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Небесная энциклопедия

Космические корабли и станции, автоматические КА и методы их проектирования, бортовые комплексы управления, системы и средства жизнеобеспечения, особенности технологии производства ракетно-космических систем

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Мониторинг СМИ

Мониторинг СМИ и социальных сетей. Сканирование интернета, новостных сайтов, специализированных контентных площадок на базе мессенджеров. Гибкие настройки фильтров и первоначальных источников.

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Поддерживает ввод нескольких поисковых фраз (по одной на строку). При поиске обеспечивает поддержку морфологии русского и английского языка
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Применить Всего найдено 1633. Отображено 197.
17-09-2020 дата публикации

Номер: RU2017118252A3
Автор:
Принадлежит:

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13-04-2006 дата публикации

Turbolader

Номер: DE102004047103A1
Принадлежит:

Turbolader (1) für eine Brennkraftmaschine, mit einem in einem Verdichtergehäuse (2) angeordneten und von einem Antrieb drehbaren Verdichter zum Verdichten einer Ansaugluft für die Brennkraftmaschine, wobei die verdichtete Ansaugluft von dem Verdichter radial nach außen durch einen Ringspalt (3) in dem Verdichtergehäuse (2) gefördert wird und wobei eine offene Weite (A) des Ringspaltes von einem lageveränderbaren Element (4) veränderbar ist und wobei das lageveränderbare Element (4) aus einem elastischen Material ist. DOLLAR A Die vorgeschlagene Ausgestaltung führt zu einer Ausweitung des Verdichterkennfeldes zu hohen Massendurchsätzen bei gleichzeitiger Gewährleistung eines guten Wirkungsgrades bei niedrigen Massenströmen.

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05-01-2012 дата публикации

Turbine für einen Abgasturbolader sowie Verbrennungskraftmaschine mit einer solchen Turbine

Номер: DE102011016529A1
Принадлежит:

Die Erfindung betrifft eine Turbine (44) für einen Abgasturbolader (20) einer Verbrennungskraftmaschine (10), mit einem von Abgas der Verbrennungskraftmaschine (10) durchströmbaren Turbinengehäuse (50), in welchem ein Turbinenrad (66) um eine Drehachse (22) drehbar zumindest bereichsweise aufgenommen ist und welches wenigstens zwei, jeweils von zumindest einem Teil des Abgases durchströmbare und zumindest bereichsweise fluidisch voneinander getrennten Fluten (42, 48) aufweist, welchen jeweils wenigstens eine Düse (70, 72) zugeordnet ist, über welche zum Beaufschlagen des Turbinenrads (66) mit Abgas das die jeweilige Flut (42, 48) durchströmende Abgas dem Turbinenrad (66) zuführbar ist, wobei zumindest einer ersten der Düsen (70, 72) eine erste Verstelleinrichtung (74) zugeordnet ist, mittels welcher ein von dem die zugehörige Flut (70, 72) durchströmendem Abgas durchströmbarer Strömungsquerschnitt (S, SAGR) der ersten Düse (70, 72) variabel einstellbar ist, und dass eine zweite, zumindest ...

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07-01-2010 дата публикации

Sliding sleeve system for use in turbine wheel entrance of turbo-charger of motor vehicle, has vertical section profile arranged at distance and parallel to base-side basic profile, and changed with respect to basic profile

Номер: DE102008032497A1
Автор: KUHN THOMAS, KUHN, THOMAS
Принадлежит:

The system has a control device with a base and a rotor blade element (18), where the blade element has a base-side basic profile (G). The rotor blade element is extended from the base along a component axis of the control device over a predetermined blade height. A sliding sleeve is moved relative to the control device, and comprises a receiver in which the rotor blade element is accommodated. A vertical section profile (HS) arranged at a distance and parallel to the base-side basic profile is changed with respect to the basic profile.

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22-11-1989 дата публикации

Variable geometry turbine

Номер: GB0002218743A
Принадлежит:

A mounting assembly for a movable annular wall member of an inlet passageway of a variable geometry turbine. The inlet passageway is defined between the movable wall and a facing wall. The wall member is formed from a sheet material and is supported on a plurality of pins which extend parallel to the direction of movement of the wall member. The wall member comprises a tubular portion extending away from the facing wall and each pin supports a radial extending link. Each link is engaged in a respective slot in the tubular portion of the wall member, the links being a relatively close fit in the direction of movement of the wall member and a relatively loose fit in the circumferential direction.

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21-06-1989 дата публикации

Turbocharger having slidable sleeve for controlling admission to turbine

Номер: GB0002210933A
Принадлежит:

An exhaust-gas turbocharger for an internal-combustion engine is described, its turbine having a double flow housing with two channels for supplying the exhaust gases to the turbine wheel, of which on channel can be closed off as a function of a variable operating parameter by means of a sliding sleeve which is mounted in the housing so as to be axially displaceable by means of a control device. To ensure a clearly defined relationship between the adjustment of the sliding sleeve and the input variables and to create a heat-resistant control device, the sliding sleeve is connected to an axially fixed and circumferentially rotable driving ring via a positive sliding fit driving the sliding sleeve in the circumferential direction, a slot pin fixed to the housing engaging into an oblique helical groove in the sliding sleeve, and a shaft engaging on the driving ring via a positive connection and being guided radially out of the housing via a bearing in the latter.

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10-03-2004 дата публикации

Turbocharger apparatus

Номер: GB0000402771D0
Автор:
Принадлежит:

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08-01-2003 дата публикации

Variable geometry turbine

Номер: GB0000228237D0
Автор:
Принадлежит:

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26-10-2005 дата публикации

Variable turbocharger apparatus with bypass means for bypassing exhaust gases

Номер: GB0000518883D0
Автор:
Принадлежит:

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10-11-2010 дата публикации

Variable geometry turbine

Номер: GB0002470166A
Принадлежит:

A variable geometry turbine comprises: a turbine wheel (5) mounted within a housing assembly (1) for rotation about a turbine axis, the housing assembly defining a radial gas flow inlet passage (9); an annular wall member (11) defining one wall of the inlet passage and which is displaceable in a direction parallel to the turbine axis to control gas flow through the inlet passage; and a linkage mechanism comprising at least one actuating member (16) operably connected to the annular wall member to control displacement of the wall member. The actuating member extends in a direction parallel to the turbine axis through an aperture (29) defined by a retaining member (24) such that a first bearing surface defined by the actuating member extending transverse to the turbine axis is contacted by a surface of the retaining member so as to connect the actuating member to the annular wall member. The aperture is dimensioned to define a clearance (30) between a wall of the aperture and a portion of ...

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04-06-2008 дата публикации

Method for controlling the exhaust gas temperture for after-treatment systems on a diesel engine using a variable geometry turbine

Номер: GB0000807722D0
Автор:
Принадлежит:

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15-12-1982 дата публикации

CASING FOR A TURBINE ROTOR

Номер: GB0002035467B
Автор:
Принадлежит: CUMMINS ENGINE CO INC

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12-09-2012 дата публикации

A variable geometry turbine

Номер: GB0201213456D0
Автор:
Принадлежит:

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31-12-2014 дата публикации

Variable geometry turbocharger turbine

Номер: GB0201420559D0
Автор:
Принадлежит:

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10-08-1983 дата публикации

VARIABLE INLET AREA TURBINE

Номер: GB0008318489D0
Автор:
Принадлежит:

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13-09-2006 дата публикации

Variable geometry turbine

Номер: GB0000615495D0
Автор:
Принадлежит:

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06-05-2009 дата публикации

Turbocharger

Номер: GB0000905038D0
Автор:
Принадлежит:

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30-04-2008 дата публикации

Variable geometry turbine

Номер: GB0000805519D0
Автор:
Принадлежит:

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15-11-2009 дата публикации

TURBOCHARGER WITH A COMPRESSOR WITH TWO BACK MOVING FORWARD IMPELLERS

Номер: AT0000446452T
Принадлежит:

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15-01-2012 дата публикации

VARIABLE TURBOCHARGER DEVICE WITH BYPASS MEANS FOR REROUTING EXHAUST GASES

Номер: AT0000540212T
Принадлежит:

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30-04-2004 дата публикации

SLIDE VANE TURBOCHARGER

Номер: AU2003264764A1
Принадлежит:

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09-08-1984 дата публикации

SURGE CONTROL IN CENTRIFUGAL COMPRESSOR

Номер: AU0000538286B2
Принадлежит:

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19-02-2016 дата публикации

LOW NOISE AEROENGINE INLET SYSTEM

Номер: CA0002900401A1
Принадлежит:

An aeroengine has an inlet system which includes at least one deformable wall disposed adjacent a peripheral wall of an inlet duct and a plurality of acoustic cells attached to a back side in fluid communication through respective holes in the at least one deformable wall with an inlet duct air flow. The at least one deformable wall selectively forms part of the peripheral wall of the inlet duct when in an undeployed position and selectively forms a curved profile projecting into the inlet duct to reduce line-of-sight noise propagation through he inlet duct.

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28-02-2018 дата публикации

BLOCKER DOOR ASSEMBLY HAVING A THERMOPLASTIC BLOCKER DOOR FOR USE IN A TURBINE ENGINE

Номер: CA0002970697A1
Принадлежит:

A blocker door assembly for use in a gas turbine engine includes a facesheet including a plurality of openings to facilitate noise attenuation and a body portion coupled to the facesheet. The body portion includes a backsheet integrally formed with a honeycomb core, wherein the body portion is molded from a thermoplastic material.

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16-04-1928 дата публикации

Kreiselmaschine.

Номер: CH0000125547A
Принадлежит: SIMMEN OSCAR

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30-04-1961 дата публикации

Turbomaschine mit radial angeordnetem Diffusor

Номер: CH0000353837A
Автор:

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15-05-1966 дата публикации

Turbomaschine

Номер: CH0000413202A

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15-05-1966 дата публикации

Einstellvorrichtung für verstellbaren Radialdiffusor

Номер: CH0000413201A

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15-06-1961 дата публикации

Turbomaschine

Номер: CH0000354887A
Автор:

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31-07-1961 дата публикации

Zentrifugalfördermaschine

Номер: CH0000355889A
Автор:

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31-10-1962 дата публикации

Radialturbine für kompressible Arbeitsmedien

Номер: CH0000365088A

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15-06-1984 дата публикации

HOUSING WITH A OF IT UMSCHLOSSENEN TURBINE.

Номер: CH0000643631A5
Автор: PAUL M. CHAPPLE

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14-12-1984 дата публикации

RADIAL COMPRESSOR.

Номер: CH0000646757A5
Автор: BOLLETER ULRICH DR
Принадлежит: SULZER AG, SULZER (GEBR.) AG

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15-07-1991 дата публикации

MOBILE RING FOR THE PART-LOAD PRICE INCREASE OF A CENTRIFUGAL TURBO COMPRESSOR WITH BLADED DIFFUSER.

Номер: CH0000677956A5
Принадлежит: CARRIER CORP, CARRIER CORPORATION

In a centrifugal compressor having a number of fixed vanes 48 on its outlet side, an axially movable sleeve 41 is provided upstream of the vanes. The sleeve can be moved by fluid pressure in a conduit 65 controlled by valve 51. The compressor also has inlet guide vanes 12 which are adjustable by a control system (33, Fig. 1) in a refrigeration system. ...

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29-07-2011 дата публикации

Variable inlet guide vane arrangement for a compressor.

Номер: CH0000702603A2
Принадлежит:

Eine variable Einlassleitschaufelanordnung (30) für einen Verdichter (18) enthält ein Gehäuse (40), das einen Einlass des Verdichters definiert, wenigstens einen Leitschaufelträger, der im Inneren des Gehäuses koaxial angeordnet. ist, mehrere Leitschaufeln (38), die in Umfangsrichtung um den Umfang des Gehäuses angeordnet sind, wobei jede Leitschaufel zwischen dem Gehäuse und dem wenigstens einen Leitschaufelträger schwenkbar montiert ist, einen Aktuatormechanismus (44, 46), der konfiguriert ist, um wenigstens einige der mehreren Leitschaufeln in einem asymmetrischen Muster um den Umfang des Gehäuses herum zu verschwenken. Ein Verfahren zur Steuerung einer variablen Einlassleitschaufelanordnung für einen Verdichter enthält ein Verschwenken wenigstens einiger der mehreren Leitschaufeln in einem asymmetrischen Muster um den Umfang des Gehäuses herum.

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30-04-1990 дата публикации

THE CONTROL APPARATUS OF A MOVABLE WALL AND METHOD FOR THE OPERATION OF THE APPARATUS.

Номер: CH0000674057A5
Автор: ZINSMEYER THOMAS M
Принадлежит: CARRIER CORP, CARRIER CORPORATION

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15-06-1989 дата публикации

PROCEDURES FOR STEERING A TURBOCOMPRESSOR AS WELL AS DEVICE TO WOULD DRIVE THROUGH THE PROCEDURE.

Номер: CH0000670482A5
Автор: LEONARD GARY S
Принадлежит: CARRIER CORP, CARRIER CORPORATION

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30-12-1988 дата публикации

Exhaust turbocharger with adjustable inlet - has blade ring on sleeve sliding on cylindrical surface

Номер: CH0000668455A5

The exhaust turbocharger has a turbine inlet of adjustable cross-section, the turbine and compressor rotors being fixed to a common shaft. Adjustment is by a sliding sleeve (4), with a blade ring (5) at one end. A covering strip (7) joins the ends of the blades (6) together. The sleeve is guided in a cylindrical surface outside the rotor periphery in the radial direction. Stop faces (10,11) define the fully-retracted and fully-extended positions of the ring. ADVANTAGE - Avoidance of leaks or of clogging by soot.

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31-08-2021 дата публикации

Turbolader.

Номер: CH713305B1

Turbolader, mit einer Turbine (2) zur Entspannung eines ersten Mediums, mit einem Verdichter zur Verdichtung eines zweiten Mediums unter Nutzung von in der Turbine (2) bei Entspannung des ersten Mediums gewonnener Energie, wobei die Turbine (2) ein Turbinengehäuse und einen Turbinenrotor (5) aufweist, wobei der Verdichter ein Verdichtergehäuse und einen mit dem Turbinenrotor (5) über eine Welle (8) gekoppelten Verdichterrotor (7) aufweist, wobei das Turbinengehäuse und das Verdichtergehäuse jeweils mit einem zwischen denselben angeordneten Lagergehäuse (9), in welchem die Welle (8) gelagert ist, verbunden sind, wobei das Turbinengehäuse ein Zuströmgehäuse, einen Düsenring (15) mit Leitschaufeln (16) sowie ein Einsatzstück (13) aufweist, und wobei der Düsenring (15) über einen Vorsprung (17) am Lagergehäuse (9) zentriert und radial geführt ist.

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30-12-2019 дата публикации

Steuerstufe für eine radial-axiale Dampfturbine.

Номер: CH0000715115A2
Принадлежит:

Steuerstufe zur Regulierung von Dampfzufuhr bei Teilastbetrieb einer axialen Dampfturbine. Um zusätzliche Energieverluste, die durch thermische und dynamische Spannung im Teillastbetrieb entstehen, zu reduzieren, wird das erste Leitradgitter (4), welches dicht von einer Steuerplatte (2) umgeben ist, axial, das heisst senkrecht, zu allen folgenden Stufen der Turbine montiert. Die Leitschaufeln (4) der Steuerstufe müssen ungekrümmt sein, damit die Platte (2) frei vor und zurück entlang der Schaufeln bewegt werden kann und dadurch die Dampfzufuhr reguliert wird. Die Steuerstufe kann bei Turbinen mit seitlicher wie auch mit zentraler Dampfzufuhr verwendet werden.

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29-06-2018 дата публикации

Turbocharger.

Номер: CH0000713305A2
Принадлежит:

Turbolader, mit einer Turbine (2) zur Entspannung eines ersten Mediums, mit einem Verdichter zur Verdichtung eines zweiten Mediums unter Nutzung von in der Turbine (2) bei Entspannung des ersten Mediums gewonnener Energie, wobei die Turbine (2) ein Turbinengehäuse und einen Turbinenrotor (5) aufweist, wobei der Verdichter ein Verdichtergehäuse und einen mit dem Turbinenrotor (5) über eine Welle (8) gekoppelten Verdichterrotor (7) aufweist, wobei das Turbinengehäuse und das Verdichtergehäuse jeweils mit einem zwischen denselben angeordneten Lagergehäuse (9), in welchem die Welle (8) gelagert ist, verbunden sind, wobei das Turbinengehäuse ein Zuströmgehäuse, einen Düsenring (15) mit Leitschaufeln (16) sowie ein Einsatzstück (13) aufweist, und wobei der Düsenring (15) über einen Vorsprung (17) am Lagergehäuse (9) zentriert und radial geführt ist.

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30-10-2020 дата публикации

Turbocharger.

Номер: CH0000716127A2
Принадлежит:

Turbolader, mit einer Turbine (2) zur Entspannung eines ersten Mediums und mit einem Verdichter zur Verdichtung eines zweiten Mediums. Die Turbine (2) weist ein Turbinengehäuse (4) und einen mit Turbinen-Laufschaufeln (14) beschaufelten Turbinenrotor (5) auf, wobei radial äußere Kanten (14a) der Turbinen-Laufschaufeln (14) und ein den Turbinen-Laufschaufeln (14) zugewandter Abschnitt des Turbinengehäuses (4) oder eines mit dem Turbinengehäuse (4) verbundenen statorseitigen Bauteils (13) einen turbinenseitigen Spalt definieren. Der Verdichter weist ein Verdichtergehäuse und einen mit dem Turbinenrotor über eine Welle (8) gekoppelten, mit Verdichter-Laufschaufeln beschaufelten Verdichterrotor auf, wobei radial äußere Kanten der Verdichter-Laufschaufeln und ein den Verdichter-Laufschaufeln zugewandter Abschnitt des Verdichtergehäuses oder eines mit dem Verdichtergehäuse verbundenen statorseitigen Bauteils einen verdichterseitigen Spalt definieren. Das Turbinengehäuse (4) und das Verdichtergehäuse ...

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25-06-2007 дата публикации

СПОСІБ РЕГУЛЮВАННЯ ДОЦЕНТРОВОЇ ТУРБІНИ З БЕЗЛОПАТКОВИМ НАПРАВЛЯЮЧИМ АПАРАТОМ

Номер: UA0000079451C2

Винахід належить до області турбінобудування, а саме до способів регулювання доцентрової турбіни. В способі регулювання доцентрової турбіни з безлопатковим направляючим апаратом, заснованому на регулюванні пропускної здатності турбіни шляхом зміни площі прохідного перерізу розгінної ділянки завитки, зміну площі прохідного перерізу розгінної ділянки завитки здійснюють за рахунок криволінійно-поступального руху профільованого елемента по або проти потоку газу, що входить у завитку, при цьому геометричну форму, розташування і величину площі прохідного перерізу розгінної ділянки завитки визначають криволінійно-поступальним рухом профільованого елемента по пропускній здатності.

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24-02-1978 дата публикации

ENGINE SPARK-IGNITION PROVIDED With a TURBOCOMPRESSOR OF OVERFEEDING HAS EXHAUST FUMES

Номер: FR0002359973A1
Автор: [UNK]
Принадлежит: Kloeckner Humboldt Deutz AG

a. Moteur à explosion muni d'un turbocompresseur de suralimentation à gaz d'échappement b. Moteur caractérisé en ce qu'une roue à aubes est entourée sur une partie de sa largeur par un tiroir tubulaire qui commande par déplacement axial un des conduits 3 des conduits jumelés. c. L'invention s'applique notamment à un moteur suralimenté par un compresseur dont la turbine comporte un carter à double flux à conduits jumelés. at. Internal combustion engine fitted with an exhaust gas supercharging turbocharger b. Motor characterized in that a paddle wheel is surrounded over part of its width by a tubular slide which controls by axial displacement one of the ducts 3 of the twin ducts. vs. The invention applies in particular to an engine supercharged by a compressor, the turbine of which comprises a double-flow casing with twin ducts.

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05-02-2016 дата публикации

AIR CIRCULATION DEVICE WITH ADJUSTABLE FLOW RATE FOR AIRCRAFT TURBOMACHINE

Номер: FR0003024496A1
Принадлежит: SNECMA

Il est proposé un dispositif (1) de circulation d'air pour turbomachine d'aéronef, comprenant deux flancs (2, 3) entre lesquels un passage d'air (C) est ménagé, l'un (2) des deux flancs comprenant consécutivement le long du passage d'air (C) une première paroi (4), une deuxième paroi (5) qui prolonge la première paroi (4) et présente une première extrémité (54) et une deuxième extrémité (56) opposées, et une troisième paroi (6), fixe relativement à la première paroi (4), qui prolonge la deuxième paroi (5). Au moins une partie de la deuxième paroi (5) comprenant la première extrémité (54) est mobile par rapport à la première paroi (4) de sorte à faire varier une section (S) du passage d'air (C), ladite première extrémité (54) étant adaptée pour coulisser le long de la première paroi (4).

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01-08-1984 дата публикации

CENTRAL OUTLET TURBOCHARGER SPIRAL HOUSING

Номер: KR19840001097B1
Автор: Chapple, Panl M.
Принадлежит:

The housing(12) is intended for the rotor(11), partic for a turbo-charger, and has a radially outer inlet(13), a spiral duct(P) and a radially inner outlet(14) enclosing the rotor periphery. The duct has two symmetrically contoured side walls, whose internal dia. (14A) approximately equals the outer dia. of the rotor. The outer wall(12A) is parallel to the rotor axis(9) and follows a spiral shape over at least 360≨C. The radial position of this wall relative to the rotor axis is defined by the path followed by free whirl flow between the side walls. Copyright 1997 KIPO ...

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08-03-2018 дата публикации

BLOCKER DOOR ASSEMBLY HAVING THERMOPLASTIC BLOCKER DOOR FOR USE IN TURBINE ENGINE

Номер: KR1020180025172A
Принадлежит:

A blocker door assembly for use in a gas turbine engine includes a facesheet including a plurality of openings to facilitate noise attenuation and a body portion coupled to the facesheet. The body portion includes a backsheet integrally formed with a honeycomb core, wherein the body portion is molded from a thermoplastic material. COPYRIGHT KIPO 2018 ...

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06-03-2018 дата публикации

conjunto de válvula para um motor de turbina a gás

Номер: BRPI0602928B1
Принадлежит:

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14-04-2011 дата публикации

TURBOMACHINE

Номер: WO2011042691A2
Принадлежит:

A variable geometry turbine comprising a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; and a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the inlet; wherein the annular inlet is divided into a first annular inlet portion and a second annular inlet portion axially offset from the first inlet portion, inlet vanes extending axially into each of the first and second inlet portions, the inlet vanes defining axially adjacent inlet passages; wherein the configuration of the inlet vanes extending into the first inlet portion differs from the configuration of the inlet vanes extending into the second inlet portion in that the vanes extending into the first inlet portion are circumferentially offset from the vanes extending into the second inlet portion.

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25-08-2011 дата публикации

TURBINE FOR AN EXHAUST GAS TURBOCHARGER

Номер: WO2011101005A1
Принадлежит:

The invention relates to a turbine (10) for an exhaust gas turbocharger, comprising a turbine housing (12), in which a turbine wheel that can be exposed to a waste gas of an internal combustion engine is accommodated and which has at least two channels (14, 16), which are fluidically separated from each other at least in some sections and through which the exhaust gas can flow, and at least one valve (22), which can be moved between a closed position that closes at least one bypass channel (20) and at least one open position that releases the bypass channel at least in some sections and by means of which the turbine wheel can be bypassed at least by part of the exhaust gas, wherein the at least two channels (14, 16) are fluidically separated from each other by the valve (22) at least in some sections in a separating section (24) in at least one position of the valve (22), wherein the valve (22) has at least one intermediate position, in which the bypass channel (20) is closed and the at ...

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31-03-2005 дата публикации

TURBOCHARGER COMPRISING A COMPRESSER HAVING TWO BACK-TO-BACK IMPELLERS

Номер: WO2005028877A3
Принадлежит:

Turbochargers of this invention comprise a turbine housing and a turbine wheel rotatably disposed therein. A center housing is connected to the turbine housing, and a compressor housing is attached to the center housing. A compressor is rotatably disposed within the compressor housing, and comprises two impellers placed in back-to-back orientation. A movable member is disposed within the compressor housing to downstream of the compressor to control the flow of air within the compressor housing. The position of the movable member can be operated to control the amount of pressurized air that is produced by one of the compressor impellers to provide enhanced compressor operating efficiency throughout the operating range and mass flow requirements of the engine.

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02-01-2014 дата публикации

NON-LINEAR ASYMMETRIC VARIABLE GUIDE VANE SCHEDULE

Номер: US20140003909A1
Принадлежит: General Electric Company

A variable inlet guide vane arrangement for a compressor includes a case defining an inlet of the compressor; at least one vane support coaxially disposed within the case; a plurality of vanes circumferentially disposed around the circumference of the case, each vane being pivotally mounted between the case and the at least one vane support; an actuator mechanism configured to pivot at least some of the plurality of vanes in an asymmetrical pattern around the circumference of the case. A method of controlling a variable inlet guide vane arrangement for a compressor includes pivoting at least some of the plurality of vanes in an asymmetrical pattern around the circumference of the case. 1. A method of controlling a variable inlet guide vane arrangement for a compressor comprising a case defining an inlet of the compressor , at least one vane support coaxially disposed within the case , a plurality of vanes circumferentially disposed around the circumference of the case , each vane being pivotally mounted between the case and the at least one vane support , and an actuator mechanism configured to pivot at least some of the plurality of vanes , the method comprising:pivoting at least some of the plurality of vanes in an asymmetrical pattern around the circumference of the case.2. A method according to claim 1 , wherein pivoting the vanes in an asymmetrical pattern comprises pivoting at least some of the plurality of vanes according to a non-linear schedule or alternating linear schedules during a portion of pivoting of the plurality of vanes from a fully closed to a fully open position.3. A method according to claim 2 , wherein at least some of the plurality of vanes are pivoted according to the non-linear schedule or alternating linear schedules at an onset of separation of a flow from said at least some of the plurality of vanes.4. A method according to claim 3 , further comprising pivoting at least some of the plurality of vanes according to a linear schedule to ...

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23-10-2012 дата публикации

Variable geometry turbine

Номер: US0008291703B2

A variable geometry turbine has a gas inlet chamber and a gas flow inlet passage downstream of the inlet chamber and upstream of said turbine wheel. The inlet passage is defined between a moveable first wall and a second wall and an actuator is operable to control displacement of the first wall in order to vary the size of the gas flow inlet passage. A piston member defining the first wall or being connected to it is received in a piston chamber and serves to move the first wall as a result of displacement of the piston member in the piston chamber. A bypass passage defined in the housing and extends between the piston chamber and a location in the turbine upstream of the inlet passage for delivering gas to the piston chamber. The bypass passage is disposed such that gas introduced through the bypass passage pressurizes the chamber and applies a force to displace the piston member in a direction that causes the first wall to move towards the second wall. The gas, which may be the exhaust ...

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31-10-1989 дата публикации

Vaned diffuser control

Номер: US0004877369A
Автор:
Принадлежит:

An improved diffuser includes a plurality of vanes and an exit type throttle. The vanes maybe high solidity vanes.

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12-12-2000 дата публикации

Actuating mechanism for sliding vane variable geometry turbine

Номер: US0006158956A
Автор:
Принадлежит:

A variable geometry system for a turbocharger includes a sliding piston disposed within a turbine housing between a primary exhaust gas volute and turbine blades. The sliding piston is axially displaceable within the turbine housing to increase or decrease the volumetric flowrate of exhaust gas to the turbine. The sliding piston is positioned by an actuator having reciprocating movement translated through a rotating sleeve with a first pin engaging a helical slot for axial motion of the piston and a second pin engaging an alignment slot for maintaining axial alignment of the piston.

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13-01-2009 дата публикации

Valve assembly for a gas turbine engine

Номер: US0007475532B2

A method for channeling compressed air to a gas turbine engine augmentor is provided. The method includes coupling an annular slide valve to a gas turbine engine separation liner, coupling a valve seat to a gas turbine engine diffuser such that an airflow passage is defined between the annular slide valve and the valve seat, and channeling compressed air to the annular slide valve to facilitate regulating the quantity of fan bypass air channeled to the gas turbine engine augmentor.

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22-07-2014 дата публикации

Variable geometry turbine

Номер: US8784039B2

A variable geometry turbine comprising: a housing; a turbine wheel supported within said housing for rotation about a turbine axis; an annular inlet passage within said housing upstream of said turbine wheel and defined between respective radial inlet surfaces of first and second wall members; an outlet passage within said housing downstream of said turbine wheel; an array of vanes extending across the inlet passage, said vanes being connected to said first wall member; at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage and/or at least one of said vanes being rotationally moveable about an axis that is substantially parallel to said turbine axis to vary the size of the inlet passage; wherein at least one particulate filter is provided within said housing at a location such that said particulate filter can be contacted by particulate matter flowing through said turbine during use.

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19-12-2007 дата публикации

VARIABLE GEOMETRY TURBINE FOR A TURBOCHARGER AND METHOD OF CONTROLLING THE TURBINE

Номер: EP0001866520A1
Принадлежит:

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29-12-2010 дата публикации

HYDRAULIC SERVO-DRIVE DEVICE AND VARIABLE TURBO-SUPERCHARGER USING THE SAME

Номер: EP2267316A1
Принадлежит:

A hydraulic servo drive device includes: a pilot spool (20) for switching supply and shutoff of oil; a servo piston (11) slid in accordance with the pilot spool (20); a stroke sensor (15) for detecting a displacement of the servo piston (11); a first hydraulic chamber (51) in which oil for moving the servo piston (11) is flowed; a first piston oil path (65) for communicating a pump port to which oil is supplied from a pump with a first hydraulic chamber (51); and a discharge circulating oil path (66) for communicating the first hydraulic chamber (51) with a drain port.

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10-10-2012 дата публикации

A turbine

Номер: EP2508714A2
Принадлежит:

According to an aspect of the invention, there is provided a variable geometry turbine comprising: a turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; and a cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the annular inlet, the annular inlet being divided into at least two axially offset inlet portions; and a ring-like seal adjacent a free end of the sleeve, at least a part of the ring-like seal being located in-between the sleeve and the inlet portions, or a structure defining the inlet portions.

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14-08-2013 дата публикации

Controlled fan stream flow bypass

Номер: EP2224100A3
Автор: Smith, J. Walter
Принадлежит:

A turbine engine component of a turbofan engine (10) fitted with a bypass air valve (20) includes at least one turbine engine component having a surface (31) with at least one aperture (37), said turbine engine component located from between a bypass fan duct (32) and a turbine exhaust nozzle (24) of the turbofan engine (10). The bypass air valve (20) includes a liner concentrically disposed about the turbine engine component and parallel to a centerline (30) of the turbofan engine (10). The liner has a surface including at least one aperture (42) and at least one impermeable region (44). Means are provided for actuating the liner about the turbine engine components. The flow transfer location (34) comprises an area proximate to a turbine exhaust stream flow (28).

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10-06-2009 дата публикации

Turbine for a waste gas turbocharger in a combustion engine

Номер: EP2067962A2
Принадлежит:

Die Erfindung betrifft eine Turbine (1) eines Abgasturboladers (2) einer Brennkraftmaschine, insbesondere für ein Kraftfahrzeug, mit einem Turbinenrad (4) und einer Anströmeinrichtung (9) für ein dem Turbinenrad (4) zuzuführendes Medium. Es ist vorgesehen, dass das Turbinenrad (4) eine Radial- (5) und eine Diagonalbeschaufelung (7) aufweist und dass die Anströmeinrichtung (9) derart verstellbar ausgebildet ist, dass ein der Turbine (1) zugeführter Mediumstrom (8) in Abhängigkeit mindestens eines Parameters in radialer Richtung der Radialbeschaufelung (5) und/oder in diagonaler Richtung der Diagonalbeschaufelung (7) zuführbar ist.

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18-10-1995 дата публикации

Arrangement in regulating valves

Номер: EP0000677687A1
Принадлежит:

The invention relates to an arrangement in regulating valves for steam, gases or liquids and includes a cage (2) fixedly disposed in a valve housing (1), there being a movable valve body in the cage, the body (3) being positionally settable in the fixed cage (2) via a spindle (4) such as to be sealingly engageable via a sealing surface (5) formed on it against a seating (6) formed in the valve housing (1), the body (3) during its movement to its upper, i.e. fully open, position successively uncovering orifices (9) in the fixed cage (2) for achieving a gradual increase in through-flow area in the valve. The body (3) has a short skirt (10) coacting with seating (6) and provided with a plurality of orifices or grooves (11) which are successively uncovered at the beginning of the valve opening phase, as the body (3) moves away from its sealing engagement against the seating (6), or successively closed off during the valve closing phase as the body moves towards sealing engagement against the ...

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13-01-1988 дата публикации

Variable width diffuser

Номер: EP0000134748B1
Принадлежит: CARRIER CORPORATION

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24-03-1992 дата публикации

Номер: JP0004016616B2
Принадлежит:

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10-03-2013 дата публикации

ТУРБОКОМПРЕССОР ДЛЯ ДВИГАТЕЛЯ ВНУТРЕННЕГО СГОРАНИЯ

Номер: RU2011135434A
Принадлежит:

... 1. Турбокомпрессор для двигателя внутреннего сгорания с корпусом турбины, вмещающим турбинное колесо (28), с направляющим устройством (17) с направляющими элементами (44) для влияния на параметры потока, поступающего на вход турбинного колеса, со сконструированным как деталь, изготавливаемая независимо от направляющего устройства (40), и сопряженным с направляющим устройством (40) подвижным регулирующим устройством (12) и со сконструированным как деталь, изготавливаемая независимо от регулирующего устройства (12), элементом гильзового газораспределения (14) для влияния на параметры потока на выходе турбинного колеса, отличающийся тем, что направляющее устройство (17), элемент гильзового газораспределения (14) и регулирующее устройство (12) монтируются как объединение деталей (10') в турбокомпрессоре.2. Турбокомпрессор по п.1, отличающийся тем, что объединение деталей (10') монтируется со стороны выхода турбины (34).3. Турбокомпрессор по п.1, отличающийся тем, что регулирующее устройство ...

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16-10-2003 дата публикации

TURBINE MIT VERSTELLBARER STATORGEOMETRIE

Номер: DE0069811686T2
Автор: PARKER JOHN, PARKER, JOHN

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03-04-2003 дата публикации

TURBINE MIT VERSTELLBARER STATORGEOMETRIE

Номер: DE0069811686D1
Автор: PARKER JOHN, PARKER, JOHN

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10-07-1969 дата публикации

Turbolader,insbesondere fuer eine Verbrennungsmaschine

Номер: DE0001451895A1
Принадлежит:

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18-05-2006 дата публикации

Turbine for exhaust gas turbocharger, has auxiliary blades, which are dimensioned such that throughput parameter of turbine wheel blades is set to throughput parameter of auxiliary blades in certain ratio, which is greater than fifteen

Номер: DE102005019937B3
Принадлежит: DAIMLER CHRYSLER AG, DAIMLERCHRYSLER AG

The turbine has a turbine wheel including a hube with a turbine wheel blades (6) and auxiliary blades (20). The auxiliary blades are arranged in a exhaust channel, which is defined by two turbine wheel blades, on the hub. The auxiliary blades are dimensioned in such a manner that a throughput parameter of the turbine wheel blades is set to a throughput parameter of the auxiliary blades in a ratio, which is greater than 15. An independent claim is also included for an exhaust-gas turbo charger in an internal combustion engine.

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20-09-2012 дата публикации

Turbine für einen Abgasturbolader

Номер: DE102011014458A1
Принадлежит:

Die Erfindung betrifft eine Turbine (32) für einen Abgasturbolader (22, mit einem Turbinengehäuse (76) und mit einem Turbinenrad (74), welches zumindest bereichsweise in dem Turbinengehäuse (76) aufgenommen und um eine Drehachse (73) drehbar ist, und welches zumindest eine wenigstens eine Anströmkante (90) und wenigstens eine Abströmkante (96, 102) aufweisende Laufradschaufel (82) aufweist, die zum Antreiben des Turbinerads (74) von das Turbinengehäuse (76) durchströmendem Abgas über die Anströmkante (90) anströmbar und über die Abströmkante (96, 102) abströmbar ist, wobei eine Verstelleinrichtung (56) vorgesehen ist, mittels welcher die Abströmkante (96, 102) der Laufradschaufel (82) des Turbinenrads (74) in einer ersten Stellung zumindest bereichsweise fluidisch freigebbar und demgegenüber in zumindest einer zweiten Stellung der Verstelleinrichtung (56) wenigstens bereichsweise fluidisch zumindest im Wesentlichen versperrbar ist.

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18-05-2006 дата публикации

Abgasturbolader in einer Brennkraftmaschine

Номер: DE0010212675B4
Принадлежит: DAIMLER CHRYSLER AG, DAIMLERCHRYSLER AG

Abgasturbolader in einer Brennkraftmaschine, mit einem Verdichter (20) im Ansaugtrakt und einer Abgasturbine (1) im Abgasstrang, wobei die Abgasturbine (1) in einem Turbinengehäuse (2) einen Spiralkanal (4) aufweist, der in einen radialen Strömungseintrittsquerschnitt (6) mündet, über den dem Turbinenrad (3) der Abgasturbine (1) Abgas zuzuführen ist, wobei im radialen Strömungseintrittsquerschnitt (6) ein radialer Leitgitterring (10) angeordnet und der wirksame Strömungseintrittsquerschnitt (6) veränderlich einstellbar ist, dadurch gekennzeichnet, dass im Turbinengehäuse (2) mindestens ein zweiter Spiralkanal (5) vorgesehen ist, der in einen radialen Strömungseintrittsquerschnitt (7) mündet, über den dem Turbinenrad (3) der Abgasturbine (1) Abgas zuzuführen ist, wobei im radialen Strömungseintrittsquerschnitt (7) der radiale Leitgitterring (10) angeordnet und der wirksame Strömungseintrittsquerschnitt (7) veränderlich einstellbar ist, und dass der radiale Leitgitterring (10) zwischen zwei ...

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10-09-2009 дата публикации

Exhaust-gas turbocharger for e.g. diesel engine, has adjustable guide vane arranged between pair of walls of housing, and axially movable circular cover provided between one of walls and guide vane

Номер: DE102008000543A1
Принадлежит:

The turbocharger has a compressor wheel (5), and a housing (1) that includes an inlet spiral (11) for exhaust-gas of an internal combustion engine. An adjustable guide vane (13) is arranged between the inlet spiral and a turbine wheel (3) of the turbocharger. The adjustable guide vane is arranged between a pair of walls (17, 19) of the housing. An axially movable circular cover (23) is provided between the wall (19) and the guide vane. The axially movable circular cover is compressed against front sides (21) of the guide vane in an elastic manner.

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12-08-2004 дата публикации

Turbolader

Номер: DE0010297203T5
Автор: NICHTNENNUNG

Veränderlicher Turbolader mit einem Gehäuse, einem Verdichter, der drehbar in dem Gehäuse angebracht ist, einer Turbine, die drehbar in dem Gehäuse angebracht ist, einem ersten Einlaß, um zu ermöglichen, daß Luft zu dem Verdichter geleitet wird, einem Auslaß um zu ermöglichen, daß Luft von dem Verdichter zu einem Motor geleitet wird, einem zweiten Einlaß, um zu ermöglichen, daß Auspuffgase von dem Motor zu der Turbine geleitet werden, um die Turbine zu drehen, einer Kammer, die die Turbine umgibt und die die Auspuffgase aus dem zweiten Einlaß erhält, bevor die Auspuffgase zu der Turbine geleitet werden, und einer Lageranordnung, um die Drehung der Turbine zu erlauben, wobei der veränderliche Turbolader feste Leitschaufeln, die in der Kammer angebracht sind und die dazu dienen, Auspuffgase genau auf die Turbine zu richten, einen Kolben, der gleitbar ist und der zwischen den Leitschaufeln und der Turbine positioniert ist, und Steuereinrichtungen, die mit dem Kolben verbunden...

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29-09-2010 дата публикации

Variable geometry turbine actuator

Номер: GB0002468871A
Принадлежит:

A variable geometry turbine comprises a turbine wheel mounted on a turbine shaft within a housing assembly for rotation about a turbine axis. The housing assembly defines a gas flow inlet passage upstream of the turbine wheel, an annular wall member 40 defining a wall of the inlet passage and which is displaceable in a direction substantially parallel to the turbine axis to control gas flow through the inlet passage, and at least one moveable rod 42, which extends substantially parallel to the turbine axis, and is operatively connected via a first end of the rod 42 to the annular wall member 40 to control its displacement. The rod 42 is connected to the annular wall member 40 via a first arm 44 and a second arm 46, a first end of the first arm 44 and a first end of the second arm 46 being attached to the rod 42, and a second end of the first arm 44 being attached to the annular wall member 40 at a first circumferential position, and a second end of the second arm 46 being attached to the ...

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13-02-2002 дата публикации

Turbocharger apparatus

Номер: GB0000130942D0
Автор:
Принадлежит:

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29-08-2007 дата публикации

Calibration of an actuator for a variable geometry turbine

Номер: GB0000713951D0
Автор:
Принадлежит:

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30-07-2008 дата публикации

Variable geometric turbine

Номер: GB0000811228D0
Автор:
Принадлежит:

Подробнее
02-01-1991 дата публикации

TURBOCHARGER APPARATUS

Номер: GB0009024250D0
Автор:
Принадлежит:

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18-03-1992 дата публикации

VARIABLE GEOMETRY TURBINE

Номер: GB0002218744B

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24-03-2010 дата публикации

Radial flow turbine

Номер: GB0002463660A
Принадлежит:

A radial flow turbine has at least two expansion stages wherein fluid flows through a turbine wheel 11 in a first radial direction in the first stage, and then through the turbine wheel 11 in the opposite radial direction in the second stage, each expansion stage having a variable inlet nozzle 16, 28. Each nozzle 16, 28 may be defined between a fixed member 19, 20 adjacent to the turbine wheel 1, and a slidable member 15, 25 which slides in a circular path around the centre of the turbine wheel 11. A sliding control mechanism 14 may be provided to move each slidable member 15, 25 either independently or together. High pressure fluid may be supplied from outside the turbine wheel 11. Fluid may flow from the final stage of the turbine to an exhaust port 17 radially outwards of the turbine wheel 11. The turbine may be part of a waste heat recovery system using a Rankine cycle and an organic fluid.

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30-05-2012 дата публикации

Fluid turbine

Номер: GB0002463660B
Принадлежит: PCA ENGINEERS LTD [GB], PCA ENGINEERS LTD

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17-11-2010 дата публикации

Turbomachine

Номер: GB0201016701D0
Автор:
Принадлежит:

Подробнее
01-07-1992 дата публикации

VARIABLE GEOMETRY TURBINE ACTUATOR ASSEMBLY

Номер: GB0002218745B

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09-11-2005 дата публикации

Control of exhaust gas temperature of turbocharger

Номер: GB0002413830A
Принадлежит:

A method for controlling a variable geometry turbine of a turbocharger to increase the temperature of the exhaust gas delivered to an after treatment system. The method includes reducing a fluid flow area to the turbine below a normal size and bypassing a portion of the exhaust gas around a plurality of guide vanes 10 for example through bypass holes 32.

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20-08-2008 дата публикации

Radial flow turbine control

Номер: GB0002446597A
Принадлежит:

A radial flow gas turbine has a scroll 5 surrounding a turbine wheel 1, the scroll 5 having a first inlet arranged to direct gases from a gas supply manifold in a first direction A around the scroll 5. A valve 7 is movable to open or close a second inlet 6 in response to the gas pressure in the manifold, the second inlet 6 being arranged to direct gases from the gas supply manifold in a second, opposite, direction B around the scroll 5, thereby controlling the increase in rotational speed of the turbine wheel 1 as the volume of gases passing there through increases above a predetermined level. A second, smaller, scroll (11, figures 2, 3) may be provided in parallel with the scroll 5, the second scroll (11) having an inlet permanently in communication with the gas supply manifold. In this arrangement the first and second inlets of the scroll 5 may both be closed by valve 7 and all of the gas from the manifold supplied to the second scroll (11).

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16-09-2009 дата публикации

Variable geometry turbine for a turbocharger

Номер: GB2458191A
Принадлежит:

A variable geometry turbine 1 of the kind used in a turbocharger comprises a turbine wheel 4 supported in a housing 5 having a gas flow inlet passageway 13 defined between an annular wall of a movable wall member, such as a nozzle ring 14, and a facing wall such as a shroud plate 15. The nozzle ring 14 is moveable axially relative to the housing 5 to vary a width of the inlet passageway 13. An annular array of vanes 17 extends across the inlet passageway 13, the vanes 17 having an axial height extending from a root 26 to a tip 27. Each of the vanes 17 is receivable in a corresponding slot 18 provided in one of the walls. Some, most or all of the vanes 17 are tapered along their axial extent, eg by increasing the machining tolerance towards the vane tip, such that they are thinner at the tip 27 than the root 26 to avoid sticking of the vanes when the nozzle ring 14 is moved to more open positions. The amount of taper may vary eg non-linearly.

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01-03-2012 дата публикации

Variable geometry turbine

Номер: US20120051882A1
Автор: John Frederick Parker
Принадлежит: Individual

A variable geometry turbine comprising a turbine wheel supported in a housing for rotation about a turbine axis with an annular inlet passageway defined between a radial face of a nozzle ring and a facing wall of the housing. The nozzle ring is movable along the turbine axis to vary the width of the inlet passageway and of vanes that are received in corresponding slots in the facing wall. Each vane major surface such that at a predetermined axial position of the nozzle ring relative to the facing wall the recess is in axial alignment with the slot and affords an exhaust gas leakage path through the inlet passageway. The recess is configured to reduce the efficiency of the turbine at small inlet gaps appropriate to engine braking or exhaust gas heating modes.

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24-05-2012 дата публикации

Variable geometry turbine

Номер: US20120128471A1
Принадлежит: Cummins Turbo Technologies Ltd

A variable geometry turbine comprises a turbine wheel mounted within a housing for rotation about a turbine axis; and a gas flow control passage upstream of said turbine wheel, the gas flow control passage being defined at least in part between a radial first surface of a movable wall member and a facing wall of the housing, the movable wall member also comprising second and third surfaces which oppose the first surface. The movable wall member is movable in an axial direction so as to vary the size of the gas flow control passage. There is a first gas region of the turbine, a portion of which is upstream of the gas flow control passage, the first gas region including at least a portion of the gas flow control passage; a second gas region of the turbine downstream of the gas flow control passage which contains the turbine wheel; and a third gas region of the turbine downstream of the turbine wheel. The first gas region comprises the first and second surfaces, and the second gas region or third gas region comprises the third surface.

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14-11-2013 дата публикации

Inner turbine shell axial movement

Номер: US20130302147A1
Принадлежит: General Electric Co

A clearance control system for a turbine having a stator assembly and a rotor assembly includes a hydraulic or pneumatic controller that axially drives, through a shaft, one or more actuators connected to the stator assembly casing. The controller causes relative movement between the stator and rotor assemblies to adjust the clearances between portions of the stator and rotor in accordance with the varying operating conditions of the turbine. More particularly, the controller moves the stator relative to the rotor in first and second axial directions to compensate for thermal expansion and contraction during the operating conditions of the turbine.

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25-01-2018 дата публикации

RADIAL CENTRIFUGAL TURBOMACHINE

Номер: US20180023412A1
Принадлежит: EXERGY S.P.A.

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 ...

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08-02-2018 дата публикации

A TURBINE SYSTEM

Номер: US20180038240A1
Автор: ERIKSSON Pontus
Принадлежит: VOLVO TRUCK CORPORATION

A turbine system for recovering energy of exhaust gases of an internal combustion engine is provided. The turbine system includes a first turbine device, a second turbine device, and a flow control valve for bypassing exhaust gases passed the second turbine device. The turbine system further includes a pneumatic valve arranged between the first turbine device and the second turbine device and being configured to control the flow of exhaust gas to the second turbine device. 110010110120130120100140110120120. A turbine system () for recovering energy of exhaust gases of an internal combustion engine () , comprising a first turbine device () , a second turbine device () , and a flow control valve () for bypassing exhaust gases passed the second turbine device () , characterized in that the turbine system () further comprises a pneumatic valve () arranged between the first turbine device () and the second turbine device () and configured to control the flow of exhaust gas to the second turbine device ().2100140. The turbine system () according to claim 1 , wherein the pneumatic valve () is an on/off valve.310010110120130120100140110120120. A turbine system () for recovering energy of exhaust gases of an internal combustion engine () claim 1 , comprising a first turbine device () claim 1 , a second turbine device () claim 1 , and a flow control valve () claim 1 , which is configured to be positioned in at least one intermediate position between a fully opened and a closed position claim 1 , for bypassing exhaust gases passed the second turbine device () claim 1 , characterized in that the turbine system () further comprises an on/off valve () claim 1 , arranged between the first turbine device () and the second turbine device () and configured to control the flow of exhaust gas to the second turbine device ().4150130140130140. The turbine system according to or claim 1 , further comprising a controller () being connected to the flow control valve () and to the on/off ...

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16-02-2017 дата публикации

Turbocharger turbine with variable nozzle

Номер: US20170044925A1
Принадлежит: BorgWarner Inc

An exhaust gas turbocharger ( 1 ) includes a turbine section ( 2 ) having a turbine housing ( 11 ) and a turbine wheel ( 4 ) disposed in the turbine housing ( 11 ). The turbine housing ( 11 ) defines a fluid inlet ( 13 ), a fluid outlet ( 10 ), and a volute ( 9 ) that receives fluid from the fluid inlet ( 13 ). The turbine wheel ( 4 ) is disposed in the turbine housing ( 11 ) between the volute ( 9 ) and the fluid outlet ( 10 ). In addition, a radially-extending nozzle ( 20 ) is defined between a working surface ( 34 ) of an adjustable nozzle ring ( 32 ) and a facing surface ( 11 b ) of the turbine housing ( 11 ). An inner peripheral edge ( 40 ) of the nozzle ring ( 32 ) is movable in an axial direction relative to an outer peripheral edge ( 38 ) of the nozzle ring ( 32 ), whereby the nozzle dimensions can be varied.

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25-02-2016 дата публикации

VARIABLE GEOMETRY INLET SYSTEM

Номер: US20160053683A1
Принадлежит:

A variable geometry inlet system of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise. 1. A variable geometry inlet system of an aeroengine comprising an inlet duct for directing an air flow from an opening in the inlet duct to a compressor , the inlet duct including at least first and second sections , the first and the second sections movable relative to one another between an extended position and a retracted position , the first and second sections in the extended position defining an axially longer inlet duct than when in the retracted position , the inlet duct extending continuously from the opening to the compressor in both positions and providing only one inlet path for the air flow from the opening to the compressor regardless of the inlet duct position.2. The aeroengine of wherein the first section is affixed to a stationary structure of the engine and the second section is moveable relative to the first section.3. The aeroengine of wherein the first section is positioned generally downstream of the second section relative to the air flow through the inlet duct.4. The aeroengine of wherein the first and second sections telescopically cooperate with one another.5. The system as defined in claim 1 , wherein at least one of the first and second sections includes an acoustic treatment area defined on an inner surface.6. The system as defined in wherein the engine is a turbofan and the compressor is a fan rotor claim 1 , the system further comprising a nacelle surrounding the fan rotor claim 1 , the nacelle including a main portion having an annular outer skin and an inner barrel in a stationary position on the engine claim 1 , the inner barrel defining the first section of the inlet ...

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25-02-2016 дата публикации

LOW NOISE AEROENGINE INLET SYSTEM

Номер: US20160053685A1
Принадлежит:

An aeroengine has an inlet system which includes at least one deformable wall disposed adjacent a peripheral wall of an inlet duct and a plurality of acoustic cells attached to a back side in fluid communication through respective holes in the at least one deformable wall with an inlet duct air flow. The at least one deformable wall selectively forms part of the peripheral wall of the inlet duct when in an undeployed position and selectively forms a curved profile projecting into the inlet duct to reduce line-of-sight noise propagation through he inlet duct. 1. An aeroengine having a compressor inlet comprising an inlet duct for directing an air flow to a compressor , and at least one deformable wall providing a portion of a peripheral wall of the inlet duct and deformable between an undeployed and a deployed position , the at least one deformable wall having a first surface exposed to the air flow and a second surface opposite to the first surface , a plurality of acoustic cells being attached to the second surface of the at least one deformable wall , the at least one deformable wall having a plurality of holes extending therethrough from first to second surface and being in communication with the respective acoustic cells , the at least one deformable wall in the undeployed position being shaped as part of the peripheral wall to substantially avoid interfering with the air flow through the inlet duct , and the at least one deformable wall in the deployed position being deformed to project into the inlet duct to reduce an effective cross-sectional area of the inlet duct to reduce line-of-sight noise propagation.2. The aeroengine as defined in wherein the at least one deformable wall comprises a plurality of panels pivotally connected one to another to allow relative pivotal axes oriented transverse to the direction of the air flow.3. The aeroengine as defined in wherein the at least one deformable wall is made of a flexible material.4. The aeroengine as defined in ...

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15-05-2014 дата публикации

VARIABLE GEOMETRY TURBINE

Номер: US20140133969A1
Принадлежит: Cummins Turbo Technologies Limited

A variable geometry turbine comprises: a turbine wheel in a housing for rotation about a turbine axis; an annular inlet passage defined between respective radial inlet surfaces of first and second wall members, at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage; an array of vanes extending across the inlet passage, said vanes being connected to said first wall member; a complementary array of vane slots defined by the second wall member, said vane slots configured to receive said vanes to accommodate relative movement between the first and second wall members; the second wall member comprising at least two axially adjacent co-axial plates, a first plate defining a first array of openings which overlie a second array of openings defined by a second plate so as to define said array of vane slots, said first plate being fixed to said second plate. 191.-. (canceled)92. A variable geometry turbine comprising:a turbine wheel supported in a housing for rotation about a turbine axis;an annular inlet passage defined between respective radial inlet surfaces of first and second wall members, at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage;an array of vanes extending across the inlet passage, said vanes being connected to said first wall member;a complementary array of vane slots defined by the second wall member, said vane slots being configured to receive said vanes to accommodate relative movement between the first and second wall members;wherein the second wall member comprises at least two axially adjacent co-axial plates, a first of said plates defining a first array of openings which overlie a second array of openings defined by a second of said plates so as to define said array of vane slots, said first plate being fixed to said second plate.9397.-. (canceled)98. A turbine according to claim 92 , wherein the second ...

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03-03-2016 дата публикации

Turbomachine

Номер: US20160061103A1
Принадлежит: Cummins Ltd

A variable geometry turbine comprising a turbine wheel mounted for rotation about a turbine axis within a housing. The housing defines an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls. The turbine further comprises a cylindrical sleeve that is axially movable across the annular inlet to vary the size of a gas flow path through the inlet. The annular inlet is divided into at least two axially offset inlet passages. The inner diameter of the sleeve is greater than the inner diameter of the inlet passages.

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09-03-2017 дата публикации

VARIABLE GEOMETRY TURBINE ASSEMBLY

Номер: US20170067359A1
Принадлежит:

A variable geometry turbine assembly comprising an inlet passageway, extending radially inwards towards a turbine wheel, defined between a surface of a movable wall member and a facing wall and an actuation mechanism arranged to move the movable wall member axially and comprising a cam member provided with at least one formation and a carrier member axially coupled to at least one co-operating formation, wherein one of the at least one formation and the at least one co-operating formation is a radially extending formation, the at least one formation or the at least one co-operating formation extending in both the circumferential direction and the axial direction such that as the cam member is rotated relative to the carrier member, the at least one formation and the at least one co-operating formation engage such the movable wall member is moved in the axial direction. 170-. (canceled)71. A variable geometry turbine assembly comprising: 'an annular inlet passageway extending radially inwards towards the turbine wheel;', 'a turbine wheel mounted within a turbine housing for rotation about a turbine axis;'}the annular inlet passageway being defined between a surface of a movable wall member and a facing wall;the movable wall member being movable in an axial direction so as to vary the size of the annular inlet passageway,and an actuation mechanism arranged to move the movable wall member axially relative to the facing wall;the actuation mechanism comprising:a carrier member, the carrier member being movable in the axial direction and coupled to the movable wall member such that as the carrier member is moved in the axial direction, the moveable wall member is moved in the axial directiona cam member provided with at least one formation;the carrier member being coupled to at least one co-operating formation such that as the at least one co-operating formation is moved in the axial direction, the carrier member is moved in the axial direction, wherein one of the at ...

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26-03-2015 дата публикации

DIFFUSER WITH STRUT-INDUCED VORTEX MIXING

Номер: US20150086339A1
Автор: Orosa John A.
Принадлежит:

A gas turbine engine includes inner and outer shrouds forming an annular gas path, and a plurality of struts connecting the inner shroud to the outer shroud. Airfoil shaped shields surround the struts, and each of the shields include a main body having an upstream leading edge defining a chordal axis extending in a downstream axial direction from the leading edge toward a downstream end of the shield. A trailing edge flap is located at the downstream end of each shield, the trailing edge flap including first and second span-wise portions. The first span-wise portion is oriented to direct flow at an angle relative to the chordal axis of the main body and the second span-wise portion is oriented to direct flow in a direction that is at a different angle than the angle of first span-wise portion. 1. A gas turbine engine having a turbine exhaust section comprising:a pair of concentrically spaced rings;a plurality of strut structures extending radially between the rings, interconnecting and supporting the rings;the strut structures supported downstream of a last row of rotating blades and comprising a main body portion having an elongated chordal dimension in the direction of an axial gas flow through the engine and defining a chordal axis extending in a downstream direction from an upstream end of the main body portion toward a downstream end of the strut structure; anda trailing edge flap located at the downstream end of each main body portion, the trailing edge flap including first and second span-wise portions, the first span-wise portion oriented to direct flow at an angle relative to the chordal axis of the main body portion and the second span-wise portion oriented to direct flow in a direction that is at a different angle than the angle of the first span-wise portion.2. The gas turbine engine of claim 1 , wherein the first span-wise portion defines a flap angle in a direction to a first side the chordal axis claim 1 , and the second span-wise portion defines a ...

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21-03-2019 дата публикации

Turbocharger With Progressively Variable A/R Ratio

Номер: US20190085717A1
Автор: Blaylock Jimmy L.
Принадлежит:

A turbocharger including a pivoting vane () aligned with a volute slot () of the housing () and located proximal a downstream end () of a tongue () defining an initial inlet throat area () of the housing. When the vane is in its fully closed position (), inlet exhaust gas is prevented from flowing into the volute slot and, therefore, the turbine wheel, until the inlet exhaust gas passes a downstream end () of the vane. The vane effectively extends the inlet throat area to define a revised inlet throat area (). The A/R ratio of the housing progressively varies as the vane pivots between the fully opened and fully closed positions. 1. A turbocharger comprising:{'b': 10', '25', '10', '15', '17', '11', '21', '10, 'a housing () including a volute slot () located along a midline of an inner periphery of the housing () and a tongue () including a downstream end () defining an end of an initial inlet throat area (/) of the housing ();'}{'b': 50', '60', '65', '70', '57', '23, 'a vane () located proximal to the downstream end of the tongue, above and co-aligned with the volute slot and pivotable between a fully closed (), a neutral (), and a fully opened position (), a downstream end () of the vane defining a second inlet throat area () having a same cross-sectional area as the initial inlet throat area when the vane is in the fully opened position and a reduced cross-sectional area when the vane is in the fully closed position;'}wherein when the vane is in the fully opened position, the vane is adjacent an outer wall of the housing and the volute slot is unobstructed by the vane; andwherein when the vane is in the fully closed position, the volute slot is blocked by the vane up to the downstream end of the vane.2. A turbocharger according to claim 1 , further comprising:{'b': 41', '55, 'means for pivoting () the vane between the fully closed, neutral, and fully opened positions, the pivot means connected to an upstream end () of the vane.'}3. A turbocharger according to ...

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13-05-2021 дата публикации

DIVIDED VOLUTE TURBOCHARGER HAVING VANE RING WITH PLURALITY OF VANES HAVING ASYMMETRIC VANE PATTERN AND SYSTEM INCLUDING THE SAME

Номер: US20210140366A1
Принадлежит:

A system includes a divided volute turbocharger that delivers compressed air to an internal combustion engine and receives exhaust gas from the internal combustion engine. The turbocharger includes a turbine housing, a first and second volute, and a turbine housing outlet. The system also includes turbine wheel disposed in the turbine housing and a vane ring disposed in the turbine housing between the turbine wheel and the volutes. The vane ring includes a plurality of vanes having an asymmetric vane pattern disposed on a vane ring surface of an annular disk that receives the turbine wheel therewithin to direct and control the flow of exhaust from the volutes into the turbine wheel with generally equal flow while significantly reducing HCF forcing function. 1. An entryway system comprising: a turbine housing comprising a turbine housing interior adapted to receive a turbine wheel having a plurality of equally spaced turbine blades,', 'a first volute adapted for fluid communication with the internal combustion engine and said turbine housing interior for delivering exhaust gas from the first group of cylinders to said turbine housing interior,', 'a second volute adapted for fluid communication with the internal combustion engine and said turbine housing interior for delivering exhaust gas from the second group of cylinders to said turbine housing interior independently of said first volute,', 'a turbine housing outlet in fluid communication with said turbine housing interior, and', 'a wall separating said first volute from said second volute and including a first tongue and a second tongue spaced from said first tongue; and, 'a divided volute turbocharger for receiving exhaust gas from an internal combustion engine and for delivering compressed air to the internal combustion engine, the internal combustion engine including a first group of cylinders and a second group of cylinders, with the relative pulse of exhaust gas delivered from the first and second group of ...

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30-04-2020 дата публикации

Exhaust gas turbocharger

Номер: US20200131926A1
Принадлежит: BMTS Technology GmbH and Co KG

The present disclosure relates to an exhaust gas turbocharger, for example for a motor vehicle. The exhaust gas turbocharger includes a turbine including a turbine housing and a turbine wheel, a variable turbine geometry including a vane ring and at least one adjustable guide vane, and a spring arrangement including a disc spring structured and arranged to mechanically impact the vane ring in a direction of the turbine housing. The disc spring extends in a circumferential direction with respect to a rotary axis of the turbine wheel and comprises a disc opening that extends up to a radial inside of the disc spring. A heat shield of the spring arrangement extends in the circumferential direction and is arranged on a side of the disc spring axially facing towards the vane ring.

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04-09-2014 дата публикации

VARIABLE GEOMETRY TURBINE

Номер: US20140248138A1
Принадлежит: Cummins Turbo Technologies Limited

A variable geometry turbine comprises: a turbine wheel in a housing for rotation about a turbine axis; an annular inlet passage defined between respective radial inlet surfaces of first and second wall members, at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage; an array of vanes extending across the inlet passage, said vanes being connected to said first wall member; a complementary array of vane slots defined by the second wall member, said vane slots configured to receive said vanes to accommodate relative movement between the first and second wall members; the second wall member comprising at least two axially adjacent co-axial plates, a first plate defining a first array of openings which overlie a second array of openings defined by a second plate so as to define said array of vane slots, said first plate being fixed to said second plate. 92. A variable geometry turbine comprising:a turbine wheel supported in a housing for rotation about a turbine axis;an annular inlet passage defined between respective radial inlet surfaces of first and second wall members, at least one of said first and second wall members being moveable along the turbine axis to vary the size of the inlet passage;an array of vanes extending across the inlet passage, said vanes being connected to said first wall member;a complementary array of vane slots defined by the second wall member, said vane slots being configured to receive said vanes to accommodate relative movement between the first and second wall members;wherein the second wall member comprises at least two axially adjacent co-axial plates, a first of said plates defining a first array of openings which overlie a second array of openings defined by a second of said plates so as to define said array of vane slots, said first plate being fixed to said second plate.93. A turbine according to claim 92 , wherein the cross-sectional shape transverse to said ...

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11-09-2014 дата публикации

Axial-flow turbine and power plant including the same

Номер: US20140250859A1
Принадлежит: Toshiba Corp

An axial-flow turbine according to an embodiment includes a plurality of nozzle structures and a plurality of blade structures. At least one nozzle structure includes an outer ring diaphragm and an inner ring diaphragm. The outer ring diaphragm and the inner ring diaphragm form an annular opening portion which extends in a circumferential direction therebetween. A nozzle is provided in a portion of a region of the annular opening portion in the circumferential direction, and a closing part is provided in another portion of the region of the annular opening portion in the circumferential direction. The closing part closes this other portion of the region to prevent a working fluid from flowing into this other portion of the region. A closing part medium passage is provided in the closing part and is configured to flow a cooling medium which cools the closing part.

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05-07-2018 дата публикации

LOW NOISE AEROENGINE INLET SYSTEM

Номер: US20180187599A1
Принадлежит:

An aeroengine includes an inlet duct having a section including opposed and substantially flat first and second peripheral walls, a first deformable wall providing a portion of the first peripheral wall and a second deformable wall providing a portion of the second peripheral wall. The deformable walls are deformable between undeployed and deployed positions, and each include panels pivotally connected one to another to allow pivotal movement of the panels relative to respective adjacent panels about respective parallel axes oriented transverse to a direction of the air flow. The deformable walls in the undeployed position each being substantially flat to substantially avoid interfering with the air flow, and in the deployed position each projecting into the inlet duct from the respective peripheral wall to reduce an effective cross-sectional area of the inlet duct to reduce line-of-sight noise propagation. 1. An aeroengine comprising: an inlet duct for directing an air flow from an intake opening to a compressor , the inlet duct having a section including opposed and substantially flat first and second peripheral walls , a first deformable wall providing a portion of the first peripheral wall and a second deformable wall providing a portion of the second peripheral wall , the first and second deformable walls being deformable between undeployed and deployed positions , the first and second deformable walls each including a plurality of panels pivotally connected one to another to allow pivotal movement of the panels relative to respective adjacent ones of the panels about respective parallel axes oriented transverse to a direction of the air flow , the first and second deformable walls in the undeployed position each being substantially flat to substantially avoid interfering with the air flow and the first and second deformable walls in the deployed position each projecting into the inlet duct from a respective one of the first and second peripheral walls to ...

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21-07-2016 дата публикации

TURBINE DAMPING DEVICE

Номер: US20160208638A1
Автор: Chen Yongjun
Принадлежит:

A turbine damping device is mounted on a fitness device, and has a housing assembly, a turbine assembly, and a regulating unit. The turbine assembly is mounted inside the housing assembly and has a turbo casing, a turbo wheel, and an adjusting plate. The turbo casing has an exhaling hole. The adjusting plate is controlled by the regulating unit and mounted movably in the exhaling hole. The turbo wheel is mounted rotatably inside the turbo casing. The turbo casing and the turbo wheel generate an airflow resistance that is an exercising load for users using the fitness device. The adjusting plate regulates an opening size of the exhaling hole to adjust the airflow resistance. The turbine damping device has a simple structure and maintenance thereof is easy. A user adjusts the exercising load easily by controlling the adjusting plate. The fitness device with airflow resistance is helpful to environmental protections. 1. A turbine damping device for a fitness device , the turbine damping device comprising:a housing assembly; [ an inhaling hole defined on a side surface of the turbo casing; and', 'an exhaling hole defined on a circumferential edge of the turbo casing;, 'a turbo casing having'}, 'a turbo wheel mounted inside the turbo casing; and', 'an adjusting plate mounted movably in the exhaling hole;, 'a turbine assembly mounted inside the housing assembly and having'}a shaft mounted through the turbo wheel axially, wherein the shaft rotates with the turbo wheel and both ends of the shaft are mounted rotatably inside the housing assembly;a shaft driving assembly mounted on one of the ends of the shaft that extends out of the turbo casing; anda regulating unit connecting and driving the adjusting plate to regulate an opening size of the exhaling hole.2. The turbine damping device as claimed in claim 1 , wherein multiple inlet holes defined on the housing assembly and communicating with the inhaling hole of the turbo casing;', 'an outlet hole defined on a ...

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27-06-2019 дата публикации

TURBOCHARGER HAVING VARIABLE COMPRESSOR TRIM

Номер: US20190195122A1
Принадлежит:

A turbocharger includes a compressor and an airflow adjustment assembly. The airflow adjustment assembly includes a plurality of guide vanes. Each of the plurality of guide vanes has a guide tip and a guide base spaced from the guide tip along an axis. The guide tips define a vane diameter (VD) less than the inlet diameter (ID) and perpendicular to the axis. The airflow adjustment assembly further includes a sliding ring and a plurality of connecting rods. The sliding ring is configured to be axially movable along the axis. Additionally, the plurality of connecting rods are axially moveable along the axis when the sliding ring moves axially along the axis, thereby selectively increasing and/or decreasing the vane diameter (VD) when the sliding ring moves axially along the axis. 1. A turbocharger for receiving exhaust gas from an internal combustion engine and for delivering compressed air to the internal combustion engine , said turbocharger comprising:a turbine housing defining a turbine housing interior;a turbine wheel disposed within said turbine housing interior for receiving the exhaust gas from the internal combustion engine;a turbocharger shaft coupled to and rotatable by said turbine wheel, with said turbocharger shaft extending along an axis that extends longitudinally through said turbine housing interior;a compressor housing defining an interior, with said compressor housing having an air inlet portion spaced from said turbocharger shaft and disposed about said axis, and with said air inlet defining an inlet diameter (ID) perpendicular to said axis;a compressor wheel disposed within said interior and coupled to said turbocharger shaft, with said compressor wheel being rotatable by said turbocharger shaft for delivering compressed air to said air inlet portion and said turbine wheel; and a plurality of guide vanes at least partially disposed within said interior of said compressor, with each of said plurality of guide vanes having a guide tip and a guide ...

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02-10-2014 дата публикации

Turbine for an exhaust gas turbocharger

Номер: US20140294576A1
Принадлежит: IHI Charging Systems International GmbH

In a turbine for an exhaust gas turbocharger with a turbine casing having receiving chamber for accommodating a turbine wheel and at least one volute through which the exhaust gas is guided via a feed passage into the receiving chamber and wherein at least one guide element is provided in the turbine casing so as to project into the feed passage in a guide region for guiding the exhaust gas onto the turbine wheel, the guide element comprises a first length region in the axial direction of the turbine, in which the guide element is designed with respect to its aerodynamic properties differently from its aerodynamic design in a second length region adjoining the first length region.

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25-08-2016 дата публикации

EXHAUST GAS-TURBOCHARGED INTERNAL COMBUSTION ENGINE COMPRISING A RADIAL COMPRESSOR WITH GUIDE DEVICE ARRANGED IN THE DIFFUSER, AND METHOD FOR OPERATING AN INTERNAL COMBUSTION ENGINE OF SAID TYPE

Номер: US20160245159A1
Принадлежит:

Methods and systems are provided for an adjustable diffuser of a turbocharger compressor. In one example, a compressor includes a diffuser formed in a compressor housing downstream of an impeller of the compressor, the diffuser including guide blades mounted on a rotatable annular support of the diffuser. Further, an engine controller may adjust rotation of the annular support based on one or more engine operating conditions. 1. A supercharged internal combustion engine , comprising:an intake system for the supply of charge air;an exhaust-gas discharge system for the discharge of exhaust gas; andat least one exhaust-gas turbocharger which comprises a radial turbine arranged in the exhaust-gas discharge system and a radial compressor arranged in the intake system, the compressor being equipped with at least one impeller which is mounted, in a compressor housing, on a rotatable shaft, a diffuser being formed in the compressor housing downstream of the at least one impeller, guide blades of a guide device being arranged in the diffuser, and the guide device comprising an annular support which holds the guide blades of the guide device, wherein the annular support together with guide blades is formed as a support which revolves about the shaft of the compressor, an electric auxiliary drive being provided for driving the support in accordance with demand, by means of which electric auxiliary drive the annular support can have a revolving movement forcibly imparted to it in at least one direction of rotation.2. The supercharged internal combustion engine as claimed in claim 1 , wherein the annular support can claim 1 , by means of the auxiliary drive claim 1 , be rotated in the opposite direction to the at least one impeller of the compressor and wherein the annular support can claim 1 , by means of the auxiliary drive claim 1 , be rotated in the same direction as the at least one impeller of the compressor.3. The supercharged internal combustion engine as claimed in ...

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29-08-2019 дата публикации

Variable geometry turbine

Номер: US20190264576A1
Принадлежит: Cummins Ltd

A variable geometry turbine is disclosed comprising: a housing; a turbine wheel supported in the housing for rotation about an axis; a movable wall member; a cavity provided in the housing; and an inlet passageway extending radially inwards towards the turbine wheel. The movable wall member comprises a generally annular wall and radially inner and outer flanges extending axially from the generally annular wall, inner surfaces of the generally annular wall and radially inner and outer flanges defining an interior surface of the movable wall member. The cavity is suitable for receipt of the radially inner and outer flanges of the moveable member, the movable wall member being axially movable relative to the housing to vary the extent to which the radially inner and outer flanges of the moveable member are received in the cavity.

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20-08-2020 дата публикации

Turbocharger With A Pivoting Sliding Vane For Progressively Variable A/R Ratio

Номер: US20200263559A1
Автор: Blaylock Jimmy L.
Принадлежит:

An improvement to a turbocharger having a housing () with a slot () located along a midline of the housing () above the turbine wheel () and a tongue () defining the end of an initial inlet throat area () of the housing (), the slot () permitting inlet exhaust gas which flows past the tongue () to flow into the turbine wheel (), the improvement being a pivoting vane () aligned with the slot () and having an upstream end () located at a downstream end () of the tongue (). When the vane () is in its fully closed position (), the inlet exhaust gas is prevented from flowing into the slot () and, therefore, the turbine wheel (), until the inlet exhaust gas passes the downstream end () of the vane (). The vane () effectively extends the tongue () to define a revised inlet throat area (). The A/R ratio of the housing () progressively varies as the vane () pivots between the fully opened () and fully closed () positions. 1. A turbocharger comprising:a housing including a volute containing an inlet throat section and a volute slot;a dual vane co-aligned with the volute slot, an upstream end of the dual vane located in proximity to a downstream end of the inlet throat section;the dual vane including a primary vane and a secondary vane, the secondary vane disposed on an upper surface of the primary vane and shaped complementary to the primary vane, the primary vane configured to pivot away from and toward the volute slot between a fully opened position and a fully closed position, the secondary vane configured to slide between a fully retracted position and a fully extended position;wherein the secondary vane is in the fully retracted position when the primary vane pivots between the fully opened and closed positions;wherein in the fully closed position, a portion of the volute slot lying below the dual vane is blocked and the secondary vane may extend from the fully retracted position;wherein when the secondary vane is extended, an additional portion of the volute slot lying ...

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20-08-2020 дата публикации

Valve assembly for a dual volute turbocharger and dual volute turbocharger including the same

Номер: US20200263599A1
Автор: Michael Daniel COLA
Принадлежит: BorgWarner Inc

A valve assembly for controlling exhaust gas flow to a turbine housing interior of a dual volute turbocharger includes a first valve member, a valve shaft, and a second valve member. The first valve member is disposed about and extends along an axis between a first end and a second end and is movable between a first, a second, and a third position for controlling exhaust gas flow to the turbine housing interior. The first valve member defines a valve interior between the first and second ends. The valve shaft is partially disposed in the valve interior and is coupled to the first end of the first valve member. The second valve member has a base coupled to and disposed about the valve shaft and a projection extending from the base and about the shaft into the valve interior. The second valve member is movable between closed and open positions.

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11-10-2018 дата публикации

TURBOMACHINE

Номер: US20180291802A1
Принадлежит:

A variable geometry turbine comprising a turbine wheel mounted for rotation about a turbine axis within a housing. The housing defines an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls. The turbine further comprises a cylindrical sleeve that is axially movable across the annular inlet to vary the size of a gas flow path through the inlet. The annular inlet is divided into at least two axially offset inlet passages. The inner diameter of the sleeve is greater than the inner diameter of the inlet passages. 1. A variable geometry turbine comprisinga turbine wheel mounted for rotation about a turbine axis within a housing, the housing defining an annular inlet surrounding the turbine wheel and defined between first and second inlet sidewalls; anda cylindrical sleeve axially movable across the annular inlet to vary the size of a gas flow path through the inlet;wherein the annular inlet is divided into at least two axially offset inlet passages, andwherein the inner diameter of the sleeve is greater than the inner diameter of the inlet passages.2. A variable geometry turbine according to claim 1 , wherein the inner diameter of the sleeve is less than or substantially equal to the outer diameter of the inlet passages.3. A variable geometry turbine according to claim 1 , wherein the inner diameter of the sleeve is greater than the outer diameter of the inlet passages.4. A variable geometry turbine according to claim 1 , wherein the sleeve is axially movable across the annular inlet in a direction towards the second inlet sidewall so as reduce the size of the gas flow path through the inlet claim 1 , and wherein at least a portion of an end of the sleeve nearer to the first inlet sidewall than the second inlet sidewall is configured so as to be exposable to gases flowing through said annular inlet during use.5. A variable geometry turbine according to claim 1 , wherein the sleeve is axially movable across the annular inlet in ...

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17-09-2020 дата публикации

DIFFUSER AND TURBOCHARGER

Номер: US20200291847A1

A diffuser includes a connection section and a body section. The connection section extends from an outlet of turbine rotor blades. The body section is connected to an end of the connection section on a downstream side and has a larger flow passage sectional area than the connection section. The shape of the flow passage sectional surface of the connection section is formed into a circle at an outlet of the turbine rotor blades and is formed into an ellipse at an inlet of the body section. The shape of the flow passage sectional surface of the connection section is further formed to be gradually enlarged in a long-axis direction of the ellipse from the outlet of the turbine rotor blades toward the inlet of the body section.

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17-09-2020 дата публикации

TURBOCHARGER HAVING ADJUSTABLE-TRIM CENTRIFUGAL COMPRESSOR INCLUDING DIVERGENT-WALL DIFFUSER

Номер: US20200291851A1
Принадлежит: Garrett Transportation I Inc.

A centrifugal compressor for a turbocharger includes an inlet-adjustment mechanism in an air inlet for the compressor, operable to move between an open position and a closed position in the air inlet. Movement of the inlet-adjustment mechanism from the open position to the closed position is effective to shift the compressor's surge line to lower flow rates. The compressor includes a diffuser extending between an exducer of the compressor wheel and a volute for collecting pressurized air from the compressor. The diffuser is defined between first and second walls that diverge from each other in a radially outwardly direction through the diffuser. The divergent-wall diffuser enhances the shift of the surge line to lower flow rates when the inlet-adjustment mechanism is put in the closed position.

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24-09-2020 дата публикации

THE EFFECT OF THE NOZZLE WIDTH TO HARNESS ON ENGINE PULSE ENERGY

Номер: US20200300160A1
Автор: Hughes Stephen David
Принадлежит:

A turbine comprises a turbine wheel for rotation within a turbine housing, the turbine housing including at least one volute arranged to deliver a fluid to the turbine wheel via the turbine nozzle. A method for determining a width of a turbine nozzle for the turbine, comprises selecting from a relationship between a turbine stage efficiency and an effective nozzle area, at least one target effective nozzle area. As used here, the effective nozzle area is dependent on both the width of the turbine nozzle and a whirl angle induced by the at least one volute. The method further comprises determining, in dependence on the whirl angle, the width of the turbine nozzle as a width that will achieve the at least one target effective nozzle area. 1. A method for determining a width of a turbine nozzle for a turbine , the turbine comprising a turbine wheel for rotation within a turbine housing , the turbine housing including at least one volute arranged to deliver a fluid to the turbine wheel via the turbine nozzle , the method comprising:selecting from a relationship between a turbine stage efficiency and an effective nozzle area, at least one target effective nozzle area, wherein the effective nozzle area is dependent on both the width of the turbine nozzle and a whirl angle induced by the at least one volute; anddetermining in dependence on the whirl angle, the width of the turbine nozzle as a width that will achieve the at least one target effective nozzle area.2. The method of further comprising determining the relationship between the turbine stage efficiency and the effective nozzle area from which the at least one target effective nozzle area is determined.3. The method of wherein the effective nozzle area is proportional to a product of the width of the turbine nozzle and a cosine of the whirl angle.4. The method of wherein the turbine is a twin-volute turbine comprising two volutes.5. The method of when wherein determining the width of the turbine nozzle in ...

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24-11-2016 дата публикации

POSITION ADJUSTMENT DEVICE, ROTATING MACHINE PROVIDED WITH SAME, AND POSITION ADJUSTMENT METHOD

Номер: US20160341069A1
Принадлежит:

A position adjustment device is provided with an eccentric pin and a push rod. The eccentric pin has a rotating shaft part, and an eccentric shaft part inserted into an end in a circumferential direction of a lower-half inside member. The push rod is inserted into the lower-half inside member from an end surface in the circumferential direction of the lower-half inside member, the push rod being able to come into contact with the eccentric shaft part within the lower-half inside member. The rotating shaft part has a columnar shape with a rotational axis line. The eccentric shaft part is formed with: a side peripheral surface that comes into contact with the inner peripheral surface of an eccentric shaft hole in the lower-half inside member into which the eccentric shaft part is inserted, and a rod contact surface that comes into contact with the push rod. 1. A position adjustment device that adjusts , relative to a lower-half outside member that forms a lower half of a cylindrical outside cylinder with a rotor axis line as the center , a position in a vertical direction of a lower-half inside member that forms a lower half of a ring-shaped inside ring disposed on an inner peripheral side of the outside cylinder and having the rotor axis line as the center , the position adjustment device comprising: a rotating shaft part rotatably supported at an end in a circumferential direction of the lower-half outside member, and', 'an eccentric shaft part inserted into an end in a circumferential direction of the lower-half inside member, the eccentric shaft part rotating integrally with rotation of the rotating shaft part; and, 'an eccentric pin that includes'}a push rod inserted into the lower-half inside member from an end surface in the circumferential direction of the lower-half inside member, the push rod being able to come into contact with the eccentric shaft part within the lower-half inside member, whereinthe rotating shaft part has a columnar shape with a rotational ...

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15-11-2018 дата публикации

Turbocharger Comprising a Slider for Fluid Connection

Номер: US20180328218A1
Принадлежит:

A turbocharger, in particular a turbocharger for a motor vehicle, is provided. The turbocharger includes a turbine to which exhaust gases can be supplied by two fluid ducts between which a separation wall extends; a closeable fluid connection hole in the separation wall that can be closed by a plate-shaped slider between the fluid ducts. The invention further relates to a motor vehicle comprising the turbocharger. 1. A turbocharger , comprising:a turbine;two channel ducts configured to supply exhaust gases to the turbine;a channel connection opening between the two channel ducts; anda slider configured to close the channel connection opening when moved between the two channel ducts along a plane containing the slider.2. The turbocharger as claimed in claim 1 , wherein claim 1 , in a closed state of the slider claim 1 , a front end of the slider is located within the channel connection opening and an outer surface of the slider transverse to the plane containing the slider bears against an inner surface of the channel connection opening.3. The turbocharger as claimed in claim 2 , wherein the slider has a shape which tapers toward the front end in the plane containing the slider.4. The turbocharger as claimed in claim 3 , wherein one of the inner surface of the channel connection opening and the outer surface of the slider is formed concavely and the other of the channel connection opening and the outer surface of the slider is formed convexly.5. The turbocharger as claimed in claim 4 , further comprising:a housing containing at least portions of the two channel ducts; anda cover configured to be fastened to the housing and in which at least half of the slider is accommodated when the slider is in an opened state of the channel connection opening.6. The turbocharger as claimed in claim 5 , whereina sliding element at a rear end of the slider includes a guide plate perpendicular to the plane containing the slider, andthe guide plate of the sliding element is configured ...

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14-12-2017 дата публикации

Variable geometry turbocharger turbine

Номер: US20170356333A1
Автор: Apostolos Pesiridis
Принадлежит: Brunel University London

In an effort to increase the reliability and net power and efficiency benefit of the axial- and mixed-flow turbocharger turbine, there is provided, a tapered, axially translatable (“sliding nozzle”) flow restrictor member to provide appropriate inlet exhaust gas flow characteristics for the operation of an axial or mixed flow turbine. The invention produces change of turbine flow with acceptable resolution at a lower cost than that for a conventional pivoting vane, variable geometry axial turbocharger turbine or at a similar cost but higher efficiency than a conventional sliding nozzle, variable geometry mixed, flow turbocharger turbine.

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14-11-2019 дата публикации

VARIABLE DIFFUSER HAVING A RESPECTIVE PENNY FOR EACH VANE

Номер: US20190345838A1
Принадлежит:

A variable diffuser comprises a passage, at least two vanes disposed within the passage, and at least two pennies. The passage is defined between opposing disk faces of a hub and a tip. Each of the vanes comprises a body having a leading edge and a trailing edge. The body extends between the hub face and the disk face. Each of the pennies is coupled to a respective vane body near an edge of the penny and an actuator. Rotation of at least one penny changes the orientation of the respective vane relative to the hub face. 1. A variable diffuser comprising:a passage defined between opposing faces of a hub and a tip;at least two vanes within the passage, each of said vanes comprising a body having a leading edge and a trailing edge, the body extending between the hub face and the tip face;at least two rotatable pennies, each of said pennies coupled to a respective vane body and an actuator, wherein each penny is coupled to a respective vane body near an edge of the penny; andwherein rotation of at least one penny changes an orientation of the respective vane relative to the hub face.2. The variable diffuser of claim 1 , wherein each penny is rotatable a minimum of 90 degrees.3. The variable diffuser of claim 1 , wherein each vane body defines a slot and each penny is coupled to a respective body via a pin extending from the penny and into the respective slot.4. The variable diffuser of claim 1 , wherein each penny comprises a forked pin extending from a face of said penny claim 1 , and wherein each penny is coupled to a respective body such that the body is disposed within a fork of the forked pin.5. The variable diffuser of claim 1 , wherein each penny defines a recess configured to receive a respective pin claim 1 , and wherein each body is coupled to the respective penny by a respective pin extending from said body into said recess.6. The variable diffuser of claim 5 , wherein the hub face defines a slot respective to each body and each body is further coupled to the ...

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14-11-2019 дата публикации

VARIABLE DIFFUSER HAVING A RESPECTIVE PENNY FOR EACH VANE

Номер: US20190345839A1
Принадлежит:

A variable diffuser comprises a passage, at least two vanes disposed within the passage, and at least two pennies. The passage is defined between opposing disk faces of a hub and a tip. Each of the vanes comprises a body having a leading edge and a trailing edge. The body extends between the hub face and the disk face. Each of the pennies is coupled to a respective vane body near an edge of the penny and an actuator. Rotation of at least one penny changes the orientation of the respective vane relative to the hub face. 1. A variable diffuser comprising:a passage defined between opposing faces of a hub and a tip;at least one vane within the passage, said vane comprising a body having a leading edge and a trailing edge, the body extending between the hub face and the tip face; andat least one rotatable penny coupled to said body and an actuator, wherein the penny is coupled to the body near an edge of the penny;wherein the hub face defines a slot and the body is coupled to the hub face via a pin extending from the body and into the slot, the pin movable within the slot;wherein rotation of at least one penny changes an orientation of the at least one vane relative to the hub face.2. The variable diffuser of claim 1 , wherein the slot can be oriented radially with respect to a center axis.3. The variable diffuser of claim 1 , wherein the slot can be oriented circumferentially with respect to a center axis.4. The variable diffuser of claim 1 , wherein the tip face defines a second slot opposite the slot in the hub face claim 1 , and the body is coupled to the tip face via a second pin extending from the body to the second slot.5. The variable diffuser of claim 1 , wherein the penny is configured to rotate in unison with other pennies.6. The variable diffuser of claim 5 , wherein said actuator comprises an actuating ring claim 5 , the penny having a drive shaft extending from a first face of the penny claim 5 , said first face opposite a second face of the penny proximate ...

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10-12-2020 дата публикации

TURBOCHARGER

Номер: US20200386116A1
Принадлежит:

A turbocharger, having a turbine and a compressor. The turbine comprises a turbine housing and a turbine rotor with turbine blades. Radially outer edges of the rotor blades and a portion of the turbine housing or a stator-side component connected to the turbine housing define a turbine-side gap. The compressor comprises a compressor housing and a compressor rotor with compressor blades. Radially outer edges of the compressor blades and a portion of the compressor housing facing the compressor blades or a stator-side component connected to the compressor housing define a compressor-side gap. The portion of the turbine housing facing the turbine rotor blades or the stator-side component connected to the turbine housing and/or the portion of the compressor housing facing the compressor rotor blades or the stator-side component connected to the compressor housing comprises a running-in structure comprising hollow spaces. 1. A turbocharger , comprising:a shaft; a turbine housing;', 'a turbine rotor;', 'turbine rotor blades of the turbine rotor; and', 'a turbine-side gap defined between radially outer edges of the turbine rotor blades and a portion of the turbine housing facing the turbine rotor blades or a stator-side component connected to the turbine housing;, 'a turbine configured to expand a first medium comprising a compressor housing;', 'a compressor rotor:', 'compressor rotor blades of the a compressor rotor coupled to the turbine rotor via the shaft; and', 'a compressor-side gap defined between radially outer edges of the compressor rotor blades and a portion of the compressor housing facing the compressor rotor blades or a stator-side component connected to the compressor housing;, 'a compressor configured to compress a second medium utilizing energy extracted in the turbine during expansion of the first medium, the compressor comprisinga bearing housing arranged between and connected to the turbine housing and the compressor housing and in which the shaft is ...

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13-01-2016 дата публикации

A nozzle arrangement for a gas turbine engine

Номер: EP2966267A1
Автор: Andrew Rolt
Принадлежит: Rolls Royce PLC

A gas turbine engine comprising: a bypass duct having a bypass nozzle; an engine core having a core nozzle; and, a mixer duct defined by a mixer fairing and having a mixer nozzle, wherein the mixer duct is arranged to receive an airflow from the bypass duct through a mixer duct inlet and an airflow from the engine core, when in use, and the geometry of the mixer duct is selectively adjustable by moving the mixer fairing relative to the bypass duct and engine core in use.

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28-01-1987 дата публикации

Variable width diffuser

Номер: KR870000017B1

내용 없음.

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05-02-2004 дата публикации

Exhaust gas turbocharger for an internal combustion engine

Номер: DE10233042A1
Принадлежит: DaimlerChrysler AG

Ein Abgasturbolader für eine Brennkraftmaschine weist eine Abgasturbine im Abgasstrang und einen Verdichter im Ansaugtrakt auf, wobei eine einstellbare Drosseleinrichtung stromauf des Verdichterrades zur Regulierung des zuzuführenden Luftmassenstromes vorgesehen ist. Die Drosseleinrichtung umfasst ein erstes Leitgitter und ein zweites Leitgitter im Zuströmbereich zum Verdichterrad. Jedes Leitgitter besitzt eine verstellbare Gittergeometrie. An exhaust-gas turbocharger for an internal combustion engine has an exhaust-gas turbine in the exhaust-gas train and a compressor in the intake tract, with an adjustable throttling device being provided upstream of the compressor wheel for regulating the air-mass flow to be supplied. The throttle device comprises a first guide grid and a second guide grid in the inflow region to the compressor wheel. Each baffle has an adjustable grid geometry.

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29-01-2004 дата публикации

Exhaust gas turbocharger for an internal combustion engine

Номер: WO2004009961A1
Принадлежит: DaimlerChrysler AG

The invention relates to an exhaust gas turbocharger for an internal combustion engine, said turbocharger comprising an exhaust gas turbine in the exhaust gas system and a compressor in the induction tract. A regulatable throttle device is provided upstream of the compressor disc, for regulating the air mass flow to be supplied. Said throttle device comprises a first guiding vane ring and a second guiding vane ring in the incoming region towards the compressor disc. Each guiding vane ring has an adjustable vane ring geometry.

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16-01-2003 дата публикации

Exhaust gas turbocharger for internal combustion engine enables different flow rates through exhaust gas openings to be set by altering valve body position

Номер: DE10132672A1
Принадлежит: DaimlerChrysler AG

The device has an exhaust gas turbine (3), a valve housing forming a common component with an exhaust gas turbine housing and a valve body in the valve housing for opening and closing first and second outlet openings associated with first and second exhaust gas channels. Different flow rates through the openings can be set by altering the valve body position.

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28-07-2016 дата публикации

Turbine with variable inlet cross-sectional area

Номер: DE112014005008T5
Автор: Verschoor Mart
Принадлежит: BorgWarner Inc

Die Erfindung betrifft eine Turbine 28 für einen Abgasturbolader, aufweisend ein Turbinengehäuse 2, eine in dem Turbinengehäuse 2 angeordnete, um eine Rotationsachse 12 verdrehbare Trommel 11, ein in der Trommel 11 rotierbar angeordnetes Turbinenrad 5, zumindest eine im Turbinengehäuse 2 ausgebildete Volute 16, 17, zumindest einen in der Trommel 11 ausgebildeten Durchbruch 14 zum Leiten einer Gasströmung aus der zumindest einen Volute 16, 17 auf das Turbinenrad 5, wobei durch ein Verändern eines Verdrehwinkels v der Trommel 11 relativ zu dem Turbinengehäuse 2 eine Eintrittsquerschnittsfläche Av der Volute 16, 17 variiert werden kann und wobei die Trommel über Lagerelemente 19 in den Turbinengehäuse 2 gelagert ist. The invention relates to a turbine 28 for an exhaust gas turbocharger, comprising a turbine housing 2, a drum 11 arranged in the turbine housing 2, rotatable about a rotation axis 12, a turbine wheel 5 rotatably arranged in the drum 11, at least one volute 16, 17 formed in the turbine housing 2 at least one opening 14 formed in the drum 11 for directing a gas flow from the at least one volute 16, 17 onto the turbine wheel 5, wherein an inlet cross-sectional area Av of the volute 16, 17 is produced by changing a rotation angle v of the drum 11 relative to the turbine housing 2 can be varied and wherein the drum is mounted via bearing elements 19 in the turbine housing 2.

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22-04-2010 дата публикации

Exhaust-gas turbocharger for internal combustion engine, particularly motor vehicle, has turbine and compressor, where switchable device is provided in intake port, which covers predetermined surface of intake air flow cross-section

Номер: DE102008052256A1
Принадлежит: VOLKSWAGEN AG

The exhaust-gas turbocharger has a turbine and a compressor. The compressor has a compressor wheel (10) and an intake port having a predetermined intake air flow cross-section. A switchable device is provided in the intake port, which covers the predetermined surface of the intake air flow cross-section such that a segment of the cross-section surface of the compressor wheel is shielded by the feed air.

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11-08-2010 дата публикации

Exhaust gas turbocharger for an internal combustion engine

Номер: EP1530671B1
Принадлежит: DAIMLER AG

An exhaust gas turbocharger for an internal combustion engine has an exhaust gas turbine in the exhaust gas train and a compressor in the intake tract, whereby an adjustable throttle device is provided upstream from the compressor wheel, for regulating the air mass stream to be supplied. The throttle device comprises a first guide grid and a second guide grid in the inflow region to the compressor wheel. Each guide grid possesses an adjustable grid geometry.

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05-08-2010 дата публикации

Exhaust gas turbocharger for an internal combustion engine

Номер: WO2010086005A2
Автор: Torsten Hirth
Принадлежит: DAIMLER AG

Die Erfindung betrifft einen Abgasturbolader für eine Verbrennungskraftmaschine mit einem ein Turbinenrad aufnehmenden Turbinengehäuse (28), mit einer Leitvorrichtung (17) mit Leitelementen (44) zur Beeinflussung von Strömungsparametern in einem Turbinenradeintrittsbereich, mit einer der Leitvorrichtung (40) zugeordneten bewegbaren Verstellvorrichtung (12) und mit einem Konturhülsenelement (14) zur Beeinflussung von Strömungsparametern in einem Turbinenradaustrittsbereich, wobei die Leitvorrichtung (17), das Konturhülsenelement (14) und die Verstellvorrichtung (12) als ein Teileverbund (10') im Abgasturbolader montiert sind.

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26-09-2007 дата публикации

Internal combustion engine comprising a compressor in the suction part and method therefor

Номер: EP1639245B1
Автор: Siegfried Sumser
Принадлежит: DaimlerChrysler AG

The invention relates to an internal combustion engine (1) comprising a compressor (5) in the suction part (7), said compressor comprising a compression wheel which is rotationally mounted in a compression inlet channel (105). The compression wheel can compress the supplied combustion air to form a higher charging pressure. An inflowing additional channel (115) is also provided in the compression inlet channel (105). An adjustable locking element (109) is arranged in the compression inlet channel (105) upstream from the compression wheel (102) and an adjustable torsion device is arranged in the opening area (116) of the additional channel (115). A NOx-storage catalyst (12) is arranged in the waste gas pipe. The torsion device (114, 117) can be adjusted in a position in order to produce an air-fuel ratio with a relative fuel surplus. Said position impinges the compression wheel (102) upon a driving torsion element and the locking element (109) can be adjusted to a position reducing the supply of air.

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06-06-2013 дата публикации

Compressor for supercharger used in e.g. diesel engine, has two adjusters respectively arranged in compressor wheel upstream and compressor wheel outlet, to influence flow parameters at compressor impeller and compressor wheel outlet

Номер: DE102011120168A1
Автор: Siegfried Sumser
Принадлежит: DAIMLER AG

Die Erfindung betrifft einen Verdichter für einen Abgasturbolader mit einem Verdichterrad (25) und einem zumindest abschnittsweise korrespondierend zum Verdichterrad (25) ausgeformten Verdichtergehäuse (24), wobei stromauf des Verdichterrads (25) eine axial verschiebbare Verstellvorrichtung (31) angeordnet ist, mittels derer Strömungsparameter an einem Verdichterradeintritt (36) beeinflussbar sind. Erfindungsgemäß ist an einem Verdichterradaustritt (23) eine weitere Verstellvorrichtung (22) angeordnet, mittels derer Strömungsparameter an einem Verdichterradaustritt (23) beeinflussbar sind.

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22-06-2017 дата публикации

A method of controlling exhaust gas temperature for after-treatment systems of a diesel engine using a variable geometry turbine

Номер: DE102005021096B4
Принадлежит: Cummins Inc

Verfahren, mit den Schritten: Betreiben eines Turboladers mit einer Turbine mit variabler Geometrie, der einen Einlassdurchgang zur Turbine mit einer Fluiddurchströmungsfläche umfasst, die für einen in einem Normalbetriebsbereich arbeitenden Verbrennungsmotor eine Normalgröße hat, Verringern der Größe der Fluiddurchströmungsfläche von der Normalgröße auf eine verringerte Größe zur Abgaserwärmung, wobei der Schritt des Verringerns einen Bypass-Fluidströmungsweg für das Abgas im Einlassdurchgang freilegt, der normalerweise blockiert ist, wenn die Fluiddurchströmungsfläche die Normalgröße hat, und Leiten eines Teils des in den Einlassdurchgang eintretenden Abgases an den Leitschaufeln der Turbine mit veränderlicher Geometrie vorbei.

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10-09-2016 дата публикации

DIFFUSER WITH RETAINED BLADES FOR COMPRESSORS

Номер: RU2015104708A
Принадлежит: Боргварнер Инк.

1. Турбонагнетатель, содержащий крыльчатку (14) компрессора и турбинное колесо, соединенные вращающимся валом, при этом улучшение включает систему (36) диффузора с втягиваемыми лопатками, содержащую:диффузор (18), образованный стенкой (30) ступицы и стенкой (32) кожуха и образующий путь (34) потока для воздуха, покидающего крыльчатку (14) компрессора; илопатку (38), втягиваемую в стенку (30) ступицы или стенку (32) кожуха.2. Турбонагнетатель по п. 1, отличающийся тем, что стабильность работы при низких значениях массового расхода воздуха улучшается за счет управления потоком воздуха.3. Турбонагнетатель по п. 1, отличающийся тем, что лопатка (38) является одной из множества лопаток.4. Турбонагнетатель по п. 1, дополнительно содержащий набор лопаток (40) на кольце (44) направляющего аппарата, при этом указанный набор лопаток (40) выполнен с возможностью втягивания в каждую из стенки (30) ступицы и стенки (32) кожуха.5. Турбонагнетатель по п. 1, отличающийся тем, что лопатка (38) выполнена отдельно от соседних лопаток.6. Турбонагнетатель по п. 5, отличающийся тем, что лопатка (38) может быть втянута, когда соседние лопатки выдвинуты.7. Турбонагнетатель по п. 1, дополнительно содержащий кольцо (44) направляющего аппарата в полости (42) стенки (32) кожуха диффузора (18), при этом кольцо (44) направляющего аппарата содержит множество лопаток (38), втягиваемых в стенку (32) кожуха.8. Турбонагнетатель по п. 1, отличающийся тем, что приведение в действие системы (36) диффузора с втягиваемыми лопатками вызвано массовым расходом воздуха, при этом меньшие значения массового расхода воздуха вызывают выдвижение лопатки (38) в путь (34) потока, и при этом более высокие значения массового расхода воздуха вызывают втягивание лопатки (38).9. Турбонагнетатель по п. 1, РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (51) МПК F02B 37/12 (11) (13) 2015 104 708 A (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2015104708, 11.07.2013 (71) Заявитель(и ...

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09-11-2010 дата публикации

Variable turbocharger and control method for the same

Номер: KR100993377B1

본 발명의 실시예에 따른 가변 터보 과급기는 터빈 내로 유입되는 배기 가스의 유입부의 단면적을 가변 시킬 수 있어 저속 및 고속에서 엔진의 효율을 향상시키는 것을 목적으로, 터빈 하우징, 배기 가스가 터빈을 지나 유출되도록 상기 터빈 하우징 내에 형성된 제1스크롤 및 상기 제1스크롤 주위에 상기 제1스크롤을 따라 형성된 제2스크롤, 상기 제1스크롤 및 상기 제2스크롤을 가변적으로 분리하도록 구비된 차단부, 및 상기 제2스크롤로 유입되는 상기 배기 가스를 가변적으로 차단하도록 배기 가스 유입부에 구비된 유량 조절 밸브를 포함한다. 터보 챠저, 터빈, A/R 비, 배기가스 유동

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09-11-2005 дата публикации

Method of controlling the exhaust gas temperature for after-treatment systems on a diesel engine using a variable geometry turbine

Номер: CN1693679A
Принадлежит: Cummins Inc

一种控制涡轮增压器的可变形涡轮机的方法,可以增加输送到后处理系统的废气的温度。在一种构型中,该方法包括将流向涡轮机的流体流动面积减小到正常尺寸大小以下,并且使废气的一部分沿多个导向叶片旁路流动。

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15-11-1986 дата публикации

Diffuser Side Plate Control System

Номер: KR860008425A

내용 없음

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26-03-2003 дата публикации

Rotary slide valve for the control of steam flow to a steam turbine

Номер: EP0808992B1
Автор: Richard Geist
Принадлежит: Alstom SA

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16-02-2011 дата публикации

Hydraulic servo-drive device and variable turbo-supercharger using the same

Номер: CN101978175A
Принадлежит: KOMATSU LTD

本发明提供一种液压伺服驱动装置以及利用该液压伺服驱动装置的可变涡轮增压器,该液压伺服驱动装置构成为具有:利用先导压力滑动且在油的供给和截断油的供给之间进行切换的先导滑阀(20)、跟随先导滑阀(20)进行滑动的伺服活塞(11)、检测伺服活塞(11)的移动量的行程传感器(15)、用于使伺服活塞(11)移动的油流入的第一液压室(51)、将被供给来自泵的油的泵口与第一液压室(51)连通的第一活塞油路(65)以及将第一液压室(51)与排油口连通的排出循环油路(66)。

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16-07-1988 дата публикации

Centrifugal compressor

Номер: KR880001268B1

The contrifugal compressor includes a housing having an inlet and an annular diffuser passage terminating at an outlet scroll, an impeller rotatably mounted in the housing between the inlet and diffuser passage and a diffuser in the diffuser passage. This includes a fixed vane diffuser having a mixing length at least one half the cover length of the fixed vane diffuser and a movable annular ring located upstream of the fixed vane diffuser for restricting the diffuser passage. An actuator moves the movable annlar ring to restrict the diffuser passage according to the load on the compressor. The fixed vane diffuser can be of a vaned island construction.

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13-11-2013 дата публикации

Hydraulic servo-drive device and variable turbo-supercharger using the same

Номер: CN101978175B
Принадлежит: KOMATSU LTD

本发明提供一种液压伺服驱动装置以及利用该液压伺服驱动装置的可变涡轮增压器,该液压伺服驱动装置构成为具有:利用先导压力滑动且在油的供给和截断油的供给之间进行切换的先导滑阀(20)、跟随先导滑阀(20)进行滑动的伺服活塞(11)、检测伺服活塞(11)的移动量的行程传感器(15)、用于使伺服活塞(11)移动的油流入的第一液压室(51)、将被供给来自泵的油的泵口与第一液压室(51)连通的第一活塞油路(65)以及将第一液压室(51)与排油口连通的排出循环油路(66)。

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10-11-2011 дата публикации

TURBO COMPRESSOR OPERATING ON EXHAUST GASES FOR THE INTERNAL COMBUSTION ENGINE

Номер: RU2010116524A

1. Турбокомпрессор, работающий на отработавших газах, для двигателя внутреннего сгорания, содержащий корпус (14) и ротор (18), при этом корпус (14) содержит выполненный с возможностью протекания участок (15) отвода отработавших газов, а ротор (18) содержит турбинное колесо (20) и вал (21), жестко соединенный на кручение с турбинным колесом (20), причем турбинное колесо (20) установлено в опорах с возможностью вращения в участке (15) отвода отработавших газов и выполнено с возможностью подачи на него отработавших газов, а в участке (15) отвода отработавших газов расположено направляющее устройство (29) для изменения подачи отработавших газов на турбинное колесо (20), причем направляющее устройство (29) включает в себя выполненное с возможностью протекания через него направляющее решетчатое кольцо (30) и осевую задвижку (31), а направляющее решетчатое кольцо (30) содержит стойку (37) для фиксированного опирания, а также направляющие лопатки (36), а осевая задвижка (31) выполнена с возможностью захватывания направляющих лопаток (36), ! отличающийся тем, что направляющее решетчатое кольцо (30) размещено таким образом, что направляющие лопатки (36) выполнены с возможностью захватывания осевой задвижкой (31), начиная от стойки (37). ! 2. Турбокомпрессор, работающий на отработавших газах, по п.1, отличающийся тем, что стойка (37) установлена на контурной втулке (32) направляющего устройства (29) соосно с осью (22) вращения. ! 3. Турбокомпрессор, работающий на отработавших газах, по п.1 или 2, отличающийся тем, что контурная втулка (32) выполнена в качестве центрирующего устройства (39). ! 4. Турбокомпрессор, работающий на отработавших газах, по п.1 или 2, отличающийся тем, что д� РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2010 116 524 (13) A (51) МПК F01D 17/14 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ, ПАТЕНТАМ И ТОВАРНЫМ ЗНАКАМ (12) ЗАЯВКА НА ИЗОБРЕТЕНИЕ (21)(22) Заявка: 2010116524/06, 10.09.2008 (71) Заявитель(и): ДАЙМЛЕР АГ (DE) Приоритет(ы): (30) ...

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08-09-2011 дата публикации

Internal combustion engine

Номер: DE102010010319A1
Принадлежит: DAIMLER AG

Die Erfindung betrifft eine Verbrennungskraftmaschine (10) für einen Kraftwagen, mit wenigstens zwei Brennräumen (12), insbesondere Zylindern (12), und mit wenigstens einem Abgasturbolader (22), welcher eine in einem Abgastrakt (28) der Verbrennungskraftmaschine (10) angeordnete Turbine (38) mit einem Turbinengehäuse (66) mit einem Aufnahmeraum (70) umfasst, in welchem ein Turbinenrad (68) drehbar aufgenommen ist, welches über wenigstens einen Spiralkanal (58a–d) des Turbinengehäuses (66) mit Abgas aus zumindest einem der Brennräume (12), insbesondere Zylinder (12), beaufschlagbar ist, wobei die Turbine (38) eine Versteileinrichtung (48) umfasst, mittels welcher ein Spiraleneintrittsquerschnitt (AS) und/oder ein Düsenquerschnitt (AR) des wenigstens einen Spiralkanals (58a–d) zum Aufnahmeraum (70) einstellbar ist, wobei die Verbrennungskraftmaschine (10) in einem Stauaufladungsbetrieb betreibbar ist. The invention relates to an internal combustion engine (10) for a motor vehicle, with at least two combustion chambers (12), in particular cylinders (12), and with at least one exhaust gas turbocharger (22) which has a turbine arranged in an exhaust gas tract (28) of the internal combustion engine (10) (38) with a turbine housing (66) with a receiving space (70) in which a turbine wheel (68) is rotatably received, which via at least one spiral duct (58a-d) of the turbine housing (66) with exhaust gas from at least one of the combustion chambers (12), in particular cylinder (12), can be acted upon, the turbine (38) comprising an adjusting device (48) by means of which a spiral inlet cross section (AS) and / or a nozzle cross section (AR) of the at least one spiral channel (58a-d) can be adjusted to the receiving space (70), the internal combustion engine (10) being operable in a ram charging mode.

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28-10-2010 дата публикации

Internal combustion engine and method for operating an internal combustion engine

Номер: WO2010121684A1
Принадлежит: DAIMLER AG

The invention relates to an internal combustion engine (10) having a high-pressure exhaust gas turbocharger (18) and a low-pressure exhaust gas turbocharger (20) connected in series, each comprising a turbine (22, 24, 24') at least on the exhaust gas side (14) of the internal combustion engine (10) through which exhaust from the internal combustion engine (10) flows, wherein a bypass (32) having a blow-off valve (34) received by a turbine housing (106) of the low-pressure exhaust gas turbocharger (20) is provided, by means of which the turbine (22) of the high-pressure exhaust gas turbocharger (18) can be bypassed by the exhaust gas, and the exhaust gas can be directed into an inlet flow (36, 38, 38', 38") of the turbine (24, 24') of the low-pressure exhaust gas turbocharger (20), wherein the turbine (24, 24') of the low-pressure exhaust gas turbocharger (20) comprises a first inlet flow (36, 38, 38', 38") by means of which the exhaust gas can be fed substantially in the radial direction of the turbine wheel (116) to a turbine wheel (116) received by the turbine housing (106) of the low-pressure exhaust gas turbocharger (20), and that the turbine (24, 24') of the low-pressure exhaust gas turbocharger (20) comprises a second inlet flow (36, 38, 38', 38") by means of which the exhaust gas can be fed to the turbine wheel (116) of the low-pressure exhaust gas turbocharger (20) substantially transverse or diagonal to the radial direction of the turbine wheel (116).

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28-10-2010 дата публикации

Internal combustion engine and method for operating an internal combustion engine

Номер: DE102009018583A1
Принадлежит: DAIMLER AG

Die Erfindung betrifft eine Verbrennungskraftmaschine (10) mit einem Hochdruck-Abgasturbolader (18) und einem zu diesem seriell geschalteten Niederdruck-Abgasturbolader (20), welche jeweils zumindest auf einer Abgasseite (14) der Verbrennungskraftmaschine (10) eine von einem Abgas der Verbrennungskraftmaschine (10) durchströmbare Turbine (22, 24, 24') aufweisen, wobei ein Bypass (32) mit einem durch ein Turbinengehäuse (106) des Niederdruck-Abgasturboladers (20) aufgenommenen Abblaseventil (34) vorgesehen ist, mittels welchem die Turbine (22) des Hochdruck-Abgasturboladers (18) vom Abgas umströmbar und das Abgas in eine Einströmflut (36, 38, 38', 38") der Turbine (24, 24') des Niederdruck-Abgasturboladers (20) leitbar ist, wobei die Turbine (24, 24') des Niederdruck-Abgasturboladers (20) eine erste Einströmflut (36, 38, 38', 38") aufweist, mittels welcher das Abgas einem durch das Turbinengehäuse (106) des Niederdruck-Abgasturboladers (20) aufgenommenen Turbinenrad (116) im Wesentlichen in radialer Richtung des Turbinenrads (116) zuführbar ist, und dass die Turbine (24, 24') des Niederdruck-Abgasturboladers (20) eine zweite Einströmflut (36, 38, 38', 38") aufweist, mittels welcher das Abgas dem Turbinenrad (116) des Niederdruck-Abgasturboladers (20) im Wesentlichen quer bzw. schräg zur radialen Richtung des Turbinenrads (116) zuführbar ist. The invention relates to an internal combustion engine (10) having a high-pressure exhaust gas turbocharger (18) and a low-pressure exhaust gas turbocharger (20) connected in series therewith, one of an exhaust gas of the internal combustion engine (10) at least on one exhaust side (14) of the internal combustion engine (10). 10) through-flow turbine (22, 24, 24 '), wherein a bypass (32) with a by a turbine housing (106) of the low-pressure exhaust gas turbocharger (20) recorded blow-off valve (34) is provided, by means of which the turbine (22) The exhaust gas can flow around the ...

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09-11-2006 дата публикации

Turbine with a turbine wheel for an exhaust gas turbocharger of an internal combustion engine and exhaust gas turbocharger for an internal combustion engine

Номер: WO2006117072A1
Принадлежит: DaimlerChrysler AG

The invention relates to a turbine with a turbine wheel for an exhaust gas turbocharger of an internal combustion engine, which comprises a hub, provided with turbine wheel blades and auxiliary blades, whereby said auxiliary blades are arranged on the hub in exhaust channels, delimited by two turbine wheel blades. According to said invention, the dimensions of the auxiliary blades (20) are fixed, whereby the ratio between a throughput parameter of the turbine wheel blades (6) and a throughput parameter of the auxiliary blades (20) is higher than 15. Said invention is mainly provided for exhaust gas turbochargers in the automotive industry.

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07-09-2005 дата публикации

Blade for a turbomachine and turbomachine

Номер: EP1571298A1
Автор: Christian Menke
Принадлежит: SIEMENS AG

The blade (1) has an upper platform (2a) and lower platform (2b) with blade (4) inbetween. At least one of the platforms is adjustable to vary the inflow surface of the blade. The or each platform can be mounted displaceable about a rotational axis (D). Independent claim describes method for operating turbo machine where the minimal flow cross-section can be set by adjusting the platforms in dependence on the load required.

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23-01-2014 дата публикации

Parallel diffuser for a fluid machine

Номер: WO2014012725A1
Автор: Klaus JACOBY
Принадлежит: SIEMENS AKTIENGESELLSCHAFT

The invention relates to a parallel diffuser (304) for a fluid machine (300), wherein the parallel diffuser comprises a housing with a fluid channel (310), which extends from an input region to an output region of the parallel diffuser, and at least one housing element (306), wherein the at least one housing element can be moved in a direction perpendicular to the direction of movement of a fluid, which flows from the input region to the output region of the parallel diffuser (304), and wherein the parallel diffuser comprises at least one blade element (305) which is arranged in the fluid channel (310).

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06-08-2013 дата публикации

Method and apparatus for enhancing compressor performance

Номер: US8500399B2
Принадлежит: Rolls Royce Corp

The present invention provides a non-axisymmetric flow member disposed in a duct of a gas turbine engine. The flow member narrows the area aft of a vane to reduce the cross sectional area through which a wake from the vane traverses.

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15-01-2009 дата публикации

EXHAUST BOLDER FOR AN INTERNAL COMBUSTION ENGINE

Номер: AT505407B1
Автор: [UNK]
Принадлежит: Ghm Engineering

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18-02-2009 дата публикации

Exhaust gas turbocharger for a combustion engine

Номер: EP2025880A2
Принадлежит: Jegel Franz Peter Ing

The turbocharger (2) has an exhaust gas turbine (1) and a compressor. The exhaust gas turbine has two groups of guide vanes. Guide vane channels are provided whose channel cross-sections are changed by a gate valve (8) and have larger radial components as guide vanes whose guide vane channel cross sections are changed. The gate valve has multiple runners distributed evenly over the area.

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08-11-2016 дата публикации

Inner turbine shell axial movement

Номер: US9488062B2
Принадлежит: General Electric Co

A clearance control system for a turbine having a stator assembly and a rotor assembly includes a hydraulic or pneumatic controller that axially drives, through a shaft, one or more actuators connected to the stator assembly casing. The controller causes relative movement between the stator and rotor assemblies to adjust the clearances between portions of the stator and rotor in accordance with the varying operating conditions of the turbine. More particularly, the controller moves the stator relative to the rotor in first and second axial directions to compensate for thermal expansion and contraction during the operating conditions of the turbine.

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31-03-1998 дата публикации

Radial rotary slide valve

Номер: JPH1082470A
Принадлежит: ABB Patent GmbH

(57)【要約】 【課題】本発明の目的は、ラジアル・ロータリ・スライ ド弁において、スライドギャップの幅を最適とし、か つ、タービンの運転に極めて危険なジャミングの発生を 防止、ないしは大幅に減少させることである。 【解決手段】 ロータリリングの上部2aとロータリリ ングの下部2bとが、適当な連結手段(8,9;11〜 15)により、2つの対向するハーフリングの少なくと も端部の間の距離が変えられるようになっており、こう して、ロータリリング2と固定リング1との間の、回動 に必要な、スライド遊びがとれるように、ロータリリン グの内径が変えられるようになっていることを特徴とす るラジアル・ロータリ・スライド弁。

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27-07-2017 дата публикации

Turbocharger with slide for flood connection

Номер: DE102016200812A1
Принадлежит: Bayerische Motoren Werke AG

Die Erfindung betrifft einen Turbolader (1) mit einer Turbine (3) zu der Abgase aus zwei Flutenkanälen (5, 6) zuführbar sind, zwischen denen eine Trennwand (7) verläuft, in der eine verschließbare Flutenverbindungsöffnung (4) ausgebildet ist, wobei die Flutenverbindungsöffnung (4) durch einen plattenförmigen Schieber (8) verschließbar ist, der entlang seiner Plattenebene (xy) zwischen die Flutenkanäle (5, 6) schiebbar ist. Darüber hinaus betrifft die Erfindung ein Kraftfahrzeug mit solch einem Turbolader (1). The invention relates to a turbocharger (1) with a turbine (3) to the exhaust gases from two flood channels (5, 6) can be supplied, between which a partition wall (7) extends, in which a closable flood connection opening (4) is formed, wherein the Flood connection opening (4) by a plate-shaped slide (8) is closable, along its plate plane (xy) between the flood channels (5, 6) can be pushed. Moreover, the invention relates to a motor vehicle with such a turbocharger (1).

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01-12-2011 дата публикации

Turbine for an exhaust gas turbocharger

Номер: DE102010021928A1
Принадлежит: DAIMLER AG

Die Erfindung betrifft eine Turbine für einen Abgasturbolader (22) einer Verbrennungskraftmaschine (10), mit zumindest einem Gehäuseteil (56), welches wenigstens zwei, von Abgas der Verbrennungskraftmaschine (10) durchströmbare und jeweilige Spiraleneintrittsquerschnitte (AS) aufweisende Spiralkanäle (58) umfasst, wobei das Gehäuseteil (56) in einem den Spiralkanälen (58) gemeinsamen, durch wenigstens ein weiteres Gehäuseteil (72) der Turbine (54) gebildeten Aufnahmeraum (74) aufgenommen ist, von welchem Abgas der Verbrennungskraftmaschine (10) über die jeweiligen Spiraleneintrittsquerschnitte (AS) in die Spiralkanäle (58) einströmbar ist. The invention relates to a turbine for an exhaust gas turbocharger (22) of an internal combustion engine (10), with at least one housing part (56) which comprises at least two spiral ducts (58) through which exhaust gas from the internal combustion engine (10) can flow and which have respective spiral inlet cross sections (AS), wherein the housing part (56) is accommodated in a receiving space (74) which is common to the spiral channels (58) and is formed by at least one further housing part (72) of the turbine (54), from which exhaust gas from the internal combustion engine (10) via the respective spiral inlet cross-sections (AS ) can flow into the spiral channels (58).

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09-11-1983 дата публикации

Centrifugal compressor

Номер: KR830008058A

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11-07-2007 дата публикации

Turbocharger

Номер: GB0710670D0
Автор: [UNK]
Принадлежит: Cummins Turbo Technologies Ltd

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29-04-1955 дата публикации

Improvements to turbo-machines

Номер: FR1093003A
Автор: Bernard Collignon
Принадлежит: SNCF Mobilites

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07-10-2005 дата публикации

SELF-CONDUCTING CONNECTION PIECE COULD BE CONNECTED TO A NEIGHBORING CONNECTION PIECE

Номер: FR2803442B1
Автор: Ariel Ruiz, Sylvain Barrat
Принадлежит: Entrelec SAS

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29-03-1985 дата публикации

Multistage centrifugal compressor

Номер: FR2552501A1
Автор: Helmuth O Jacobi
Принадлежит: Dresser Industries Inc

The multi-stage centrifugal compressor comprises a housing (10) with a flow path (22) from inlet (12) to outlet (16) passing through successive bladed stages (14) of the rotor on the drive shaft (20). This path comprises successive inter-stage portions defined by partitions (26,28,30,32; 34,33) in the housing. At least one (32,33) of these partitions has an annular disc, secured by screws to a partition (33), which has a side facing upstream and downstream side and is provided with axial bores to equalise the pressure between these sides.

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06-07-2001 дата публикации

SELF-STRIPPING CONNECTING PIECE THAT CAN BE CONNECTED TO A NEIGHBORING CONNECTING PIECE

Номер: FR2803442A1
Автор: Ariel Ruiz, Sylvain Barrat
Принадлежит: Entrelec SAS

Cette pièce (2) comporte une partie en forme de profilé présentant une section polygonale creuse au long de laquelle est ménagée longitudinalement une fente de dénudage et de retenue (6) pour au moins un fil.Une face (8) de la section polygonale est prolongée par une patte (18) recourbée vers la pièce de connexion, un espace destiné à recevoir une dent (24) d'un peigne d'interconnexion (26) subsistant entre la patte (18) recourbée et la pièce de connexion (2).

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16-05-1980 дата публикации

TURBINE WHEEL COVER

Номер: FR2439299A1
Автор: [UNK]
Принадлежит: Cummins Engine Co Inc

ENVELOPPE ENTOURANT UNE ROUE DE TELLE MANIERE QUE LE FLUIDE ABORDE CELLE-CI EN ETANT DANS UN ETAT UNIFORME. L'ENVELOPPE COMPREND AU MOINS UN CANAL EN SPIRALE QUI ENTOURE LA PERIPHERIE DE LA ROUE ET QUI COMPREND UNE ENTREE EXTERIEURE ET UNE SORTIE INTERIEURE, CETTE DERNIERE ENTOURANT LA PERIPHERIE DE LA ROUE. LE CANAL EST DELIMITE PAR DEUX PAROIS LATERALES QUI SONT SYMETRIQUES PAR RAPPORT A L'AXE DE LA ROUE ET DONT LA CIRCONFERENCE INTERIEURE EST PROCHE DE LA PERIPHERIE DE CETTE DERNIERE. UNE PAROI EXTERIEURE DISPOSEE ENTRE LES DEUX PAROIS LATERALES SE PROLONGE SUR LA CIRCONFERENCE SUR AU MOINS 360 D'ARC AUTOUR DE L'AXE DE LA TURBINE. LA POSITION RADIALE DE LA PAROI EXTERIEURE EST DETERMINEE PAR LE TRAJET PRESCRIT PAR LA DIRECTION DE L'ECOULEMENT DU FLUIDE DE MANIERE QUE CELUI-CI AIT LA FORME D'UN TOURBILLON LIBRE CONTENU PAR LES PAROIS LATERALES. APPLICATION AVANTAGEUSE AUX TURBO-COMPRESSEURS DES MOTEURS A COMBUSTION INTERNE. ENCLOSURE SURROUNDING A WHEEL IN SUCH A WAY THAT THE FLUID APPROACHES IT WHILE IN A UNIFORM STATE. THE ENCLOSURE INCLUDES AT LEAST ONE SPIRAL CHANNEL SURROUNDING THE WHEEL PERIPHERY AND WHICH INCLUDES AN EXTERNAL INLET AND AN INTERNAL EXIT, THE LATTER SURROUNDING THE WHEEL PERIPHERY. THE CHANNEL IS BOUNDED BY TWO SIDE WALLS WHICH ARE SYMMETRICAL WITH THE AXIS OF THE WHEEL AND WHOSE INTERNAL CIRCUMFERENCE IS CLOSE TO THE PERIPHERY OF THE LATTER. AN EXTERIOR WALL ARRANGED BETWEEN THE TWO SIDE WALLS EXTENDS ON THE CIRCUMFERENCE FOR AT LEAST 360 ARC AROUND THE TURBINE AXIS. THE RADIAL POSITION OF THE OUTER WALL IS DETERMINED BY THE ROUTE PRESCRIBED BY THE DIRECTION OF FLUID FLOWING SO THAT IT HAS THE FORM OF A FREE VIRGIN CONTAINED BY THE SIDE WALLS. ADVANTAGEOUS APPLICATION TO TURBO-COMPRESSORS OF INTERNAL COMBUSTION ENGINES.

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25-02-1966 дата публикации

Turbomachine

Номер: FR1429796A
Автор:
Принадлежит: Gebrueder Sulzer AG, Sulzer Ag

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12-06-1998 дата публикации

EXHAUST GAS TURBOCHARGER TURBINE ENGINE FOR AN INTERNAL COMBUSTION ENGINE

Номер: FR2756867A1
Принадлежит: Daimler Benz AG

La turbine d'échappement d'un turbocompresseur comprend un tiroir axial pourvu d'une grille de guidage à aubes directrices pouvant coulisser axialement dans une fente annulaire entre le carter de turbine et un guide intérieur pour le réglage de la pression d'alimentation du compresseur. Le tiroir axial (4) peut être engagé par sa grille de guidage (9) dans un espace annulaire radial (8) servant à l'écoulement des gaz entre le carter de turbine (1) et la roue de turbine (7). Dans une position reculée du tiroir (4), dans laquelle la grille (9), possédant des aubes directrices (10), n'est pas engagée dans l'espace annulaire radial (8), le tiroir (4) démasque une ouverture de sortie (11) menant à un canal d'évacuation de gaz (12), ménagés tous deux dans le guide intérieur (6). Applicable notamment aux moteurs de véhicules automobiles. The exhaust turbine of a turbocharger comprises an axial slide provided with a guide grid with guide vanes which can slide axially in an annular slot between the turbine housing and an internal guide for adjusting the supply pressure of the compressor. . The axial slide (4) can be engaged by its guide grid (9) in a radial annular space (8) serving for the flow of gases between the turbine housing (1) and the turbine wheel (7). In a retracted position of the slide (4), in which the grid (9), having guide vanes (10), is not engaged in the radial annular space (8), the slide (4) unmasks an opening of outlet (11) leading to a gas discharge channel (12), both provided in the inner guide (6). Applicable in particular to motor vehicle engines.

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28-08-1987 дата публикации

APPARATUS AND METHOD FOR CALIBRATING A MOBILE DIFFUSER WALL OF A CENTRIFUGAL COMPRESSOR

Номер: FR2594969A1
Автор: Thomas M Zinsmeyer
Принадлежит: Carrier Corp

Appareil et procédé d'initialisation et de calibration d'un système de réfrigération commandé par microprocesseur comprenant un compresseur centrifuge ayant une section formant diffuseur de largeur variable. (CF DESSIN DANS BOPI)

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28-03-1986 дата публикации

NOVEL TURBINE WHEEL DESIGN, SUCH AS A RELAXATION TURBINE, AND METHOD OF USING SUCH A WHEEL

Номер: FR2513312B1
Автор: [UNK]
Принадлежит: Bedue Abel

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23-03-2001 дата публикации

EXHAUST GAS TURBOCHARGER TURBINE FOR AN INTERNAL COMBUSTION ENGINE

Номер: FR2756867B1
Принадлежит: Daimler Benz AG

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18-03-1960 дата публикации

Turbo machine

Номер: FR1211950A
Автор:
Принадлежит: Gebrueder Sulzer AG, Sulzer Ag

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24-11-1989 дата публикации

DIFFUSER CONSTRUCTION FOR A CENTRIFUGAL COMPRESSOR

Номер: FR2552501B1
Автор: Helmuth O Jacobi
Принадлежит: Dresser Industries Inc

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15-10-1929 дата публикации

Device for adjusting the operating conditions of centrifugal machines

Номер: FR667306A
Автор:
Принадлежит: Rateau SA

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31-01-2014 дата публикации

VARIABLE SECTION BLOWER TUBE WITH REAR GRILLE TRANSLATION

Номер: FR2993860A1
Автор: Timothy Gormley
Принадлежит: Rohr Inc

Tuyère de soufflante à section variable (VAFN) (150,154) de moteur à double flux (110) d'aéronef ayant une extrémité avant (410) et étant supportée en continu à l'intérieur d'un évidement circonférentiel (404) dans la paroi (402) de la nacelle (118,400) devant de celle-ci. En fonctionnement, la VAFN se translate vers l'arrière et l'avant mais a toujours son extrémité avant (410) à l'intérieur de l'évidement. Des éléments d'étanchéité aident à étanchéifier l'évidement contre la VAFN. Un réseau d'ouvertures (158) avec des aubes (360,362,622) faisant face à l'arrière, appelé grille arrière, est construit à l'intérieur de la VAFN. Les ouvertures sont cachées à l'intérieur de l'évidement lorsque la VAFN est dans les positions les plus vers l'avant, et sont exposées pour permettre à l'air de s'écouler du conduit de dérivation à travers la grille lorsque la VAFN est dans les positions vers l'arrière. Les grilles arrière peuvent avoir différentes directions d'écoulement d'air basées sur leurs emplacements autour du moteur. Variable area blower nozzle (VAFN) (150,154) of an aircraft double flow motor (110) having a front end (410) and being continuously supported within a circumferential recess (404) in the wall (402) of the nacelle (118,400) in front of it. In operation, the VAFN is translated backwards and forwards but still has its front end (410) inside the recess. Sealing elements help seal the recess against the VAFN. An array of openings (158) with rear-facing blades (360,362,622), referred to as the back gate, is constructed within the VAFN. The openings are hidden inside the recess when the VAFN is in the most forward positions, and are exposed to allow air to flow from the bypass duct through the grate when the VAFN is in the rearward positions. The rear grilles may have different airflow directions based on their locations around the engine.

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10-05-2012 дата публикации

Turbo compressor driven by ice exhaust gases

Номер: RU2450127C2
Принадлежит: Даймлер Аг

FIELD: engines and pumps. SUBSTANCE: proposed turbo compressor comprises housing 14 and rotor 18. Note here that housing comprises exhaust gas discharge section 15 while rotor 18 comprises turbine impeller 20 and shaft 21 with rotational axis 22 rigidly jointed with said impeller 20. Note here said impeller runs in bearings in said section 15 driven by exhaust gases. Note also that guide device 29 is arranged in said section to vary feed of said gases to turbine impeller 20. Note here that said guide device 29 comprises guide grid wheel 30 and axial gate 31 while said grid wheel comprises locking post and guide vanes 36 while axial gate 31 may grip guide vanes 36. In compliance with this invention aforesaid guide grid wheel 30 comprises guide vanes 36 to be gripped by axial gate beginning from post 37. EFFECT: higher reliability. 8 cl, 3 dwg РОССИЙСКАЯ ФЕДЕРАЦИЯ (19) RU (11) 2 450 127 (13) C2 (51) МПК F01D 17/14 (2006.01) F02B 37/18 (2006.01) F02C 6/12 (2006.01) ФЕДЕРАЛЬНАЯ СЛУЖБА ПО ИНТЕЛЛЕКТУАЛЬНОЙ СОБСТВЕННОСТИ (12) ОПИСАНИЕ ИЗОБРЕТЕНИЯ К ПАТЕНТУ (21)(22) Заявка: 2010116524/06, 10.09.2008 (24) Дата начала отсчета срока действия патента: 10.09.2008 (72) Автор(ы): ФЛЕДЕРСБАХЕР Петер (DE), ХИРТ Торстен (DE) (73) Патентообладатель(и): ДАЙМЛЕР АГ (DE) R U Приоритет(ы): (30) Конвенционный приоритет: 28.09.2007 DE 102007046458.6 (43) Дата публикации заявки: 10.11.2011 Бюл. № 31 2 4 5 0 1 2 7 (45) Опубликовано: 10.05.2012 Бюл. № 13 (56) Список документов, цитированных в отчете о поиске: WO 2007/031752, 22.03.2007. SU 1271987 A1, 23.11.1986. RU 2003820 C1, 30.11.1993. RU 2296869 C2, 10.04.2007. WO 2006/133838 A1, 21.12.2006. DE 3839968 A1, 31.05.1990. 2 4 5 0 1 2 7 R U (86) Заявка PCT: EP 2008/007395 (10.09.2008) C 2 C 2 (85) Дата начала рассмотрения заявки PCT на национальной фазе: 28.04.2010 (87) Публикация заявки РСТ: WO 2009/043430 (09.04.2009) Адрес для переписки: 101000, Москва, М.Златоустинский пер., 10, кв.15, "ЕВРОМАРКПАТ", пат.пов. М.Б. Веселицкому, рег.№ 503 ( ...

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11-10-2012 дата публикации

Turbine for an exhaust gas turbocharger and internal combustion engine with such a turbine

Номер: WO2012136234A1
Принадлежит: DAIMLER AG

The invention relates to a turbine (44) for an exhaust gas turbocharger (20) of an internal combustion engine (10), having a turbine housing (50) through which exhaust gas from the internal combustion engine (10) flows and in which a turbine wheel (66) is received at least in some regions so as to be rotatable about an axis of rotation (22). The turbine housing has at least two flow sections (42, 48) through each of which at least a part of the exhaust gas can flow and which are fluidically separated from one another at least in some regions. At least one nozzle (70, 72) is associated with said flow sections, via which nozzle exhaust gas flowing through the respective flow section (42, 48) can be fed to the turbine wheel (66) so that exhaust gas can act on the turbine wheel (66). A first adjusting unit (74) is associated with at least a first one of the nozzles (70, 72), wherein said adjusting unit can variably adjust a flow cross-section (Sλ,S AGR ) of the first nozzle (70, 72) which has flowing through it the exhaust gas which flows through the associated flow section (70, 72). A second adjusting unit (76) is provided which is disposed at least partially in a turbine wheel outlet region (78) and by means of which flow conditions can be influenced at least substantially in the turbine wheel outlet region (78).

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18-06-2014 дата публикации

Variable geometry turbine assembly

Номер: GB201408087D0
Автор: [UNK]
Принадлежит: Cummins Ltd

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16-05-1981 дата публикации

Method and apparatus for surge detection and control in centrifugal gas compressors

Номер: ES8105071A1
Автор: [UNK]
Принадлежит: Westinghouse Electric Corp

A centrifugal gas compressor having a shrouded rotatable impeller 14 in an impeller chamber 40, and provided with capacity control vanes 30 and a diffuser passage 18 throttle plate 38, is provided with surge control means including a thermistor 50 which senses a temperature rise beyond a predetermined value in the impeller chamber and exterior of the gas flow path through the impeller, and through relay means such as 52, 58 electrically connected to the thermistor 50 operates to change the compressor operation to a nonsurging condition.

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04-04-1989 дата публикации

Diffuser construction for a centrifugal compressor

Номер: CA1252075A
Автор: Helmuth O. Jacobi
Принадлежит: Dresser Industries Inc

DIFFUSER CONSTRUCTION FOR A CENTRIFUGAL COMPRESSOR Abstract of the Disclosure Constant flow width through the last stage diffuser of a centrifugal compressor is maintained against widening by the forces of differential pressure via a diffuser defined between oppositely positioned radial faces of a diaphragm and an annular diffuser plate secured spaced from the diaphragm at the desired with. Enabling the diffuser plate to withstand width deflection and/or enlargement is a pressure balance imposed against the rear surface of the plate as compared to the pressure level incurred from the gas flow at the front surface facing the diaphragm. This is achieved by a sealed radial cavity exposed to the rear surface of the plate and in continuous pressure communica-tion with the front surface through a plurality of vent holes extending therebetween.

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29-07-1980 дата публикации

Variable-capacity radial turbine

Номер: US4214850A
Автор: Shojiro Sato
Принадлежит: IHI Corp

A variable-capacity radial turbine is provided with a gas flow rate control plate which may throttle a restriction of a scroll-shaped channel of a turbine casing, through which flows the exhaust gases into a turbine impeller, so that the impeller may rotate substantially at a constant speed and consequently the intake pressure may be maintained constant over a predetermined engine speed range.

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24-05-2007 дата публикации

Sliding piston cartridge and turbocharger incorporating same

Номер: WO2007058647A1
Принадлежит: HONEYWELL INTERNATIONAL INC.

A sliding piston cartridge (50)for a turbocharger (20) that is insertable into a bore (44) in the turbine housing (38) as a unit and that includes all of the components of a sliding piston type variable nozzle. The sliding piston cartridge comprises a carrier (52) having a tubular portion that interfaces with the bore of the turbine housing. A sliding piston (62) is disposed within the carrier and makes sliding contact therewith. Vanes (58) are mounted on or formed as a part of the carrier at its upstream end, the vanes extending across a turbine nozzle. The piston slides between a closed position and an open position relative to the carrier. The tubular portion of the carrier can include openings (66) that are progressively uncovered by the piston as it moves toward the open position, to allow additional flow to enter the turbine wheel without passing through the vanes.

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04-06-1992 дата публикации

ASSEMBLY OF A SLIDING WALL IN THE INLET OF A RADIAL TURBINE.

Номер: DE68901359D1
Автор: Peter Mckean
Принадлежит: Holset Engineering Co Ltd

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22-02-1966 дата публикации

Turbine

Номер: US3236500A
Автор: Kofink Siegfried
Принадлежит: GERATEBAU EBERSPACHER oHG

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24-02-2016 дата публикации

Variable geometry inlet system

Номер: EP2987989A1
Принадлежит: Pratt and Whitney Canada Corp

A variable geometry inlet system (11 a) of an aircraft engine includes an inlet duct. The inlet duct includes at least first and second sections (40,42) moveable between extended and retracted positions such that the inlet duct defines a variable axial length of an inlet passage for selective flight conditions. The inclusion of acoustic treatment may assist in controlling noise.

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24-04-1980 дата публикации

Turbine housing

Номер: AU5197579A
Автор: Paul M. Chapple
Принадлежит: Cummins Engine Co Inc

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