EP0253234A1 - Variable guide vane actuating device for a turbine engine - Google Patents

Variable guide vane actuating device for a turbine engine Download PDF

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Publication number
EP0253234A1
EP0253234A1 EP87109592A EP87109592A EP0253234A1 EP 0253234 A1 EP0253234 A1 EP 0253234A1 EP 87109592 A EP87109592 A EP 87109592A EP 87109592 A EP87109592 A EP 87109592A EP 0253234 A1 EP0253234 A1 EP 0253234A1
Authority
EP
European Patent Office
Prior art keywords
ring
turbine housing
adjusting device
guide vanes
adjusting
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.)
Granted
Application number
EP87109592A
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German (de)
French (fr)
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EP0253234B1 (en
Inventor
Christian Greune
Hilbert Holzhauer
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.)
MTU Aero Engines GmbH
Original Assignee
MTU Motoren und Turbinen Union Muenchen GmbH
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 MTU Motoren und Turbinen Union Muenchen GmbH filed Critical MTU Motoren und Turbinen Union Muenchen GmbH
Priority to AT87109592T priority Critical patent/ATE47617T1/en
Publication of EP0253234A1 publication Critical patent/EP0253234A1/en
Application granted granted Critical
Publication of EP0253234B1 publication Critical patent/EP0253234B1/en
Expired legal-status Critical Current

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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
    • F01D17/16—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes
    • F01D17/162—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of nozzle vanes for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line

Definitions

  • the invention relates to an adjustment device for pivotable guide vanes of turbo engines with an adjustment ring located outside the turbine housing, which is rotatably supported by bearings on a coaxial support ring and on which the pivoting lever of the guide vanes, which is flexible on the blade side perpendicular to the pivot plane, is movably arranged in four degrees of freedom.
  • Such an adjustment device is known from US-PS 29 33 234.
  • the adjustment ring is mounted on sliding members on concentrically inner carrier ring segments, which in turn are attached to the housing of the turbo engine.
  • the flexible swivel levers of the guide vanes are supported by ball joints in the adjustment ring.
  • the result of this arrangement is that the engine heat can be transferred unhindered to the adjusting device, which results in large temperature differences between the starting and operating phases of the engine with correspondingly high thermal expansions of the adjusting device.
  • sufficient elasticity or play must be provided in the adjustment device. This in turn leads to inaccuracies in the guide vane adjustments due to the large actuating forces to be transmitted, which are associated with losses in efficiency. It can e.g. B. even cause mechanical damage due to vibrations.
  • the object of the invention is to avoid these disadvantages and to ensure an exact setting of the guide vanes regardless of the temperature fluctuations caused by different operating states.
  • the object is achieved in that the carrier ring is connected in a heat-insulating manner to the turbine housing via a plurality of connecting lugs distributed over the circumference.
  • This arrangement ensures that the heat flow from the turbine housing to the carrier and adjusting ring remains relatively low regardless of the operating state of the engine and that this maintains an approximately constant temperature. Since the turbine housing is generally surrounded by a cooling air flow, the heat conduction via the connecting straps is further restricted.
  • the connecting straps are preferably flat sections of a ring band. This enables a surface / cross-sectional ratio that is favorable for reduced heat conduction to be achieved.
  • the connecting straps have a certain elasticity in the radial direction, as a result of which the different thermal expansions of the turbine housing, which becomes hot during operation, and of the adjustment and carrier ring that remain cool are compensated for.
  • the connecting straps are connected to a fastening ring fastened to the turbine housing. This enables simple and exact assembly of the adjusting device to be achieved.
  • the carrier ring, fastening ring and connecting straps are combined to form a bearing ring which is designed as an integral component, which leads to a simplification of the production.
  • the bearing ring can consist of two or more ring segments connected to one another, whereby the fastening of the adjustment device is facilitated.
  • the carrier ring is connected to the turbine housing via a plurality of sliding block guides distributed around the circumference.
  • the carrier ring is movable in the axial direction of the engine and can advantageously absorb different thermal expansions of the carrier ring and the housing.
  • the heat flow from the housing into the ring is reduced.
  • a fastening ring 2 is screwed to the turbine housing 9. This is connected to the U-shaped carrier ring 7 via flat connecting straps 8 (FIG. 2).
  • the adjusting ring 4 is provided with axial bores 10, in which the spherical ends of the pivot levers 3 are guided. On the blade side, the pivot levers 3 are firmly connected to the pivotable guide blades 1. To adjust the guide vanes l, the adjusting ring 4 is rotated in the circumferential direction by a device (not shown), as a result of which the spherical ends of the pivot levers 3 located in the bores l0 are also moved and in this way pivot the guide vanes l. The pivot levers 3 are bent elastically.
  • the connecting straps 8 and the swivel levers 3 are designed as flat tongues, as a result of which the heat flow from the hot turbine housing 9 onto the adjusting device remains low.
  • the carrier ring 7 is connected to the turbine housing 9 via sliding block guides 12.
  • the sliding block guides l2 distributed over the circumference - as can be seen in FIG. 4 - consist of a pin l3 attached on the support ring side, which is movably arranged between guide shoulders l4 of a fastening profile l5 screwed to the turbine housing 9.
  • the swivel lever 3 is mounted in a ball socket l6 of the carrier ring 4, as a result of which surface contact between the swivel lever 3 and the carrier ring 4 is advantageously achieved.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Control Of Turbines (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Supercharger (AREA)
  • Support Of The Bearing (AREA)

Abstract

An adjusting mechanism for pivotal guide blades of turbo-propulsion units in which a rotatable adjusting ring is supported in a concentric support ring. The support ring is heat-insulatingly connected with the turbine housing by way of several connecting lugs or slide block guidances distributed over the circumference and the adjusting ring is connected with the guide blades by way of bendable pivot levers. It is achieved thereby that the heat flow from the hot turbine housing to the adjusting mechanism remains small and an exact adjustment of the guide blades can be achieved in this manner.

Description

Die Erfindung betrifft eine Verstellvorrichtung für schwenk­bare Leitschaufeln von Turbotriebwerken mit einem außer­halb des Turbinengehäuses befindlichen Verstellring, der über Lager an einem koaxialen Trägerring drehbar gelagert ist und an dem schaufelseitig senkrecht zur Schwenkebene biegsame Schwenkhebel der Leitschaufeln in vier Freiheitsgraden beweglich angeordnet sind.The invention relates to an adjustment device for pivotable guide vanes of turbo engines with an adjustment ring located outside the turbine housing, which is rotatably supported by bearings on a coaxial support ring and on which the pivoting lever of the guide vanes, which is flexible on the blade side perpendicular to the pivot plane, is movably arranged in four degrees of freedom.

Eine derartige Verstellvorrichtung ist aus der US-PS 29 33 234 bekannt. Hierbei ist der Verstellring über Gleitglieder an konzentrisch innen liegenden Trägerringsegmenten gela­gert, welche wiederum am Gehäuse des Turbotriebwerkes befestigt sind. Die biegsamen Schwenkhebel der Leitschau­feln sind über Kugelgelenke im Verstellring gelagert. Diese Anordnung hat zur Folge, daß sich die Triebwerk­wärme ungehindert auf die Verstellvorrichtung übertragen kann, wodurch sich große Temperaturunterschiede zwischen der Start- und Betriebsphase des Triebwerkes mit entspre­chend hohen Wärmedehnungen der Verstellvorrichtung er­geben. Um diese aufnehmen zu können, müssen ausreichende Elastizitäten oder Spiele in der Verstellvorrichtung vorgesehen sein. Dies wiederum führt wegen den großen zu übertragenden Betätigungskräften zu Ungenauigkeiten der Leitschaufelverstellungen, welche mit Wirkungsgrad­verlusten verbunden sind. Es kann z. B. durch Vibrationen sogar zu mechanischen Schäden führen.Such an adjustment device is known from US-PS 29 33 234. Here, the adjustment ring is mounted on sliding members on concentrically inner carrier ring segments, which in turn are attached to the housing of the turbo engine. The flexible swivel levers of the guide vanes are supported by ball joints in the adjustment ring. The result of this arrangement is that the engine heat can be transferred unhindered to the adjusting device, which results in large temperature differences between the starting and operating phases of the engine with correspondingly high thermal expansions of the adjusting device. In order to be able to accommodate these, sufficient elasticity or play must be provided in the adjustment device. This in turn leads to inaccuracies in the guide vane adjustments due to the large actuating forces to be transmitted, which are associated with losses in efficiency. It can e.g. B. even cause mechanical damage due to vibrations.

Aufgabe der Erfindung ist es, diese Nachteile zu vermeiden und eine exakte Einstellung der Leitschaufeln unabhängig von den durch unterschiedliche Betriebszustände hervorge­rufenen Temperaturschwankungen zu gewährleisten.The object of the invention is to avoid these disadvantages and to ensure an exact setting of the guide vanes regardless of the temperature fluctuations caused by different operating states.

Gemäß der Erfindung wird die Aufgabe dadurch gelöst, daß der Trägerring wärmedämmend über mehrere am Umfang verteilte Verbindungslaschen mit dem Turbinengehäuse verbunden ist.According to the invention, the object is achieved in that the carrier ring is connected in a heat-insulating manner to the turbine housing via a plurality of connecting lugs distributed over the circumference.

Durch diese Anordnung wird erreicht, daß der Wärmefluß vom Turbinengehäuse auf Träger- und Verstellring unab­hängig vom Betriebszustand des Triebwerkes relativ gering bleibt und dieser eine in etwa konstante Temperatur bei­behält. Da das Turbinengehäuse im allgemeinen von einem Kühlluftstrom umgeben ist, wird die Wärmeleitung über die Verbindungslaschen weiter eingeschränkt.This arrangement ensures that the heat flow from the turbine housing to the carrier and adjusting ring remains relatively low regardless of the operating state of the engine and that this maintains an approximately constant temperature. Since the turbine housing is generally surrounded by a cooling air flow, the heat conduction via the connecting straps is further restricted.

Geringe Wärmedehnungen in triebwerksaxialer Richtung können ohne Fehler für die Schaufeleinstellung von den Laschen aufgenommen werden, während die Koaxialität von Trägerring und Triebwerk gewährleistet bleibt.Small thermal expansions in the axial direction of the engine can be absorbed by the tabs without errors for the blade adjustment, while the coaxiality of the carrier ring and the engine is guaranteed.

Vorzugsweise sind die Verbindungslaschen flache Abschnitte eines Ringbandes. Dadurch läßt sich ein für reduzierte Wärmeleitung günstiges Oberflächen-/Querschnittsverhält­nis erzielen. Außerdem weisen die Verbindungslaschen in radialer Richtung eine gewisse Elastizität auf, wo­durch die unterschiedlichen Wärmedehnungen des im Betrieb heiß werdenden Turbinengehäuses und des kühl bleibenden Verstell- und Trägerrings ausgeglichen wird.The connecting straps are preferably flat sections of a ring band. This enables a surface / cross-sectional ratio that is favorable for reduced heat conduction to be achieved. In addition, the connecting straps have a certain elasticity in the radial direction, as a result of which the different thermal expansions of the turbine housing, which becomes hot during operation, and of the adjustment and carrier ring that remain cool are compensated for.

In einer besonderen Ausführungform sind die Verbindungs­laschen mit einem am Turbinengehäuse befestigten Befesti­gungsring verbunden. Dadurch läßt sich eine einfache und exakte Montage der Verstellvorrichtung erzielen.In a special embodiment, the connecting straps are connected to a fastening ring fastened to the turbine housing. This enables simple and exact assembly of the adjusting device to be achieved.

In einer weiteren Ausführungsform sind Trägerring, Be­festigungsring und Verbindungslaschen zu einem Lagerring zusammengefaßt, der als ein integrales Bauteil ausgeführt ist, welches zu einer Vereinfachung der Herstellung führt.In a further embodiment, the carrier ring, fastening ring and connecting straps are combined to form a bearing ring which is designed as an integral component, which leads to a simplification of the production.

Der Lagerring kann in einer weiteren Ausführungsform aus zwei oder mehreren miteinander verbunden Ringsegmen­ten bestehen, wodurch die Befestigung der Verstellvor­richtung erleichtert wird.In a further embodiment, the bearing ring can consist of two or more ring segments connected to one another, whereby the fastening of the adjustment device is facilitated.

In einer alternativen Ausgestaltung der Erfindung ist der Trägerring über mehrere am Umfang verteilte Gleitstein­führungen mit dem Turbinengehäuse verbunden. Dadurch ist der Trägerring in triebwerksaxialer Richtung beweglich und kann so vorteilhafterweise unterschiedliche Wärme­dehnungen von Trägerring und Gehäuse aufnehmen. Außerdem ist der Wärmefluß vom Gehäuse in den Ring reduziert.In an alternative embodiment of the invention, the carrier ring is connected to the turbine housing via a plurality of sliding block guides distributed around the circumference. As a result, the carrier ring is movable in the axial direction of the engine and can advantageously absorb different thermal expansions of the carrier ring and the housing. In addition, the heat flow from the housing into the ring is reduced.

Anhand der Zeichnungen wird ein Ausführungsbeispiel wei­ter beschrieben. Dabei zeigt:

  • Fig. l einen Längsschnitt durch einen Leitschaufelkranz,
  • Fig. 2 ein Schrägbild des Träger- und Befestigungsringes,
  • Fig. 3 ein Längsschnitt durch einen alternativen Leit­schaufelkranz,
  • Fig. 4 eine Draufsicht auf die Gleitsteinführungen.
An exemplary embodiment is further described with the aid of the drawings. It shows:
  • 1 shows a longitudinal section through a guide vane ring,
  • 2 is an oblique view of the carrier and fastening ring,
  • 3 shows a longitudinal section through an alternative vane ring,
  • Fig. 4 is a plan view of the sliding block guides.

Nach Fig. l ist ein Befestigungsring 2 am Turbinengehäuse 9 verschraubt. Uber flache Verbindungslaschen 8 ist dieser mit dem U-förmigen Trägerring 7 verbunden (Fig. 2). Uber gleichmäßig über dem Umfang verteilte Führungsrollen 5, die durch Bolzen 6 im Trägerring 7 montiert sind, ist der Verstellring 4 in Umfangsrichtung drehbar gelagert, wobei dessen genaue Führung durch die Schultern ll des Verstellringes 4 gewährleistet wird.1, a fastening ring 2 is screwed to the turbine housing 9. This is connected to the U-shaped carrier ring 7 via flat connecting straps 8 (FIG. 2). Guide rollers 5, which are evenly distributed over the circumference and are mounted in the carrier ring 7 by bolts 6, have the adjusting ring 4 rotatably mounted in the circumferential direction, its precise guidance being ensured by the shoulders 11 of the adjusting ring 4.

Der Verstellring 4 ist mit axialen Bohrungen l0 versehen, in denen die kugelförmigen Enden der Schwenkhebel 3 ge­führt werden. Schaufelseitig sind die Schwenkhebel 3 fest mit den schwenkbaren Leitschaufeln l verbunden. Zur Verstellung der Leitschaufeln l wird der Verstell­ring 4 durch eine nicht dargestellte Vorrichtung in Um­fangsrichtung verdreht, wodurch die in den Bohrungen l0 befindlichen kugelförmigen Enden der Schwenkhebel 3 mit­bewegt werden und auf diese Weise die Leitschaufeln l schwenken. Dabei werden die Schwenkhebel 3 elastisch verbogen.The adjusting ring 4 is provided with axial bores 10, in which the spherical ends of the pivot levers 3 are guided. On the blade side, the pivot levers 3 are firmly connected to the pivotable guide blades 1. To adjust the guide vanes l, the adjusting ring 4 is rotated in the circumferential direction by a device (not shown), as a result of which the spherical ends of the pivot levers 3 located in the bores l0 are also moved and in this way pivot the guide vanes l. The pivot levers 3 are bent elastically.

Die Verbindungslaschen 8 und die Schwenkhebel 3 sind als flache Zungen ausgeführt, wodurch der Wärmefluß vom heißen Turbinengehäuse 9 auf die Verstellvorrichtung gering bleibt.The connecting straps 8 and the swivel levers 3 are designed as flat tongues, as a result of which the heat flow from the hot turbine housing 9 onto the adjusting device remains low.

Bei der in Fig. 3 gezeigten Ausführung ist der Trägerring 7 über Gleitsteinführungen l2 mit dem Turbinengehäuse 9 verbunden.In the embodiment shown in FIG. 3, the carrier ring 7 is connected to the turbine housing 9 via sliding block guides 12.

Die über den Umfang verteilten Gleitsteinführungen l2 bestehen - wie in Fig. 4 zu sehen - aus einem trägerring­seitig angebrachten Stift l3, welcher zwischen Führungs­schultern l4 eines am Turbinengehäuse 9 angeschraubten Befestigungsprofils l5 beweglich angeordnet ist. Der Schwenkhebel 3 ist in der gezeigten Ausführungsform in einer Kugelpfanne l6 des Trägerringes 4 gelagert, wodurch vorteilhafterweise eine Flächenberührung zwischen Schwenk­hebel 3 und Trägerring 4 erreicht wird.The sliding block guides l2 distributed over the circumference - as can be seen in FIG. 4 - consist of a pin l3 attached on the support ring side, which is movably arranged between guide shoulders l4 of a fastening profile l5 screwed to the turbine housing 9. In the embodiment shown, the swivel lever 3 is mounted in a ball socket l6 of the carrier ring 4, as a result of which surface contact between the swivel lever 3 and the carrier ring 4 is advantageously achieved.

Claims (7)

1. Verstellvorrichtung für schwenkbare Leitschaufeln von Turbotriebwerken mit einem außerhalb des Turbinen­gehäuses befindlichen Verstellring, der über Lager an einem koaxialen Trägerring drehbar gelagert ist und an dem schaufelseitig senkrecht zur Schwenkebene biegsame Schwenkhebel der Leitschaufeln in vier Frei­heitsgraden beweglich angeordnet sind, dadurch gekenn­zeichnet, daß der Trägerring (7) wärmedämmend über mehrere am Umfang verteilte Verbindungslaschen (8) mit dem Turbinengehäuse (9) verbunden ist.1. Adjustment device for pivotable guide vanes of turbo engines with an adjustment ring located outside the turbine housing, which is rotatably supported by bearings on a coaxial support ring and on the blade side of the guide vanes, which are flexible in four degrees of freedom and are movably arranged, characterized in that the support ring (7) is connected to the turbine housing (9) in an insulating manner via a plurality of connecting lugs (8) distributed around the circumference. 2. Verstellvorrichtung nach Anspruch l, dadurch gekenn­zeichnet, daß die Verbindungslaschen (8) flache Ab­schnitte eines Ringbandes sind.2. Adjusting device according to claim l, characterized in that the connecting tabs (8) are flat sections of a ring band. 3. Verstellvorrichtung nach Anspruch l und 2, dadurch gekennzeichnet, daß die Verbindungslaschen (8) mit einem am Turbinengehäuse (9) befestigten Befestigungs­ring (2) verbunden sind.3. Adjusting device according to claim l and 2, characterized in that the connecting tabs (8) with a on the turbine housing (9) attached fastening ring (2) are connected. 4. Verstellvorrichtung nach den Ansprüchen l - 3, da­durch gekennzeichnet, daß der Trägerring (7), der Befe­stigungsring (2) und die Verbindungslaschen (8) als ein integrales Bauteil ausgeführt sind.4. Adjusting device according to claims l - 3, characterized in that the carrier ring (7), the fastening ring (2) and the connecting tabs (8) are designed as an integral component. 5. Verstellvorrichtung nach Anspruch 4, dadurch gekenn­zeichnet, daß das Bauteil aus zwei oder mehreren miteinander verbundenen Ringsegmenten besteht.5. Adjusting device according to claim 4, characterized in that the component consists of two or more interconnected ring segments. 6. Verstellvorrichtung für schwenkbare Leitschaufeln von Turbotriebwerken mit einem außerhalb des Turbinen­gehäuses befindlichen Verstellring, der über Lager an einem koaxialen Trägerring drehbar gelagert ist und an dem schaufelseitig senkrecht zur Schwenkebene biegsame Schwenkhebel der Leitschaufeln beweglich angebracht sind, dadurch gekennzeichnet, daß der Trägerring (7) über mehrere am Umfang verteilte Gleit­steinführungen (l2) mit dem Turbinengehäuse (9) ver­bunden ist.6. Adjusting device for pivotable guide vanes of turbo engines with an adjusting ring located outside the turbine housing, which is rotatably supported by bearings on a coaxial carrier ring and on which the pivoting lever of the guide vanes, which is flexible and perpendicular to the pivot plane, is movably attached, characterized in that the carrier ring (7) is connected to the turbine housing (9) via a plurality of sliding block guides (l2) distributed around the circumference. 7. Verstellvorrichtung nach Anspruch 6, dadurch gekennzeich­net, daß die Gleitsteinführungen (l2, l3, l4) jeweils radial ausgerichtet sind.7. Adjusting device according to claim 6, characterized in that the sliding block guides (l2, l3, l4) are each aligned radially.
EP87109592A 1986-07-09 1987-07-03 Variable guide vane actuating device for a turbine engine Expired EP0253234B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
AT87109592T ATE47617T1 (en) 1986-07-09 1987-07-03 INTRODUCTION DEVICE FOR TURBO ENGINES GUIDE BLADES.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE3623001 1986-07-09
DE3623001A DE3623001C1 (en) 1986-07-09 1986-07-09 Adjustment device for swiveling guide vanes of turbo engines

Publications (2)

Publication Number Publication Date
EP0253234A1 true EP0253234A1 (en) 1988-01-20
EP0253234B1 EP0253234B1 (en) 1989-10-25

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ID=6304703

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Application Number Title Priority Date Filing Date
EP87109592A Expired EP0253234B1 (en) 1986-07-09 1987-07-03 Variable guide vane actuating device for a turbine engine

Country Status (5)

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US (1) US4810165A (en)
EP (1) EP0253234B1 (en)
JP (1) JPH0735734B2 (en)
AT (1) ATE47617T1 (en)
DE (2) DE3623001C1 (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2206381B (en) * 1987-06-30 1991-10-09 Rolls Royce Plc A variable stator vane arrangement for a compressor
EP0532907A1 (en) * 1991-09-19 1993-03-24 Asea Brown Boveri Ag Axial turbine
US5342169A (en) * 1992-04-25 1994-08-30 Asea Brown Boveri Ltd. Axial flow turbine

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5049033A (en) * 1990-02-20 1991-09-17 General Electric Company Blade tip clearance control apparatus using cam-actuated shroud segment positioning mechanism
DE4102188C2 (en) * 1991-01-25 1994-09-22 Mtu Muenchen Gmbh Guide vane adjustment device of a turbine of a gas turbine engine
GB2301867A (en) * 1995-06-05 1996-12-18 Rolls Royce Plc Supporting unison rings in pivotable vane actuating mechanisms
US6174129B1 (en) 1999-01-07 2001-01-16 Siemens Westinghouse Power Corporation Turbine vane clocking mechanism and method of assembling a turbine having such a mechanism
DE10013335A1 (en) * 2000-03-17 2001-09-20 Abb Turbo Systems Ag Baden Conducting apparatus is for position alteration of conducting blades in turbocharger exhaust gas turbine has blades arranged axially symmetrically to the turbine axis in an exhaust gas flow channel and can be pivoted by a pivot device
SE519353C2 (en) * 2000-11-15 2003-02-18 Volvo Aero Corp Stator for a gas turbine
ATE550521T1 (en) * 2003-05-06 2012-04-15 Honeywell Int Inc SYSTEM THAT INCLUDES A WARRANTY CALIBRATION DEVICE, ESPECIALLY FOR A TURBOCHARGER WITH ADJUSTABLE GUIDE VANES
DE10351202A1 (en) * 2003-11-03 2005-06-02 Mtu Aero Engines Gmbh Device for adjusting vanes
FR2902454A1 (en) * 2006-06-16 2007-12-21 Snecma Sa TURBOMACHINE STATOR COMPRISING A FLOOR OF ADJUSTERS ADJUSTED BY A ROTATING CROWN WITH AUTOMATIC CENTERING
US9039355B2 (en) 2012-05-31 2015-05-26 United Technologies Corporation Actuator mounted to torque box
CN104533540B (en) * 2014-11-14 2016-04-20 沈阳黎明航空发动机(集团)有限责任公司 The device of rotating ring and compressor casing concentricity is made in a kind of guarantee
FR3063779B1 (en) * 2017-03-07 2022-11-04 Safran Aircraft Engines STATOR BLADE STAGE TIMING CONTROL RING

Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2637984A (en) * 1950-07-26 1953-05-12 Gen Electric Turbine
US2778564A (en) * 1953-12-01 1957-01-22 Havilland Engine Co Ltd Stator blade ring assemblies for axial flow compressors and the like
US2936108A (en) * 1957-04-29 1960-05-10 Gen Electric Compressor
FR2030895A5 (en) * 1969-05-23 1970-11-13 Motoren Turbinen Union
US3861822A (en) * 1974-02-27 1975-01-21 Gen Electric Duct with vanes having selectively variable pitch
US4035101A (en) * 1976-03-24 1977-07-12 Westinghouse Electric Corporation Gas turbine nozzle vane adjusting mechanism
GB1499531A (en) * 1976-05-24 1978-02-01 Secr Defence Apparatus for varying the incidence of turbomachinery stator blades
GB1533940A (en) * 1976-12-23 1978-11-29 Caterpillar Tractor Co Variable geometry turbine or compressor nozzle
US4130375A (en) * 1975-10-14 1978-12-19 Westinghouse Canada Ltd. Vane rotator assembly for a gas turbine engine
US4400135A (en) * 1981-04-06 1983-08-23 General Motors Corporation Vane actuation system

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
BE514728A (en) * 1951-10-10
GB755527A (en) * 1953-10-15 1956-08-22 Power Jets Res & Dev Ltd Mounting of swivelling guide vane elements in axial flow elastic fluid turbines
US2933234A (en) * 1954-12-28 1960-04-19 Gen Electric Compressor stator assembly
US2932440A (en) * 1955-05-20 1960-04-12 Gen Electric Compressor blade adjustment means
DE1108988B (en) * 1957-04-04 1961-06-15 Napier & Son Ltd Adjustable guide vane ring for turbines, especially gas turbines
US3303992A (en) * 1965-03-03 1967-02-14 Gen Motors Corp Variable vane stator ring
DE2253030A1 (en) * 1972-10-28 1974-05-09 Sljusarew DEVICE FOR BLADE ADJUSTMENT OF THE CONTROL UNIT OF A FLOW MACHINE
US3990809A (en) * 1975-07-24 1976-11-09 United Technologies Corporation High ratio actuation linkage
GB2042646B (en) * 1979-02-20 1982-09-22 Rolls Royce Rotor blade tip clearance control for gas turbine engine
US4363600A (en) * 1981-04-06 1982-12-14 General Motors Corporation Variable vane mounting
DE3514354A1 (en) * 1985-04-20 1986-10-23 MTU Motoren- und Turbinen-Union München GmbH, 8000 München COOLED GAS TURBINE WITH LOAD-ADJUSTABLE COOLING AIR AMOUNT

Patent Citations (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2637984A (en) * 1950-07-26 1953-05-12 Gen Electric Turbine
US2778564A (en) * 1953-12-01 1957-01-22 Havilland Engine Co Ltd Stator blade ring assemblies for axial flow compressors and the like
US2936108A (en) * 1957-04-29 1960-05-10 Gen Electric Compressor
FR2030895A5 (en) * 1969-05-23 1970-11-13 Motoren Turbinen Union
US3861822A (en) * 1974-02-27 1975-01-21 Gen Electric Duct with vanes having selectively variable pitch
US4130375A (en) * 1975-10-14 1978-12-19 Westinghouse Canada Ltd. Vane rotator assembly for a gas turbine engine
US4035101A (en) * 1976-03-24 1977-07-12 Westinghouse Electric Corporation Gas turbine nozzle vane adjusting mechanism
GB1499531A (en) * 1976-05-24 1978-02-01 Secr Defence Apparatus for varying the incidence of turbomachinery stator blades
GB1533940A (en) * 1976-12-23 1978-11-29 Caterpillar Tractor Co Variable geometry turbine or compressor nozzle
US4400135A (en) * 1981-04-06 1983-08-23 General Motors Corporation Vane actuation system

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2206381B (en) * 1987-06-30 1991-10-09 Rolls Royce Plc A variable stator vane arrangement for a compressor
EP0532907A1 (en) * 1991-09-19 1993-03-24 Asea Brown Boveri Ag Axial turbine
US5342169A (en) * 1992-04-25 1994-08-30 Asea Brown Boveri Ltd. Axial flow turbine

Also Published As

Publication number Publication date
JPS6325327A (en) 1988-02-02
JPH0735734B2 (en) 1995-04-19
ATE47617T1 (en) 1989-11-15
US4810165A (en) 1989-03-07
EP0253234B1 (en) 1989-10-25
DE3760882D1 (en) 1989-11-30
DE3623001C1 (en) 1987-07-09

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