The outer shell circumscribing the volute portion in a radial plane and includes an outer base portion circumscribing the inner base portion. The inner shell includes a first plurality of sheet metal structures joined to one another in the radial plane, the outer shell includes a second plurality of sheet metal structures, and first portions of the second plurality of sheet metal structures surrounding the volute portion are joined to one another in an axial plane transverse to the radial plane. 1. A turbine housing assembly comprising: an inner base portion defining an inlet; and', 'a volute portion defining an outer contour of a volute in fluid communication with the inlet;, 'an inner shell comprising the inner shell comprises a first plurality of sheet metal structures joined to one another in the radial plane;', 'the outer shell comprises a second plurality of sheet metal structures; and', 'first portions of the second plurality of sheet metal structures surrounding the volute portion are joined to one another in an axial plane transverse to the radial plane., 'an outer shell circumscribing the volute portion in a radial plane and including an outer base portion circumscribing the inner base portion, wherein2. The turbine housing assembly of claim 1 , wherein:the first plurality of sheet metal structures are coupled about the volute portion; andsecond portions of the second plurality of sheet metal structures enclosing the volute portion in an axial direction are coupled diametrically.3. The turbine housing assembly of claim 1 , wherein the outer shell defines a bearing opening having a radial dimension greater than a radial dimension of the ...

SHEET METAL TURBINE HOUSING WITH CONTAINMENT DAMPERS

Turbine housing assemblies and related turbocharger systems are provided. One exemplary turbine housing assembly includes an inner shell defining an inner inlet portion and a volute portion providing an outer contour of a volute, an outer shell surrounding the volute portion and defining an outer inlet portion circumscribing the inner inlet portion, and one or more energy absorbing members coupled to an inner surface of the outer shell between the outer shell and the inner shell. The inner shell includes a first plurality of sheet metal structures coupled together in a first plane and the outer shell includes a second plurality of sheet metal structures coupled together in a second plane transverse to the first plane. 1. A turbine housing assembly comprising:an inner shell defining an inner inlet portion and a volute portion providing an outer contour of a volute, the inner shell comprising a first plurality of sheet metal structures coupled together in a first plane;an outer shell surrounding the volute portion and defining an outer inlet portion circumscribing the inner inlet portion, the outer shell comprising a second plurality of sheet metal structures coupled together in a second plane transverse to the first plane; andone or more energy absorbing members coupled to an inner surface of the outer shell between the outer shell and the inner shell.2. The turbine housing assembly of claim 1 , wherein each of the second plurality of sheet metal structures includes a respective energy absorbing member of the one or more energy absorbing members coupled to the inner surface of a respective one of the second plurality of sheet metal structures.3. The turbine housing assembly of claim 1 , wherein a thickness of the one or more energy absorbing members is different from a thickness of the inner shell.4. The turbine housing assembly of claim 1 , wherein a thickness of the one or more energy absorbing members is equal to a thickness of the outer shell.5. The turbine ...

DIFFUSER IN WASTEGATE TURBINE HOUSINGS

A number of variations may include a turbine housing comprising a turbine body; an inlet passage and an outlet passage connected to the turbine body; a wastegate passage operatively connected to the outlet passage; a diffuser positioned within the outlet passage comprising at least one radial opening; wherein the first flow passage accepts fluid flow from the wastegate passage and the second flow passage accepts fluid flow from the turbine wheel; wherein a first end of the diffuser is attached to a first end of the turbine outlet and a second end of the diffuser is attached to a second end of the turbine outlet so that fluid flow from the first flow passage is directed into the second flow passage through the at least one radial opening before exiting the outlet passage, and wherein the at least one radial opening minimizes turbulence of fluid flow exiting the turbine housing. 1. A turbine housing comprising:a turbine body constructed and arranged to house a turbine wheel;an inlet passage connected to the turbine body constructed and arranged to direct fluid flow into the turbine body;an outlet passage connected to the turbine body constructed and arranged to direct fluid flow out of the turbine housing;a wastegate passage operatively connected to the outlet passage constructed and arranged to direct fluid flow from a wastegate;a diffuser positioned within the outlet passage, wherein the diffuser is constructed and arranged to define a first flow passage and a second flow passage, wherein the first flow passage is defined by an inner surface of the outlet passage and an outer surface of the diffuser and the second flow passage is defined by an inner surface of the diffuser, wherein the diffuser includes at least one radial opening defined by a surface of the diffuser;wherein the first flow passage is constructed and arranged to accept fluid flow from the wastegate passage and the second flow passage is constructed and arranged to accept fluid flow from the turbine ...

Multi-stage radial turboexpander

A multi-stage turboexpander and a method for generating mechanical power therewith are disclosed. The multi-stage turboexpander includes a casing and a shaft, arranged for rotation in the casing. The shaft is supported by a first bearing at a first shaft end portion and a second bearing at a second shaft end portion. A first radial impeller and a second radial impeller are arranged between the first bearing and the second bearing on the shaft for co-rotation therewith around a rotation axis.

Device for separating an air/oil mixture

The invention relates to a device (1) for separating an air/oil mixture comprising an air/oil mixture inlet (8), an oil receiving chamber (9), an air circulation duct (11), at least one filter element (21) rotatably coupled to a rotating drive shaft (12), the device (1) being designed so that the mixture from the above-mentioned inlet (8) opens into the chamber (9) and is driven through the rotatably driven filter element (21), so that the oil contained in the mixture is centrifuged radially outside the filter element (21) and fed into the oil receiving chamber (9), the filtered air opening into the air flow line (11), characterized in that the rotating drive shaft (12) is coupled to a turbine (26) capable of being driven in rotation by at least part of the filtered air flow, the turbine (26) comprising an outlet (29) of the filtered flow which opens to the outside.

TURBOCHARGER

A turbocharger has a turbine for expanding a first medium and a compressor for compressing a second medium utilizing energy extracted in the turbine. The turbine includes a housing with a turbine inflow housing and a turbine rotor. The compressor has a compressor housing and a compressor rotor coupled to the turbine rotor via a shaft. The turbine inflow housing is constructed in a spiral-like, one-piece and double-walled manner such that between an outer wall of the turbine inflow housing and an inner wall of the turbine inflow housing a water duct for conducting cooling water is formed. The inner wall delimiting the water duct on a side of the inner wall facing away from the water duct is directly followed by a guide duct of the first medium to be expanded. 1100. A turbocharger () , comprising:{'b': '1', 'a turbine () for expanding a first medium; and'}{'b': 50', '1, 'a compressor () for compressing a second medium utilizing energy extracted in the turbine () during the expansion of the first medium,'}wherein:{'b': 1', '3', '4', '6, 'the turbine () comprises a turbine housing () with a turbine inflow housing () and a turbine rotor (),'}{'b': 50', '52', '51', '6', '7, 'the compressor () comprises a compressor housing () and a compressor rotor () coupled to the turbine rotor () via a shaft (),'}{'b': 3', '2', '2', '7, 'the turbine housing () and the compressor housing are each connected to a bearing housing (), arranged between the turbine housing and the compressor housing, in which bearing housing () the shaft () is mounted,'}{'b': 4', '17', '15', '4', '16', '4', '16', '4', '17', '16', '17', '18, 'the turbine inflow housing () is constructed in a spiral-like, one-piece and double-walled manner, a water duct () for conducting cooling water is formed between an outer wall () of the turbine inflow housing () and an outer wall () of the turbine inflow housing (), and the inner wall () of the turbine inflow housing () delimiting the water duct () is directly followed on ...

Compressor wheel of a radial compressor of an exhaust-gas turbocharger

A compressor wheel ( 1 ) of a radial compressor ( 2 ) of an exhaust-gas turbocharger ( 3 ), having a hub ( 8 ); and having two blade rows ( 9, 10 ) which are arranged adjacent to one another on the hub ( 8 ), a first blade row ( 9 ) forming the leading blade row, and the adjacent, second blade row ( 10 ) foaming the trailing blade row, wherein the number of blades ( 11 ) of the first blade row ( 9 ) is equal to the number of blades ( 12 ) of the second blade row ( 10 ).

Exhaust-Gas Turbocharger

An exhaust-gas turbocharger for an internal combustion engine has a turbine housing, in which a turbine wheel with a shaft is arranged rotatably. The shaft is mounted rotatably in a bearing housing via at least one piston ring adjacently with respect to the turbine wheel. The bearing housing has a lubricant inflow and a pressureless lubricant outflow for lubricating the shaft, wherein an insulating washer is provided which is clamped in by the turbine housing and the bearing housing and has an opening which is connected to the lubricant outflow in a manner which conducts a lubricant. Passage of lubricant out of the bearing housing into the turbine housing is avoided. 1. An exhaust-gas turbocharger for an internal combustion engine , comprising:a turbine housing in which a turbine wheel with a shaft is rotatably arranged, whereinthe shaft is rotatably mounted in a bearing housing by way of at least one piston ring adjacent to the turbine wheel, and the bearing housing has, for lubricating the shaft, a lubricant inlet and an unpressurized lubricant outlet, andbetween the turbine wheel and the bearing housing, a thermal disk is arranged, which is clamped by the turbine housing and the bearing housing and which has an opening connected in lubricant-conducting fashion to the lubricant outlet.2. The exhaust-gas turbocharger as claimed in patent claim 1 , further comprising:a lubrication gap between the shaft and the bearing housing adjacent to the piston ring which is connected in lubricant-conducting fashion to the lubricant outlet. This application is a continuation of PCT International Application No. PCT/EP2016/051636, filed Jan. 27, 2016, which claims priority under 35 U.S.C. §119 from German Patent Application No. 10 2015 204 563.3, filed Mar. 13, 2015, the entire disclosures of which are herein expressly incorporated by reference.The invention relates to an exhaust-gas turbocharger for an internal combustion engine having a turbine housing in which a turbine wheel ...

Rotary machine

A rotary machine includes: a pair of radial bearings for rotatably supporting a rotating shaft around a center axis; impellers fixed to the rotating shaft at positions separated from the radial bearings in a center axis direction; and additional masses fixed to the rotating shaft at positions separated from both the radial bearings and the impellers in the center axis direction, and applying a load to an entire circumference of the rotating shaft so as to move positions of amplitude increase regions where an amplitude in a radial direction of the rotating shaft starts to increase.

Gas turbine engine for an aircraft

A gas turbine engine for an aircraft includes an engine core with a turbine, a compressor, and a core shaft connecting them. The engine includes a fan, with a plurality of fan blades, located upstream of the core and a gearbox receiving an input from the core shaft and outputting drive so the fan is at a lower rotational speed than the core shaft. The turbine includes a plurality of stages of axially spaced rotor blades mounted on a rotor, which are surrounded by a turbine casing. The turbine has an inlet defined at an upstream end of a first stage of blades and an outlet defined at a downstream end of a last stage of blades and a ratio of the area of the outlet to the inlet is at between 2.5 and 3.5. This increases the pressure ratio of and power extracted from the turbine and the engine.

TURBINE

A turbine is provided with a turbine rotor blade, and a turbine housing having a scroll part extending along a circumferential direction of the turbine rotor blade. The scroll part is configured such that an A/R ratio of a flow passage area A to a distance R between an axis of the turbine rotor blade and a flow passage center of the scroll part has a concave distribution at least in a part of a graph where an abscissa represents a circumferential position around the axis of the turbine rotor blade and an ordinate represents the A/R ratio. 14-. (canceled)5. A turbine comprising:a turbine rotor blade;a turbine housing having a scroll part extending along a circumferential direction of the turbine rotor blade,wherein the scroll part having an inner peripheral edge defined by a virtual circle around an axis of the turbine rotor blade such as to contact a tongue part is configured such that an A/R ratio of a flow passage area A to a distance R between an axis of the turbine rotor blade and a flow passage center of the scroll part has a concave distribution at least in a part of a graph where an abscissa represents a circumferential position around the axis of the turbine rotor blade and an ordinate represents the A/R ratio.6. The turbine according to claim 5 ,wherein, provided that the circumferential position is θ at an inlet of the scroll part and a positional value of the circumferential position increases from the inlet toward an end of the scroll part, the scroll part is configured such that a rate of change of the A/R while the circumferential position changes from 0° to 90° is at least 1.2 times higher than a case where the A/R linearly decreases.7. The turbine according to claim 6 ,wherein the scroll part is configured such that the rate of change of the A/R while the circumferential position changes from 0° to 90° is at least 1.4 times higher than the case where the A/R linearly decreases.8. The turbine according to claim 5 ,wherein the scroll part is configured ...

METHODS FOR PRODUCING GAS TURBINE ENGINE ROTORS AND OTHER POWDERED METAL ARTICLES HAVING SHAPED INTERNAL CAVITIES

Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor. 1. A method for manufacturing a Gas Turbine Engine (GTE) rotor , the method comprising:consolidating a powdered metal body utilizing a Hot Isostatic Pressing (HIP) process to produce a rotor preform in which elongated sacrificial tubes are embedded, the elongated sacrificial tubes twisting about a rotational axis of the rotor preform and converging toward the rotational axis when moving in a fore-aft direction;directing a solvent into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolve the elongated sacrificial tubes and create shaped cavities within the rotor preform; andprior to or after chemical dissolution of the elongated sacrificial tubes, further processing the rotor preform to produce the GTE rotor.2. The method of further comprising filling the solvent inlet channels with a non-compressible material prior to consolidating the powdered metal body.3. The method of wherein the non-compressible material comprises a powder packing claim 2 , a liquid claim 2 , metal cores having melt points less than those of the elongated sacrificial tubes claim 2 , or a combination thereof.4. The method of wherein consolidating the powdered metal body comprises:positioning the elongated sacrificial ...

Turbocharger

A turbocharger, with a turbine for expanding a first medium and a compressor for compressing a second medium utilising energy extracted in the turbine during the expansion of the first medium. The turbine has a turbine housing and a turbine rotor. The compressor has a compressor housing and a compressor rotor coupled to the turbine rotor via a shaft. The turbine housing and the compressor housing are each connected to a bearing housing in which the shaft is mounted. The bearing housing is connected to a turbine inflow housing of the turbine housing via a compensation element. 1. A turbocharger , comprising a turbine housing', 'a turbine inflow housing of the turbine housing; and', 'a turbine rotor;, 'a turbine for expanding a first medium comprisinga shaft; a compressor housing; and', 'a compressor rotor coupled to the turbine rotor via the shaft;, 'a compressor for compressing a second medium utilising energy extracted in the turbine during expansion of the first medium, comprising'}a bearing housing arranged between the turbine housing and the compressor housing and to which the turbine housing and the compressor housing are each connected, and in which the shaft is mounted; anda compensation element that connects the bearing housing to the turbine inflow housing of the turbine housing.2. The turbocharger according to claim 1 , wherein the compensation element is connected to the turbine inflow housing at a radially outer section.3. The turbocharger according to claim 1 , wherein the compensation element is connected to the bearing housing at a radially inner section.4. The turbocharger according to claim 1 , wherein the compensation element seen in a radial direction claim 1 , comprises a wall that is one of:contoured in a manner of a bellows section andfollows a bent course.5. The turbocharger according to claim 1 , further comprising:a bearing housing cover connected to the bearing housing.6. The turbocharger according to claim 1 , wherein the compensation ...

ASSEMBLED TURBINE HOUSING

An exhaust gas turbine is provided. The exhaust gas turbine includes a first turbine housing part having insulating material extending along an interior surface and a second turbine housing part having insulating material extending along an interior surface, the second turbine housing part coupled to the first turbine housing part to form a volute directing exhaust gas to a turbine wheel. 1. A turbine housing , made from cast metal , for a turbocharger , provided with an insulating material for protection against high temperatures of an exhaust gas flow , comprising:a flow inlet duct;a turbine wheel housing which encloses a turbine wheel and is connected to the flow inlet duct; anda flow outlet duct which is connected to the flow inlet duct;wherein an exhaust gas flow path extends through the flow inlet duct, through the turbine wheel housing and through the flow outlet duct and the exhaust gas flow path has a wall which is adjacent to the exhaust gas flow; andwherein the turbine housing comprises at least two interconnected housing parts in which is formed in each case a region of the exhaust gas flow path, wherein each exhaust gas flow path region includes a section of the wall which is adjacent to the exhaust gas flow and the insulating material is provided along the exhaust gas flow path on the exhaust gas flow-facing side of the wall which is adjacent to the exhaust gas flow.2. The turbine housing as claimed in claim 1 , wherein the turbine wheel housing encloses the turbine wheel in a spiral profile.3. The turbine housing as claimed in claim 1 , wherein the exhaust gas flow path has at least one branch.4. The turbine housing as claimed in claim 3 , wherein the exhaust gas flow path has a branch in the flow inlet duct and a branch in the flow outlet duct claim 3 , and the branch in the flow inlet duct is fluidically interconnected with the branch in the flow outlet duct claim 3 , bypassing the turbine wheel housing.5. The turbine housing as claimed in claim 1 , ...

TURBINE

A turbine () includes: a turbine impeller chamber () having a tubular outflow portion (), from which an exhaust gas flows out in an outflow direction (F) substantially parallel to an axis (C) of a turbine impeller (); a bypass flow passage () bypassing the inside of the turbine impeller chamber; an outer duct () having an inner peripheral surface () that expands in diameter in the outflow direction from the outflow portion; and an inner duct () that extends in the outflow direction from the outflow portion. A diffuser flow passage () that expands in diameter in the outflow direction is disposed in the inner duct at least in a portion between the outflow portion and a distal end portion (). An outlet () of the bypass flow passage and a waste gate valve () that opens and closes the outlet are disposed on the inner peripheral surface. 1. A turbine that rotates an impeller by energy of a fluid , the turbine comprising:an impeller chamber rotatably housing the impeller and comprising an inflow portion of the fluid and an outflow portion, from which the fluid flows out in an outflow direction substantially parallel to an axis of the impeller;a bypass flow passage bypassing an inside of the impeller chamber;an outer duct having an inner peripheral surface that is substantially conical and expands in diameter in the outflow direction from the outflow portion; andan inner duct disposed on an inner side of the outer duct and being tubular and extending in the outflow direction from the outflow portion,wherein a diffuser flow passage that expands in diameter in the outflow direction is disposed in the inner duct at least in a portion between the outflow portion and a distal end portion of the inner duct, andan outlet of the bypass flow passage and a waste gate valve that opens and closes the outlet are disposed on the inner peripheral surface.2. The turbine according to claim 1 , wherein an outer flange that extends in a radial direction of the impeller is disposed on a distal ...

METHODS FOR PRODUCING GAS TURBINE ENGINE ROTORS AND OTHER POWDERED METAL ARTICLES HAVING SHAPED INTERNAL CAVITIES

Embodiments of a methods for producing gas turbine engine rotors and other powdered metal articles having shaped internal cavities are provided. In one embodiment, the method includes consolidating a powdered metal body utilizing a hot isostatic pressing process to produce a rotor preform in which elongated sacrificial tubes are embedded. Acid or another solvent is directed into solvent inlet channels provided in the elongated sacrificial tubes to chemically dissolving the elongated sacrificial tubes and create shaped cavities within the rotor preform. The rotor preform is subject to further processing, such as machining, prior to or after chemical dissolution of the elongated sacrificial tubes to produce the completed gas turbine engine rotor. 1. A method for manufacturing a Powdered Metal (PM) component , the method comprising:positioning elongated sacrificial tubes in a PM body, the elongated sacrificial tubes comprising solvent inlet channels and longitudinal axes along which the solvent inlet channels extend;consolidating the PM body utilizing a Hot Isostatic Pressing (HIP) process to produce a component preform in which the elongated sacrificial tubes are embedded;chemically dissolving the elongated sacrificial tubes by directing a solvent into the solvent inlet channels to create shaped cavities within the component preform; andprior to or after chemical dissolution of the elongated sacrificial tubes, further processing the component preform to produce the PM component.2. The method of further comprising providing internal reinforcement structures within the solvent inlet channels claim 1 , which resist collapse of the elongated sacrificial tubes during the HIP process.3. The method of further comprising filling the solvent inlet channels with a non-compressible material prior to consolidating the PM body.4. The method of further comprising dimensioning the solvent inlet channels to have diameters at least one half outer diameters of the elongated sacrificial ...

MIXED-FLOW TURBINE WHEEL

A mixed-flow turbine wheel includes: a plurality of rotor blades disposed on a circumferential surface of the hub at intervals in a circumferential direction and configured such that each of the plurality of rotor blades has a leading edge which includes, in a meridional view, an oblique edge portion where a distance between the leading edge and an axis of the rotational shaft decreases from a tip side toward a hub side, and a sensor detection surface having a flat shape and being applied with a marking which is detectable by an optical sensor device. The sensor detection surface is formed on at least one of the circumferential surface of the hub or an edge portion of a reference rotor blade being one of the plurality of rotor blades, such that, in the meridional view, a trailing-edge side angle of two angles formed between the axis of the rotational shaft and a normal of the sensor detection surface is smaller than a trailing-edge side angle of two angles formed between the axis of the rotational shaft and a normal of the oblique edge portion. 1. A mixed-flow turbine wheel , comprising:a hub fixed to a rotational shaft;a plurality of rotor blades disposed on a circumferential surface of the hub at intervals in a circumferential direction and configured such that each of the plurality of rotor blades has a leading edge which includes, in a meridional view, an oblique edge portion where a distance between the leading edge and an axis of the rotational shaft decreases from a tip side toward a hub side; anda sensor detection surface having a flat shape and being applied with a marking which is detectable by an optical sensor device,wherein the sensor detection surface is formed on at least one of the circumferential surface of the hub or an edge portion of a reference rotor blade being one of the plurality of rotor blades, such that, in the meridional view, a trailing-edge side angle of two angles formed between the axis of the rotational shaft and a normal of the ...

TURBOCHARGER TURBINE WHEEL AND TURBOCHARGER

РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2020 120 979 A (51) МПК F04D 29/00 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2020120979, 25.06.2020 (71) Заявитель(и): МАН Энерджи Солюшнз СЕ (DE) Приоритет(ы): (30) Конвенционный приоритет: 27.06.2019 DE 102019117298.5 Адрес для переписки: 101000, Москва, ул. Мясницкая, д. 13, стр. 5, ООО "Союзпатент", С.Б. Фелициной Стр.: 1 A 2 0 2 0 1 2 0 9 7 9 R U A (57) Формула изобретения 1. Колесо (1) турбины турбокомпрессора, содержащее диск (2) колеса и выполненные за одно целое с ним рабочие лопатки (3), причем рабочие лопатки (3) выполнены без внешнего бандажа, при этом рабочие лопатки (3) переходят в диск (2) колеса с образованием участка (4) заданной кривизны с заданным постоянным или переменным радиусом rf кривизны, причем для радиуса кривизны участка (4) кривизны первых рабочих лопаток (3) первой группы из первых рабочих лопаток (3) справедливо следующее отношение: 2,5% ≤ rf1·100/l ≤ 10%, где rf1 - постоянный или переменный радиус кривизны участка кривизны первых рабочих лопаток, а l - длина выходной кромки (6) первых рабочих лопаток, при этом радиус rf2 кривизны участка (4) кривизны вторых рабочих лопаток (3) второй группы из вторых рабочих лопаток (3) отличается от радиуса rf1 кривизны участка (4) кривизны первых рабочих лопаток (3) по демпфированию. 2. Колесо турбины по п. 1, отличающееся тем, что радиус rf2 кривизны участка (4) кривизны соответствующей второй рабочей лопатки (3) отличается от радиуса rf1 кривизны участка (4) кривизны первых рабочих лопаток (3) так, что радиус rf2 кривизны участка (4) кривизны соответствующих вторых рабочих лопаток (3) не удовлетворяет отношению для радиуса rf1 кривизны участка (4) кривизны первых рабочих лопаток (3). 3. Колесо турбины по п. 1 или 2, отличающееся тем, что у соответствующей второй рабочей лопатки (3) радиус rf2 кривизны участка (4) кривизны вторых рабочих лопаток (3) отличается от радиуса rf1 кривизны участка (4) ...

Device for separating a mix of air/oil

HOUSING ARRANGEMENT OF A TURBO ENGINEER

Turbine

터빈은 터빈 동익과, 터빈 동익의 둘레 방향을 따라서 연장되는 스크롤부를 갖는 터빈 하우징을 갖는다. 스크롤부는, 스크롤부의 유로 면적을 A로 하고, 스크롤부의 유로 중심으로부터 터빈 동익의 축선까지의 거리를 R로 하고, 터빈 동익의 축선의 주위에서의 둘레 방향 위치를 횡축으로 취하고, 거리 R에 대한 유로 면적 A의 비인 A/R을 종축으로 취한 그래프에 있어서, A/R이 적어도 일부에서 오목형의 분포를 갖도록 구성되어 있다. The turbine has a turbine rotor having a turbine rotor and a scroll portion extending along the circumferential direction of the turbine rotor. The scroll portion has a passage area of the scroll portion as A, a distance from the passage center of the scroll portion to the axial line of the turbine rotor as R, a circumferential position around the axial line of the turbine rotor as a horizontal axis, In the graph in which A / R, which is the ratio of the area A, is taken as the vertical axis, A / R is configured to have a concave distribution at least in part.

Gas turbine engine centrifugal impeller

In one embodiment a centrifugal impeller has an axis of rotation, a plurality of blades, and a plurality of pitches defined between the blades. A cavity may be formed in a back side of the impeller, opposite with at least one of the plurality of pitches. In one form the cavity may not extend below a radius determined according to a stress criteria or stress limitation.

Turbine

提供一种涡轮，其涡轮具有涡轮动翼和具有沿涡轮动翼的周向延伸的涡旋部的涡轮外壳。涡旋部在以涡旋部的流路面积为A、以从涡旋部的流路中心到涡轮动翼的轴线的距离为R、以在涡轮动翼的轴线周围的周向位置为横轴，以流路面积A相对于距离R的比即A/R为纵轴的曲线图中，A/R在至少一部分具有凹型的分布。

Turbine

터빈은 터빈 동익과, 터빈 동익의 둘레 방향을 따라서 연장되는 스크롤부를 갖는 터빈 하우징을 갖는다. 스크롤부는, 스크롤부의 유로 면적을 A로 하고, 스크롤부의 유로 중심으로부터 터빈 동익의 축선까지의 거리를 R로 하고, 터빈 동익의 축선의 주위에서의 둘레 방향 위치를 횡축으로 취하고, 거리 R에 대한 유로 면적 A의 비인 A/R을 종축으로 취한 그래프에 있어서, A/R이 적어도 일부에서 오목형의 분포를 갖도록 구성되어 있다.

Centrifugal impeller and turbo-machine

Центробежная турбомашина, содержащая корпус, роторный узел, содержащий по меньшей мере одно центробежное рабочее колесо для текучей среды, проходящей от впускной стороны рабочего колеса к его выпускной стороне, и уплотнение входного отверстия, проходящее между входным отверстием центробежного рабочего колеса и корпусом и предназначенное для предотвращения протечки текучей среды между корпусом и центробежным рабочим колесом. Указанное уплотнение имеет по меньшей мере первую часть, расположенную у впускной стороны, и последнюю часть, расположенную у выпускной стороны рабочего колеса, при этом диаметр последней части меньше диаметра первой части. Изобретение направлено на снижение протечки между корпусом и рабочим колесом турбомашины. 3 н. и 7 з.п. ф-лы, 5 ил. РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) (13) 2 601 909 C2 (51) МПК F01D 5/04 (2006.01) F04D 29/28 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ (21)(22) Заявка: ИЗОБРЕТЕНИЯ К ПАТЕНТУ 2014100858/06, 20.07.2012 (24) Дата начала отсчета срока действия патента: 20.07.2012 (72) Автор(ы): ЮРИШИ Джузеппе (IT), БРОГЕЛЛИ Риккардо (IT) (73) Патентообладатель(и): Нуово Пиньоне С.п.А. (IT) Приоритет(ы): (30) Конвенционный приоритет: (43) Дата публикации заявки: 10.09.2015 Бюл. № 25 R U 26.07.2011 IT CO2011A000029 (45) Опубликовано: 10.11.2016 Бюл. № 31 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 26.02.2014 (86) Заявка PCT: 2 6 0 1 9 0 9 (56) Список документов, цитированных в отчете о поиске: FR 2199386 A, 10.05.1974. US 0006039535 A1, 21.03.2000. RU 2403456 C1, 10.11.2010. US 0005890873 A1, 06.04.1999. (87) Публикация заявки PCT: WO 2013/014106 (31.01.2013) R U 2 6 0 1 9 0 9 Адрес для переписки: 191036, Санкт-Петербург, а/я 24, "НЕВИНПАТ" (54) ЦЕНТРОБЕЖНОЕ РАБОЧЕЕ КОЛЕСО И ТУРБОМАШИНА (57) Реферат: Центробежная турбомашина, содержащая между корпусом и центробежным рабочим корпус, роторный узел, содержащий по меньшей колесом. Указанное уплотнение имеет по меньшей мере одно ...

Impeller for aircraft engine

An impeller for a centrifugal compressor, the impeller rotatable about a central axis, has: an outer hub body including a first material and extending around the central axis, the outer hub body defining a gaspath face extending from an inlet to an outlet, the gaspath face extending radially away from the central axis from the inlet to the outlet; blades protruding from the gaspath face and circumferentially distributed around the central axis; and an inner hub body extending around the central axis, the inner hub body secured to the outer hub body, the outer hub body axially overlapping and extending around the inner hub body, the inner hub body made of a second material being more cold dwell resistant than the first material.

DOUBLE COMPRESSOR CENTRIFUGAL TURBOMACHINE

Turbomachine, comportant au moins deux compresseurs centrifuges (40, 42), chaque compresseur centrifuge comportant un aubage de rotor (49, 51), caractérisée en ce que les aubages de rotor des compresseurs centrifuges sont superposés radialement. Turbomachine, comprising at least two centrifugal compressors (40, 42), each centrifugal compressor comprising a rotor blade (49, 51), characterized in that the rotor blades of the centrifugal compressors are superimposed radially.

Device for separating an air/oil mixture

L’invention concerne un dispositif (1) de séparation d’un mélange air/huile comportant une entrée (8) de mélange air/huile, une enceinte (9) de réception d’huile, une conduite (11) de circulation d’air, au moins un élément filtrant (21) couplé en rotation à un arbre d’entraînement en rotation (12), le dispositif (1) étant conçu de façon à ce que le mélange issu de l’entrée (8) précitée débouche dans l’enceinte (9) et soit entrainé au travers de l’élément filtrant (21) entraîné en rotation, de sorte que l’huile contenue dans le mélange soit centrifugée radialement à l’extérieur de l’élément filtrant (21) et amenée dans l’enceinte de réception d’huile (9), l’air filtré débouchant dans la conduite de circulation d’air (11), caractérisé en ce que l’arbre d’entraînement en rotation (12) est couplé à une turbine (26) apte à être entraînée en rotation par au moins une partie du flux d’air filtré, la turbine (26) comprenant une sortie (29) du flux filtré qui débouche vers l’extérieur. The invention relates to a device (1) for separating an air/oil mixture comprising an inlet (8) for the air/oil mixture, an enclosure (9) for receiving oil, a conduit (11) for circulating air, at least one filter element (21) coupled in rotation to a rotation drive shaft (12), the device (1) being designed so that the mixture coming from the aforementioned inlet (8) emerges in the enclosure (9) and is drawn through the filter element (21) driven in rotation, so that the oil contained in the mixture is centrifuged radially outside the filter element (21) and brought in the oil receiving enclosure (9), the filtered air emerging into the air circulation pipe (11), characterized in that the rotation drive shaft (12) is coupled to a turbine (26) capable of being driven in rotation by at least part of the filtered air flow, the turbine (26) comprising an outlet (29) for the filtered flow which opens outwards.

DOUBLE COMPRESSOR CENTRIFUGAL TURBOMACHINE

Turbomachine, comportant au moins deux compresseurs centrifuges (40, 42), chaque compresseur centrifuge comportant un aubage de rotor (49, 51), caractérisée en ce que les aubages de rotor des compresseurs centrifuges sont superposés radialement.

Lead-in structure and fixing flange for turbo generator

一种用于在循环介质的循环作业中连接涡轮发电机的引入结构。上述的涡轮发电机(1)具有封闭在一个共同的壳体构件(20，30)内的一个涡轮(11)、一个发电机(13)以及一个可能有的供给泵(12)，上述的壳体构件(20，30)具有：至少一个用于导引热的蒸汽态的循环介质(8)进入涡轮(11)的第一导管；一个用于导引循环介质(9)排出涡轮(11)的第二导管(25)；和一个用于导引冷的液态循环介质(10a)进入例如供给泵(12)的第三导管(24)。该第三导管(24)具有一个最好是同心地设置在具有管形通道(26)的第二导管(25)周围的环形通道(23)。第一导管(21)具有一个最好同心地设置在第二导管(25)与第三导管(24)的环形通道(23)之间的环形通道(22)。安置上述引入结构的固定法兰(20)具有一个由压力介质控制的封闭阀(28)，该封闭阀使第二导管(25)的管形通道(26)通常保持在打开状态，并在壳体(30)分离时保持在封闭状态，上述的封闭阀(28)安置在管形通道(26)内。

Lead-in structure and a fixing flange for a turbo generator

The invention relates to a lead-in structure for coupling of a turbo generator in a circulating process of a circulating medium. The turbo generator includes a turbine and a generator as well as possibly also a feed pump enclosed in a common casing structure. The casing structure also includes at least a first duct for hot, steam-like circulating medium entering the turbine, a second duct for circulating medium exiting the turbine, and a third duct for cooled liquid circulating medium, which, for example, enters the feed pump. The third duct includes an annular channel that is placed, preferably concentrically, around the second duct, which includes an annular channel. The first duct includes an annular channel that is placed, preferably concentrically, between the second duct and the annular channel of the third duct. The fixing flange applying the lead-in structure may include a closing valve that is controlled with a pressurized medium and that is arranged to keep the tubular channel of the second duct normally open and to keep it closed for releasing the casing element, wherein the closing valve is placed inside the tubular channel.

Rotary machine

一种旋转机械，其具备：压缩部，其在壳体内配置于所述一对径向轴承之间，对流体进行压缩；膨胀部，其与所述压缩部并排地配置，使所述流体膨胀；以及推力轴承，其在所述轴线方向上配置于相对于所述压缩部及所述膨胀部而接近旋转轴的第一端部或第二端部的位置。在所述轴线方向上，在压缩部吸入口、压缩部喷出口、膨胀部吸入口以及膨胀部喷出口之中，所述压缩部吸入口配置于最接近所述第一端部的位置，所述膨胀部喷出口配置于最接近所述第二端部的位置。

Turbocharger

Runner for gas and exhaust gas turbines

Radial turbine

Exhaust gas turbocharger for combustion engine

In an exhaust gas turbocharger for an internal-combustion engine having a turbine wheel to which the exhaust gas can be supplied approximately axially via a first supply channel (7) below a predeterminable speed of the internal-combustion engine and radially, via this first and/or a second supply channel (8), above the predetermined speed, it is intended to improve the efficiency in the case of non-stationary operating conditions, i.e. particularly during acceleration in the partial load region of the internal-combustion engine. For this purpose, the flow region of the turbine is divided into a radially inner (5) and a radially outer (6) chamber, by means of an annular wall (4). In consequence, the turbine blades can have a different shape and characteristic in the two chambers. In particular, the outlet angle of the blades in the inner chamber, referred to the circumferential direction of the turbine wheel, can be smaller than that of the blades in the radially outer chamber. <IMAGE>

Partition wall for sealing the rear space of a centrifugal compressor

Die Zwischenwand (40) zur Abdichtung des Rückraums des Verdichterrades (71) eines Radialverdichters bezüglich eines von einem Lagergehäuse (30) umschlossenen Lagerraums weist einen umlaufenden, rotationssymmetrisch geformten Befestigungsflansch (41) auf, welcher zur Befestigung der Zwischenwand an dem benachbarten Lagergehäuse vorgesehen ist und welcher eine plane Kontaktfläche zur Auflage auf einer Kontaktfläche des Lagergehäuses aufweist. Dabei sind in den Befestigungsflansch mehrere Bohrungen (42, 43) auf einer virtuellen Kreislinie eingelassen, wobei die Bohrungen mindestens einen Sperrluftkanal (42) sowie mehrere, in Umfangsrichtung auf der virtuellen Kreislinie verteilt angeordnete Bohrungen (43) zur Aufnahme von Befestigungsmitteln (50) umfassen. Die Zwischenwand ist erfindungsgemäss als eine rotationssymmetrische Scheibe ausgebildet, welche in der Herstellung durch das Bearbeitungsverfahren Drehen und ohne weitere Fräsbearbeitung in ihre endgültige Form gebracht werden kann. Für die Sperrluftdurchführung ist lediglich ein Bohrer notwendig, welcher ebenfalls für das Anbohren der Bohrungen zur Aufnahme der Befestigungsmittel verwendet werden kann. Dadurch kann der Herstellungsprozess gegenüber einer herkömmlichen Zwischenwand vereinfacht werden. The intermediate wall (40) for sealing the rear space of the compressor wheel (71) of a radial compressor with respect to a storage space enclosed by a bearing housing (30) has a circumferential, rotationally symmetrical mounting flange (41) which is provided for fastening the intermediate wall to the adjacent bearing housing and which has a flat contact surface for resting on a contact surface of the bearing housing. A plurality of bores (42, 43) are embedded in a virtual circular line in the fastening flange, the bores comprising at least one sealing air channel (42) and several bores (43) arranged around the virtual circular line in the circumferential direction for receiving fastening means (50) , According to the ...

Device for power generation according to a rankine cycle

A device for power generation according to a Rankine cycle, in particular according to an organic Rankine cycle (ORC), comprises a turbine (16), for expanding a vapour of a working fluid, and at least one heat exchanger (18, 20, 22), through which the expanded vapour has to flow. The turbine (16) and the heat exchanger(s) (18, 20, 22) are contained in a vapour tight container (10). The turbine (16) is a radial-outward-flow type turbine having a shaft that is led in a sealed manner out of said container (10), an axial vapour inlet port arranged opposite the shaft and located inside the container (10), and a stator exhaust ring with stator exhaust blades defining peripheral vapour exhaust openings for discharging the expanded vapour directly into the vapour tight container (10), in which the expanded vapour flows through the heat exchanger(s) (18, 20, 22).

Radial turbine rotor for gas turbine engine

A radial turbine rotor associated with an engine includes a disk, and a plurality of blades spaced apart about a perimeter of the disk. Each blade includes a forward end, an aft end and a root. The radial turbine rotor includes a plurality of sectors, with each sector coupled to the root of a respective blade of the plurality of blades. Each sector of the plurality of sectors defines a first surface configured to contact a working fluid and a second surface configured to be coupled to the disk, and each sector of the plurality of sectors defines at least one pocket between the first surface and the second surface proximate the forward end that extends toward the aft end. The radial turbine rotor includes a feather seal slot defined between adjacent sectors of the plurality of sectors proximate the first surface.

Inlet system for a radial compressor with a wide flow range requirement

A radial compressor employs a compressor wheel having an inducer. An inlet air passage has a first region and a second region separated from the first region by a divider wall. The divider wall extends from an inlet plane of the inducer and connects the first region to a first air filter and said second region to a second air filter.

The compressor impeller of supercharging equipment

本发明涉及一种增压设备(2)的压缩机叶轮(1)，其具有毂(4)和叶片(5)以及还具有叶轮背(6)。此处，对本发明来说重要的是，叶轮背(6)具有：波浪形轮廓(13)，其从毂(4)在径向方向(7)上运行；区域(8、9、10、11)，它们从毂(4)在径向方向(7)上运行并且彼此毗连，即：第一凹形区域(8)；第二凸形区域(9)，其毗连第一凹形区域(8)；第三凹形区域(10)，其毗连第二凸形区域(9)；第四凸形区域(11)，其毗连第三凹形区域(10)。通过该方式，能够在很大程度上降低破裂趋势。

AXIAL STEAM TURBINE POWERED HIGH TEMPERATURE RADIAL

Partition for sealing the rear section of a radial compressor

Device for power generation according to a rankine cycle

A device for power generation according to a Rankine cycle, in particular according to an organic Rankine cycle (ORC), comprises a turbine (16), for expanding a vapour of a working fluid, and at least one heat exchanger (18, 20, 22), through which the expanded vapour has to flow. The turbine (16) and the heat exchanger(s) (18, 20, 22) are contained in a vapour tight container (10). The turbine (16) is a radial-outward-flow type turbine having a shaft that is led in a sealed manner out of said container (10), an axial vapour inlet port arranged opposite the shaft and located inside the container (10), and a stator exhaust ring with stator exhaust blades defining peripheral vapour exhaust openings for discharging the expanded vapour directly into the vapour tight container (10), in which the expanded vapour flows through the heat exchanger(s) (18, 20, 22).

Combined flow turbine impeller

混流式涡轮机叶轮具备多个动叶片，多个动叶片设于轮毂的周面，并构成为，在子午面观察时，多个动叶片各自的前缘包含前缘与旋转轴的轴线的距离从叶尖侧朝轮毂侧递减的斜缘部，其中，该混流式涡轮机叶轮具有平坦状的传感器检测面，该传感器检测面被加上了能够由光学传感装置检测出的标记，在子午面观察时，传感器检测面以如下方式形成于轮毂的周面和多个动叶片之一的基准动叶片的缘部中的至少一方：旋转轴的轴线与传感器检测面的法线所成的两个角度之中后缘侧的角度小于旋转轴的轴线与斜缘部的法线所成的两个角度之中后缘侧的角度。

Fluid recirculation turbine system

A rotor rotatably mounted within a turbocharger housing includes a turbine wheel and a shaft. The shaft connects the turbine wheel. The hub defines a turbine-wheel back-disk surface facing the portion of the housing containing the bearings, and the hub defines a blade-side surface. The turbine hub and the housing define a turbine-wheel back-disk cavity. The turbine hub forms a ring-shaped primary axial protrusion extending circularly around the turbine-wheel back-disk surface into a circular channel in the housing. The circular channel leads into a bypass that bypasses the turbine blades. A relief flow valve is placed in the bypass. The relief control valve is controlled to open when the bypass pressure is above a cutoff pressure, and close when it is below the cutoff pressure.

Steam turbine

The invention relates to a steam turbine having a mechanical nominal power of up to 500 kW for driving a generator, said steam turbine comprising a shaft (10), a steam inlet and an open radial impeller (6, 12) that is connected to the shaft (10) in a rotationally fixed manner and can be impinged upon by steam through the steam inlet.

A rotor.

Un rotor 18, para usarse con un generador de flujo de fluido o un reactor al flujo de fluido, para que el rotor rote alrededor de un eje central 19, teniendo una superficie que define una trayectoria de fluido arqueada para el flujo de fluido alrededor del eje central, alrededor del cual el rotor puede rotar, en donde la superficie tiene la configuracion de una curva logarítmica básicamente de acuerdo a la progresion matemática conocida como seccion dorada o progresion de Fibonacci.

Blade clearance control for gas turbine engine

Fastener arrangement for rotating group of turbomachine

A turbomachine includes a housing and a rotating group that is supported for rotation about an axis within the housing. The rotating group includes a rotor shaft, a wheel, and a fastener that clamps the wheel to the rotor shaft. The fastener is unitary and includes a head and a shank. The shank includes a piloting feature on an arcuate surface that faces radially outward with respect to the axis. The shank is received in the wheel and is attached to the rotor shaft with the piloting feature being piloted to an arcuate inner radial surface of the wheel. The head abuts an axial surface of the wheel for axially clamping the wheel to the rotor shaft.

Sheet metal turbine housing with cast core

Turbine housing assemblies (200) and related turbocharger systems (100) are provided. One exemplary turbine housing assembly includes a core structure (220) having a voided inner region defining an axial outlet (222) and an outer surface defining an inner contour of a volute and an inner sheet metal shell (202, 204) having an inner base portion (203, 205) defining an inlet (700) in fluid communication with the volute and a volute portion (212) defining an outer contour of the volute, wherein at least a portion of the core structure defining the axial outlet extends in an axial direction through an opening in the inner sheet metal shell defined by the volute portion. The turbine housing assembly also includes an outer sheet metal shell (206, 208) surrounding the volute portion and including an outer base portion (223, 225) circumscribing the inner base portion.

A kind of compressor impeller of the runoff compressor of exhaust turbine supercharger

本发明涉及一种排气涡轮增压器(3)的径流压缩机(2)的压缩机叶轮(1)，其具有一个轮毂(8)；并且具有两个叶排(9，10)，这两个叶排被彼此相邻地安排在该轮毂(8)上，一个第一叶排(9)形成前叶排，并且该相邻的第二叶排(10)形成后叶排，其中该第一叶排(9)的叶片(11)数量等于该第二叶排(10)的叶片(12)数量。

A turbo generator casing structure

Rotor

Exhaust gas turbocharger for an internal-combustion engine

The exhaust gas flow of an internal-combustion engine is be supplied to a turbine wheel of a radial turbine through a gas duct arrangement in the turbine housing. A guiding device is controlled as a function of operational parameters of the internal combustion engine, by means of which the exhaust gas current can be rerouted into separate gas ducts of the duct arrangement. In order to achieve an improved behavior in the lower nonsteady speed range, one of the gas ducts opens at a front side of the turbine housing on the side of the turbine wheel shaft in the area of the moving blades of the turbine wheel.

Impeller for an exhaust gas turbocharger

Die Erfindung betriff ein Laufrad für einen Abgasturbolader, das einen Radrücken (14), einen Nabe (12) und mehrere Schaufeln (16), die sich zwischen dem Radrücken (14) und der Nabe (12) erstrecken, aufweist, wobei die Schaufeln (16) einen in axialer Richtung vom Radrücken (14) abgewandten Endbereich (24) aufweisen, der eine Endkante (20) trägt.Um den Durchsatz und den Wirkungsgrad zu erhöhen wird vorgeschlagen, dass der Endbereich (24) in einem Schnitt quer zur Endkante (20) zumindest teilweise ein teilelliptisches Profil (25) aufweist, wobei das teilelliptische Profil (25) eine kurze Achse (a) und eine lange Achse (b) aufweist. The invention relates to an impeller for an exhaust gas turbocharger comprising a Radrücken (14), a hub (12) and a plurality of blades (16) extending between the Radrücken (14) and the hub (12), wherein the blades ( 16) has an end region (24) which faces away from the wheel back (14) in the axial direction and carries an end edge (20). In order to increase the throughput and the efficiency, it is proposed that the end region (24) be cut transversely to the end edge (24). 20) at least partially has a teilelliptisches profile (25), wherein the partially elliptical profile (25) has a short axis (a) and a long axis (b).

Variable geometry nozzle for partitioned volute

An assembly can include an exhaust gas turbine housing that includes an inner wall and an outer wall that define a first exhaust gas channel and a second exhaust gas channel to a turbine wheel space where the inner wall includes an inner wall end at the turbine wheel space and the outer wall includes an outer wall end at the turbine wheel space; a first adjustable divider vane disposed adjacent to the inner wall end; a second adjustable divider vane disposed adjacent to the outer wall end; and at least one set of adjustable variable geometry nozzle vanes that define nozzle throats that direct flow of exhaust gas from one of the exhaust gas channels to the turbine wheel space.

Centrifugal impeller and turbomachine

A centrifugal turbomachine comprising a casing, a rotor assembly comprising at least one centrifugal impeller for a fluid flowing from an inlet side to an outlet side of the impeller, and an eye seal extending between an impeller eye of the centrifugal impeller and the casing for preventing the fluid from leaking between the casing and the centrifugal impeller, wherein the eye seal comprises at least a first portion toward the inlet side and a last portion toward the outlet side of the impeller, the last portion being smaller in diameter than the first portion.

A TURBOGENERATOR HOUSING STRUCTURE.

Una estructura de carcasa de turbogenerador para acoplar un turbogenerador a un proceso de circulación de un medio circulante, comprendiendo el turbogenerador (1) una turbina (11) y un generador (13) encerrado en la estructura de carcasa (20, 30) y comprendiendo la estructura de carcasa (20, 30) al menos un primer conducto (21) para medio circulante (8) de tipo vapor, caliente que entra en la turbina (11), un segundo conducto (25) para medio circulante (9) que sale de la turbina (11), y un tercer conducto (24) para medio circulante líquido enfriado (10a), caracterizado porque el tercer conducto (24) comprende un canal anular (23), a través del cual es conducido el medio circulante líquido enfriado y que está dispuesto en torno al segundo conducto (25), y porque el primer conducto (21) comprende un canal anular (22), a través del cual el medio circulante de tipo vapor, caliente es conducido para el suministro dentro de la turbina (11) y que está dispuesto entre el segundo conducto (25) y elcanal anular (23) del tercer conducto (24).

Rotary machine

A rotary machine includes a compression section that is disposed between the pair of radial bearings in a casing and compresses a fluid, an expansion section that is disposed side by side with the compression section and expands the fluid, and a thrust bearing that is disposed at a position close to a first end portion or a second end portion of a rotary shaft in an axial direction with respect to the compression section and the expansion section. Among a compression section suction port, a compression section discharge port, an expansion section suction port, and an expansion section discharge port, the compression section suction port is disposed at a position closest to the first end portion in the axial direction, and the expansion section discharge port is disposed at a position closest to the second end portion in the axial direction.

Variable-nozzle turbine with means for radial locating of variable-nozzle cartridge

A turbocharger having a variable-nozzle turbine formed by pivotable vanes supported by a nozzle ring includes an elastically deformable locator disposed between a radially outwardly facing surface of the center housing and an opposing surface of the nozzle ring. In one embodiment the locator is a metallic ring having a radially undulating waveform shape that repeats a plurality of times about a circumference of the locator. In another embodiment the locator is a metallic ring having a C-shaped cross-section in a radial-axial plane. In still another embodiment the locator is a metallic ring having an S-shaped cross-section in a radial-axial plane. In a further embodiment the locator is a plurality of circumferentially spaced, radial locator pins affixed in the center housing and received in radial slots formed in the nozzle ring, the pins restraining the nozzle ring circumferentially and axially, but allowing thermal expansion of the nozzle ring.

Rotary machine

A rotary machine includes: a pair of radial bearings for rotatably supporting a rotating shaft around a center axis; impellers fixed to the rotating shaft at positions separated from the radial bearings in a center axis direction; and additional masses fixed to the rotating shaft at positions separated from both the radial bearings and the impellers in the center axis direction, and applying a load to an entire circumference of the rotating shaft so as to move positions of amplitude increase regions where an amplitude in a radial direction of the rotating shaft starts to increase.

Turbomachinery with tiltable casing member

Blade clearance control for turbomachinery

Turbine wheel for a radial turbine