US20100021287A1 - Turbine housing insert in sliding variable-geometry turbocharger - Google Patents

Turbine housing insert in sliding variable-geometry turbocharger Download PDF

Info

Publication number
US20100021287A1
US20100021287A1 US12/179,309 US17930908A US2010021287A1 US 20100021287 A1 US20100021287 A1 US 20100021287A1 US 17930908 A US17930908 A US 17930908A US 2010021287 A1 US2010021287 A1 US 2010021287A1
Authority
US
United States
Prior art keywords
insert
groove
turbocharger
piston
split ring
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Abandoned
Application number
US12/179,309
Other languages
English (en)
Inventor
Emmanuel Bouvier
Lorrain Sausse
Pierre Barthelet
Manuel Marques
Laurent Vautier
Francis Abel
Alain Claudon
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Honeywell International Inc
Original Assignee
Honeywell International Inc
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Honeywell International Inc filed Critical Honeywell International Inc
Priority to US12/179,309 priority Critical patent/US20100021287A1/en
Assigned to HONEYWELL INTERNATIONAL, INC. reassignment HONEYWELL INTERNATIONAL, INC. ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: VAUTIER, LAURENT, ABEL, FRANCIS, BARTHELET, PIERRE, BOUVLER, EMMANUEL, Claudon, Alain, MARQUES, MANUEL, SAUSSE, LORRAIN
Priority to EP09164972.3A priority patent/EP2148043A3/fr
Publication of US20100021287A1 publication Critical patent/US20100021287A1/en
Assigned to UNITED STATES DEPARTMENT OF ENERGY reassignment UNITED STATES DEPARTMENT OF ENERGY CONFIRMATORY LICENSE (SEE DOCUMENT FOR DETAILS). Assignors: HONEYWELL TURBO TECHNOLOGIES
Abandoned legal-status Critical Current

Links

Images

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • F01D17/143—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path the shiftable member being a wall, or part thereof of a radial diffuser
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/246—Fastening of diaphragms or stator-rings
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C6/00—Plural gas-turbine plants; Combinations of gas-turbine plants with other apparatus; Adaptations of gas-turbine plants for special use
    • F02C6/04—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output
    • F02C6/10—Gas-turbine plants providing heated or pressurised working fluid for other apparatus, e.g. without mechanical power output supplying working fluid to a user, e.g. a chemical process, which returns working fluid to a turbine of the plant
    • F02C6/12—Turbochargers, i.e. plants for augmenting mechanical power output of internal-combustion piston engines by increase of charge pressure
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/40—Application in turbochargers
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2240/00—Components
    • F05D2240/55—Seals

Definitions

  • the present invention relates generally to turbochargers, and relates more particularly to exhaust gas-driven turbochargers having an axially sliding piston for varying the size of a nozzle opening leading into the turbine wheel of the turbine so as to regulate flow through the turbine.
  • Regulation of the exhaust gas flow through the turbine of an exhaust gas-driven turbocharger provides known operational advantages in terms of improved ability to control the amount of boost delivered by the turbocharger to the associated internal combustion engine.
  • the regulation of exhaust gas flow is accomplished by incorporating variable geometry into the nozzle that leads into the turbine wheel. By varying the size of the nozzle flow area, the flow into the turbine wheel can be regulated, thereby regulating the overall boost provided by the turbocharger's compressor.
  • Variable-geometry nozzles for turbochargers generally fall into two main categories: variable-vane nozzles, and sliding-piston nozzles. Vanes are often included in the turbine nozzle for directing the exhaust gas into the turbine in an advantageous direction. Typically a row of circumferentially spaced vanes extend axially across the nozzle. Exhaust gas from a chamber surrounding the turbine wheel flows generally radially inwardly through passages between the vanes, and the vanes turn the flow to direct the flow in a desired direction into the turbine wheel. In a variable-vane nozzle, the vanes are rotatable about their axes to vary the angle at which the vanes are set, thereby varying the flow area of the passages between the vanes.
  • the nozzle may also include vanes, but the vanes are fixed in position. Variation of the nozzle flow area is accomplished by an axially sliding piston that slides in a bore in the turbine housing.
  • the piston is tubular and is located just radially inwardly of the nozzle. Axial movement of the piston is effective to vary the axial extent of the nozzle opening leading into the turbine wheel.
  • the piston can slide adjacent to radially inner (i.e., trailing) edges of the vanes; alternatively, the piston and vanes can overlap in the radial direction and the piston can include slots for receiving at least a portion of the vanes as the piston is slid axially to adjust the nozzle opening.
  • variable nozzle offers the advantage of being mechanically simpler than the variable-vane nozzle. Nevertheless, other drawbacks have generally been associated with sliding-piston type variable nozzles.
  • a linkage coupled to the piston for effecting axial movement of the piston has been disposed in the exhaust gas flow stream exiting the turbine.
  • the downstream end of the piston has often been attached to arms that connect to a control rod of an actuator located adjacent an exterior side of the turbine housing directly behind the piston.
  • the control rods penetrates through an opening in the turbine housing. The presence of the control rod and arms in the flow stream deleteriously affects the flow of the exhaust gas, which impairs turbocharger performance.
  • sliding-piston type variable nozzles Another disadvantage of some sliding-piston type variable nozzles is that the sliding piston directly engages the inner surface of the bore in the turbine housing.
  • the turbine housing typically is cast, and the as-cast surface of the bore is not dimensionally accurate enough and smooth enough to ensure good sealing between the piston and bore. Consequently, the bore must be machined to precise dimensional tolerances to ensure proper sealing.
  • the bore is relatively large, and thus a significant amount of precision machining must be performed.
  • the present disclosure concerns a turbocharger that includes a thin-walled insert installed in the bore of the turbine housing.
  • the insert is generally ring-shaped and is radially resilient.
  • the outer surface of the piston slides against the inner surface of the insert, and in preferred embodiments a piston ring that encircles the piston engages the inner surface of the insert to substantially seal the interface between the insert and the piston.
  • the insert can be made of sheet metal formed into a ring shape. Because the insert (rather than the turbine housing bore) defines the surface for sealing with the piston, precise machining of the bore is not necessary, and if desired the inner surface of the bore can be as cast.
  • the bore of the turbine housing defines a circumferential or annular groove of slightly greater diameter than the adjacent portions of the bore. At least part of the insert is disposed in the groove to restrain axial movement of the insert.
  • the axial length of the groove is sufficient to receive the full axial length of the insert in the groove.
  • the groove has at least one end wall that engages one side of the insert.
  • the other side of the insert is engaged by at least one retainer formed separately from the turbine housing and releasably affixed to the turbine housing.
  • the retainer can comprise a bolt or pin installed in a hole in the turbine housing.
  • the bolt or pin has an enlarged head or a washer (either separately formed from or integrally formed with the bolt or pin) that engages the other side of the insert to restrain its axial movement.
  • the turbine housing bore itself defines a second end wall facing axially toward the first end wall and spaced therefrom by the axial length of the insert.
  • the two end walls engage the opposite sides of the insert to restrain axial movement thereof.
  • the insert comprises a split ring such that the insert is resiliently contractible and expandable in diameter. In a relaxed state, the insert has a greater outside diameter than the groove. The insert is slightly compressed in diameter to install it in the groove, and then the insert springs back toward its relaxed diameter such that it is continually urged against the bottom surface of the groove.
  • the split in the ring is straight and oriented either parallel or non-parallel to the axial direction.
  • the split is zigzagged, crenellated, or wavy.
  • the split ring can be formed such that in its relaxed state the two ends of the split ring are axially offset from each other by a small amount such that the axial length of the split ring exceeds the axial length of the groove.
  • the ends of the split ring are axially compressed between the end walls of the groove, which helps to maintain the insert in proper position in the groove.
  • the insert can include a radially outwardly projecting flange at one axial end of the insert, and the groove can be sized to receive the flange while the remainder of the insert is outside the groove.
  • the insert can also include a radially inwardly projecting flange at its opposite end. The flanges enhance the hoop stiffness of the insert to resist deformations that would tend to cause the insert to become non-circular in shape.
  • FIG. 1 is a cross-sectional view of a turbocharger in accordance with a first embodiment of the invention
  • FIG. 2 is magnified portion of FIG. 1 ;
  • FIG. 3A is a side view of an insert in accordance with one embodiment of the invention.
  • FIG. 3B is a cross-sectional view of the insert of FIG. 3A ;
  • FIG. 4A is a side view of an insert in accordance with another embodiment of the invention.
  • FIG. 4B is a cross-sectional view of the insert of FIG. 4A ;
  • FIG. 5A is a side view of an insert in accordance with a further embodiment of the invention.
  • FIG. 5B is a cross-sectional view of the insert of FIG. 5A ;
  • FIG. 6A is a side view of an insert in accordance with still another embodiment of the invention.
  • FIG. 6B is a cross-sectional view of the insert of FIG. 6A ;
  • FIG. 7 is a cross-sectional view of a turbine housing and insert in accordance with another embodiment of the invention.
  • FIG. 8 is a magnified portion of FIG. 7 .
  • the turbocharger includes a center housing 22 that contains bearings (not shown) for a rotary shaft 26 of the turbocharger.
  • a compressor housing 28 is coupled to one side of the center housing.
  • a compressor wheel 30 is mounted on one end of the shaft 26 and is disposed in the compressor housing.
  • the compressor housing defines an inlet 32 through which air is drawn into the compressor wheel 30 , which compresses the air, and further defines a diffuser through which the compressed air is discharged from the compressor wheel into a volute 34 surrounding the compressor wheel. From the volute, the air is delivered to the intake of an internal combustion engine (not shown).
  • the turbocharger further comprises a turbine housing 38 coupled to the opposite side of the center housing 22 .
  • a turbine wheel 40 is mounted on the opposite end of the shaft 26 from the compressor wheel and is disposed in the turbine housing.
  • the turbine housing defines a chamber 42 that surrounds the turbine wheel 40 and receives exhaust gas from the internal combustion engine. Exhaust gas is directed from the chamber 42 into the turbine wheel 40 , which expands the exhaust gas and is driven thereby so as to drive the compressor wheel.
  • the turbine housing 38 defines a generally cylindrical bore 44 disposed generally radially inwardly of the chamber 42 .
  • the turbine wheel 40 resides in an upstream end of the bore 44 and the turbine wheel's rotational axis is substantially coaxial with the bore.
  • upstream in this context refers to the direction of exhaust gas flow through the bore 44 , as the exhaust gas in the chamber 42 flows into the turbine wheel 40 and is then turned to flow generally axially (left to right in FIG. 1 ) through the bore 44 , and is then discharged through a discharge conduit 45 .
  • the turbocharger further comprises a piston 60 of generally tubular form.
  • the piston is coaxially disposed within the bore 44 and is slidable in the axial direction.
  • the piston is slidable between a closed position, a partially open position, and an open position.
  • exhaust gas can flow from the chamber 42 radially inwardly through a nozzle defined between a wall 50 and an end or flange 62 of the piston, and into the turbine wheel 40 .
  • vanes 52 extend at least partway across the nozzle for guiding the flow through the nozzle.
  • the piston can be actuated by any of various actuator mechanisms, one example of which is an “in-line” actuator 64 such as shown in FIG. 1 .
  • the turbine housing 38 typically is cast and thus does not have precise dimensional tolerances on the bore 44 .
  • the as-cast surface of the bore 44 is also not very smooth.
  • an insert 70 is installed in the bore 44 of the turbine housing.
  • the insert 70 is a thin-walled ring-shaped structure, which advantageously can be made of sheet metal.
  • the wall thickness of the insert 70 measured in the radial direction between the inner and outer surfaces of the insert, can range from about 0.2 mm to about 1 mm.
  • the radially inner surface of the insert 70 forms the surface that is engaged by the piston 60 as the piston slides back and forth.
  • a sealing ring 72 is retained in a groove in the outer surface of the piston for engaging the inner surface of the insert 70 in order to seal the interface therebetween so that exhaust gas is substantially prevented from leaking between the piston and the insert.
  • the turbine housing bore 44 includes a groove 46 for retaining the insert 70 .
  • the groove's bottom surface is generally cylindrical and is of slightly greater diameter than the adjacent portions of the bore 44 .
  • the groove has at least one axially facing end wall that delimits at least one end of the groove's axial length.
  • the insert 70 is disposed in the groove, and the end wall engages the insert to restrain axial movement of the insert.
  • the groove 46 in some embodiments of the invention can be sized in diameter such that there is a slight radial clearance between the insert and the bottom wall of the groove, which can provide mechanical and thermal decoupling between the insert and the turbine housing. In other embodiments, there is substantially no such radial clearance.
  • an end wall of the groove 46 engages one side of the insert 70 .
  • the other side of the insert is engaged by at least one retainer (not shown) formed separately from the turbine housing and releasably affixed to the turbine housing.
  • the retainer can comprise a bolt or pin installed in a hole in the turbine housing.
  • the bolt or pin has an enlarged head or a washer (either separately formed from or integrally formed with the bolt or pin) that engages the other side of the insert to restrain its axial movement.
  • the groove 46 itself defines a second end wall facing axially toward the first end wall and spaced therefrom by the axial length of the insert 70 .
  • the two end walls engage the opposite sides of the insert to restrain axial movement thereof.
  • the insert 70 can be of various configurations.
  • the insert 70 comprises a split ring such that the insert is resiliently contractible and expandable in diameter. In a relaxed state, the insert has a greater outside diameter than the groove 46 . The insert is slightly compressed in diameter to install it in the groove, and a restoring spring force of the split ring urges the split ring radially outwardly against the bottom surface of the groove, whereby the radial clearance between the insert and the groove is substantially zero.
  • the split 74 in the ring is straight and oriented parallel to the axial direction.
  • an insert 70 ′ has a split 74 ′ that is straight and oriented non-parallel to the axial direction.
  • FIGS. 5A and 5B illustrate a further alternative insert 70 ′′ that has a “wavy” or zigzag-shaped split 74 ′′.
  • These split configurations are thought to be advantageous in terms of reducing leakage of exhaust gas through the pathway formed by the split.
  • any of the split ring inserts 70 , 70 ′, 70 ′′ can be formed such that in its relaxed state the two ends of the split ring are axially offset from each other by a small amount so that the axial length of the split ring exceeds the axial length of the groove 46 in the turbine housing.
  • the ends of the split ring are axially compressed between the end walls of the groove, which helps to maintain the insert in proper position in the groove.
  • FIGS. 7 and 8 illustrate yet another embodiment of the invention.
  • the turbine housing 238 defines a circumferential groove 246 that has a substantially smaller axial length than that of the insert 270 .
  • the insert 270 has a radially outwardly projecting ring or flange 271 at one axial end of the insert.
  • the flange 271 is engaged in the groove 246 in such a manner that the insert is retained by the groove and is substantially fixed against axial movement as the piston slides back and forth.
  • the flange 271 in addition to serving the function of fixing the insert in position, also enhances the “hoop” stiffness of the insert so as to better maintain the circularity of the insert.
  • the insert can also include a similar flange 273 at its opposite axial end, for further enhancing the hoop stiffness of the insert.
  • the flange 273 projects radially inwardly rather than outwardly.
  • the flanges 271 , 273 can each extend continuously a full 360°. Alternatively, one of both of the flanges can extend for less than a full 360°. In some embodiments, one or both of the flanges can be formed as a plurality of circumferentially spaced flange segments each occupying less than 180° of arc. It should also be noted that both flanges 271 , 273 are not essential, and in particular the radially inwardly projecting flange 273 can be omitted if it is not needed for stiffening.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Chemical Kinetics & Catalysis (AREA)
  • General Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Supercharger (AREA)
US12/179,309 2008-07-24 2008-07-24 Turbine housing insert in sliding variable-geometry turbocharger Abandoned US20100021287A1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US12/179,309 US20100021287A1 (en) 2008-07-24 2008-07-24 Turbine housing insert in sliding variable-geometry turbocharger
EP09164972.3A EP2148043A3 (fr) 2008-07-24 2009-07-08 Turbocompresseur à géométrie variable avec piston et insert monté dans l'alésage du carter de turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US12/179,309 US20100021287A1 (en) 2008-07-24 2008-07-24 Turbine housing insert in sliding variable-geometry turbocharger

Publications (1)

Publication Number Publication Date
US20100021287A1 true US20100021287A1 (en) 2010-01-28

Family

ID=40908905

Family Applications (1)

Application Number Title Priority Date Filing Date
US12/179,309 Abandoned US20100021287A1 (en) 2008-07-24 2008-07-24 Turbine housing insert in sliding variable-geometry turbocharger

Country Status (2)

Country Link
US (1) US20100021287A1 (fr)
EP (1) EP2148043A3 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012097365A1 (fr) * 2011-01-14 2012-07-19 Flexible Metal, Inc. Carter de turbine coulée ayant une volute emboutie
US20150361875A1 (en) * 2013-04-10 2015-12-17 Cummins Ltd Variable geometry turbine
US11453090B2 (en) 2020-05-26 2022-09-27 Raytheon Technologies Corporation Piston seal assembly guards and inserts for seal groove

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8992165B2 (en) 2010-09-22 2015-03-31 Cummins Turbo Technologies Limited Variable geometry turbine
GB201417995D0 (en) * 2014-10-10 2014-11-26 Cummins Ltd Variable geometry turbine
CN108930586A (zh) * 2018-06-29 2018-12-04 大连海事大学 一种变几何涡轮及喷嘴环装置

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4071183A (en) * 1975-04-18 1978-01-31 General Electric Company Fabrication method and fabricated article
US6928816B2 (en) * 2001-09-10 2005-08-16 Malcolm George Leavesley Turbocharger apparatus
US20070122268A1 (en) * 2005-11-29 2007-05-31 Lombard Alain R Turbocharger with sliding piston assembly
US20070227603A1 (en) * 2003-12-10 2007-10-04 Jean-Luc Perrin Variable Nozzle Device for a Turbocharger

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3828756A (en) * 1969-08-06 1974-08-13 J Kammeraad Method and apparatus for rebuilding valve guides
WO2007058647A1 (fr) * 2005-11-16 2007-05-24 Honeywell International Inc. Cartouche a piston coulissant et turbocompresseur dote d'une telle cartouche

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4071183A (en) * 1975-04-18 1978-01-31 General Electric Company Fabrication method and fabricated article
US6928816B2 (en) * 2001-09-10 2005-08-16 Malcolm George Leavesley Turbocharger apparatus
US20070227603A1 (en) * 2003-12-10 2007-10-04 Jean-Luc Perrin Variable Nozzle Device for a Turbocharger
US20070122268A1 (en) * 2005-11-29 2007-05-31 Lombard Alain R Turbocharger with sliding piston assembly

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2012097365A1 (fr) * 2011-01-14 2012-07-19 Flexible Metal, Inc. Carter de turbine coulée ayant une volute emboutie
US20150361875A1 (en) * 2013-04-10 2015-12-17 Cummins Ltd Variable geometry turbine
US9945286B2 (en) * 2013-04-10 2018-04-17 Cummins Ltd. Variable geometry turbine
US11453090B2 (en) 2020-05-26 2022-09-27 Raytheon Technologies Corporation Piston seal assembly guards and inserts for seal groove
US11945063B2 (en) 2020-05-26 2024-04-02 Rtx Corporation Piston seal assembly guards and inserts for seal groove

Also Published As

Publication number Publication date
EP2148043A2 (fr) 2010-01-27
EP2148043A3 (fr) 2013-06-26

Similar Documents

Publication Publication Date Title
EP2557275B1 (fr) Agencement d'étanchéité entre un ensemble à buse variable et un carter de turbine d'un turbocompresseur
EP2594745B1 (fr) Ensemble à buse variable d'un turbocompresseur avec bague d'étanchéité d'aube
US7338254B2 (en) Turbocharger with sliding piston assembly
EP2940253B1 (fr) Turbocompresseur à géometrie variable et régulation de jeu d'aubes directrices par le biais de pression différentielle
EP1947298B1 (fr) Ensemble de joint coulissant pour moteur de turbine à gaz
US8123470B2 (en) Turbine assembly with semi-divided nozzle and half-collar piston
EP2573363B1 (fr) Turbocompresseur à géométrie variable avec un agencement d'étanchéite d'aubes statoriques
US7883311B2 (en) Bearing assembly and method of assembling the same
EP2148043A2 (fr) Turbocompresseur à géométrie variable avec piston et insert monté dans l'alésage du carter de turbine
US8197195B2 (en) Turbocharger with stepped two-stage vane nozzle
US8979485B2 (en) Variable geometry turbine
US20120255275A1 (en) Guiding a sparkplug in a turbine engine combustion chamber
EP2028347B1 (fr) Turbocompresseur avec ensemble de piston coulissant
US8112995B2 (en) Turbocharger with variable turbine geometry
US10329948B2 (en) Stamped variable geometry turbocharger lever using retention collar
US20240344465A1 (en) Variable Geometry Turbine
EP3699400B1 (fr) Système de moteur à turbine à gaz avec joint coulissant léger à faible blocage
US20220316349A1 (en) Turbine assembly
EP3794219B1 (fr) Agencements d'aube et d'enveloppe pour une turbomachine
US8967952B2 (en) Gas turbine engine duct blocker that includes a duct blocker rotor with a plurality of roller elements
WO2024157030A1 (fr) Turbine à géométrie variable

Legal Events

Date Code Title Description
AS Assignment

Owner name: HONEYWELL INTERNATIONAL, INC., NEW JERSEY

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:BOUVLER, EMMANUEL;SAUSSE, LORRAIN;BARTHELET, PIERRE;AND OTHERS;REEL/FRAME:021300/0334;SIGNING DATES FROM 20080701 TO 20080722

AS Assignment

Owner name: UNITED STATES DEPARTMENT OF ENERGY, DISTRICT OF CO

Free format text: CONFIRMATORY LICENSE;ASSIGNOR:HONEYWELL TURBO TECHNOLOGIES;REEL/FRAME:024743/0799

Effective date: 20081202

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION