EP0253234B1 - 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
EP0253234B1
EP0253234B1 EP87109592A EP87109592A EP0253234B1 EP 0253234 B1 EP0253234 B1 EP 0253234B1 EP 87109592 A EP87109592 A EP 87109592A EP 87109592 A EP87109592 A EP 87109592A EP 0253234 B1 EP0253234 B1 EP 0253234B1
Authority
EP
European Patent Office
Prior art keywords
ring
turbine housing
adjustment device
connecting brackets
adjustment
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.)
Expired
Application number
EP87109592A
Other languages
German (de)
French (fr)
Other versions
EP0253234A1 (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 adjusting 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 carrier ring and on which the pivoting lever of the guide vanes is arranged so as to be movable on the blade side perpendicular to the pivoting plane, and the carrier ring is heat-insulating over several Scope distributed connecting tabs is connected to the turbine housing.
  • the object of the invention is to avoid these disadvantages and to ensure an exact adjustment of the guide vanes regardless of the temperature fluctuations caused by different operating states, whereby a structurally simple device should be created which at the same time has high rigidity and works equally reliably under all temperature conditions.
  • the object is achieved in that the connecting straps are flat sections of a ring band.
  • 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. 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.
  • the connecting straps are flat sections of a ring band, a surface / cross-sectional ratio which is favorable for reduced heat conduction can 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 lugs 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 adjusting device is facilitated.
  • 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 rotatably supported in the circumferential direction by means of guide rollers 5 distributed uniformly over the circumference, which are mounted by bolts 6 in the carrier ring 7, its precise guidance being ensured by the shoulders 11 of the adjusting ring 4.
  • 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 vanes 1.
  • 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 10 are also moved and in this way pivot the guide vanes 1.
  • 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.

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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 beweglich angeordnet sind, und der Trägerring wärmedämmend über mehrere am Umfang verteilte Verbindungslaschen mit dem Turbinengehäuse verbunden ist.The invention relates to an adjusting 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 carrier ring and on which the pivoting lever of the guide vanes is arranged so as to be movable on the blade side perpendicular to the pivoting plane, and the carrier ring is heat-insulating over several Scope distributed connecting tabs is connected to the turbine housing.

Eine derartige Verstellvorrichtung aus der US-PS 4 035 101 bekanntgeworden, bei der ein Verstellring koaxial neben einem stationären Ring angeordnet ist, wobei der stationäre Ring über eine Vielzahl von Verbindungslaschen beweglich am Gehäuse befestigt ist. Der Verstellring ist mittels Rollen, die an den Laschen angebracht sind, in Umfangsrichtung verdrehbar gelagert. Diese Anordnung benötigt eine Vielzahl von Scharnieren und Lagern, welche im Betrieb hohen Temperaturschwankungen ausgesetzt sind. Dadurch ist bei niedrigen Temperaturen ein Lagerspiel, bzw. bei hohen Temperaturen ein Klemmen bzw. ein Verspannen einzelner Glieder möglich.Such an adjustment device has become known from US Pat. No. 4,035,101, in which an adjustment ring is arranged coaxially next to a stationary ring, the stationary ring being movably attached to the housing via a plurality of connecting lugs. The adjusting ring is rotatably supported in the circumferential direction by means of rollers which are attached to the tabs. This arrangement requires a large number of hinges and bearings which are exposed to high temperature fluctuations during operation. In this way, a bearing clearance is possible at low temperatures, or individual elements can be clamped or braced at high temperatures.

Eine weitere Verstellvorrichtung ist aus der US-PS 2 933 234 bekannt. Hierbei ist ein 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 Triebwerkswärme 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.Another adjustment device is known from US Pat. No. 2,933,234. Here, an 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 blade adjustments, which are associated with losses in efficiency, because of the large actuating forces to be transmitted. For example, vibrations can even lead to mechanical damage.

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, wobei eine konstruktiv möglichst einfache Vorrichtung geschaffen werden soll, die gleichzeitig hohe Steifigkeit aufweist und unter allen Temperaturbedingungen gleich zuverlässig funktioniert.The object of the invention is to avoid these disadvantages and to ensure an exact adjustment of the guide vanes regardless of the temperature fluctuations caused by different operating states, whereby a structurally simple device should be created which at the same time has high rigidity and works equally reliably under all temperature conditions.

Erfindungsgemäß wird die Aufgabe dadurch gelöst, daß die Verbindungslaschen flache Abschnitte eines Ringbandes sind.According to the invention the object is achieved in that the connecting straps are flat sections of a ring band.

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. 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.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. 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.

Dadurch daß die Verbindungslaschen flache Abschnitte eines Ringbandes sind, 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.Because the connecting straps are flat sections of a ring band, a surface / cross-sectional ratio which is favorable for reduced heat conduction can 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 Ausführungsform 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 lugs 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 verbundenen 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 adjusting device is facilitated.

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

  • Fig. 1 einen Längsschnitt durch einen Leitschaufelkranz,
  • Fig. 2 ein Schrägbild des Träger- und Befestigungsringes.
An exemplary embodiment is further described with the aid of the drawings. It shows:
  • 1 shows a longitudinal section through a guide vane ring,
  • Fig. 2 is an oblique view of the carrier and mounting ring.

Nach Fig. 1 ist ein Befestigungsring 2 am Turbinengehäuse 9 verschraubt. Über flache Verbindungslaschen 8 ist dieser mit dem U-förmigen Trägerring 7 verbunden (Fig. 2). Über 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 11 des Verstellringes 4 gewährleistet wird. Der Verstellring 4 ist mit axialen Bohrungen 10 versehen, in denen die kugelförmigen Enden der Schwenkhebel 3 geführt werden. Schaufelseitig sind die Schwenkhebel 3 fest mit den schwenkbaren Leitschaufeln 1 verbunden.- Zur Verstellung der Leitschaufeln 1 wird der Verstellring 4 durch eine nicht dargestellte Vorrichtung in Umfangsrichtung verdreht, wodurch die in den Bohrungen 10 befindlichen kugelförmigen Enden der Schwenkhebel 3 mitbewegt werden und auf diese Weise die Leitschaufeln 1 schwenken. Dabei werden die Schwenkhebel 3 elastisch verbogen.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). The adjusting ring 4 is rotatably supported in the circumferential direction by means of guide rollers 5 distributed uniformly over the circumference, which are mounted by bolts 6 in the carrier ring 7, its precise guidance being ensured by the shoulders 11 of the adjusting ring 4. 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 vanes 1. To adjust the guide blades 1, 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 10 are also moved and in this way pivot the guide vanes 1. 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.

Claims (4)

1. Adjustment device for pivotable guide vanes (1) of turbo engines having an adjustment ring (4) located outside the turbine housing (9) and rotatably mounted by means of bearings (5) in a coaxial carrier ring (7), and on the vane side of which pivoting levers (3) of the guide vanes (1) are movably arranged, the levers being flexible perpendicularly to the pivotal plane, and the carrier ring (7) is connected to the turbine housing (9) in thermally insulating manner by means of several connecting brackets (8) distributed over the circumference, characterised in that the connecting brackets (8) are flat portions of an annular band.
2. Adjustment device according to claim 1, characterised in that the connecting brackets (8) are connected to a securing ring (2) secured to the turbine housing (9).
3. Adjustment device according to claims 1 or 2, characterised in that the carrier ring (7), the securing ring (2) and the connecting brackets (8) are constructed as an integral component.
4. Adjustment device according to claim 3, characterised in that the component comprises two or more annular segments joined together.
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 EP0253234A1 (en) 1988-01-20
EP0253234B1 true EP0253234B1 (en) 1989-10-25

Family

ID=6304703

Family Applications (1)

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)

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

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GB2301867A (en) * 1995-06-05 1996-12-18 Rolls Royce Plc Supporting unison rings in pivotable vane actuating mechanisms
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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
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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
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Also Published As

Publication number Publication date
JPS6325327A (en) 1988-02-02
DE3760882D1 (en) 1989-11-30
EP0253234A1 (en) 1988-01-20
DE3623001C1 (en) 1987-07-09
US4810165A (en) 1989-03-07
ATE47617T1 (en) 1989-11-15
JPH0735734B2 (en) 1995-04-19

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