EP2146056A2 - Gasturbine engine with variable stator vanes - Google Patents
Gasturbine engine with variable stator vanes Download PDFInfo
- Publication number
- EP2146056A2 EP2146056A2 EP09164130A EP09164130A EP2146056A2 EP 2146056 A2 EP2146056 A2 EP 2146056A2 EP 09164130 A EP09164130 A EP 09164130A EP 09164130 A EP09164130 A EP 09164130A EP 2146056 A2 EP2146056 A2 EP 2146056A2
- Authority
- EP
- European Patent Office
- Prior art keywords
- gas turbine
- turbine engine
- engine according
- pin
- temperature
- 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.)
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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
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- 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
- F01D9/00—Stators
- F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
- F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
- F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
-
- 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
- F05D2230/00—Manufacture
- F05D2230/60—Assembly methods
- F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
- F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
-
- 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
- F05D2270/00—Control
- F05D2270/01—Purpose of the control system
- F05D2270/07—Purpose of the control system to improve fuel economy
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/502—Thermal properties
- F05D2300/5021—Expansivity
- F05D2300/50212—Expansivity dissimilar
-
- 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
- F05D2300/00—Materials; Properties thereof
- F05D2300/50—Intrinsic material properties or characteristics
- F05D2300/505—Shape memory behaviour
Definitions
- the invention relates to a gas turbine engine with the blades associated, by means of adjusting elements about its longitudinal axis angle-adjustable guide vanes (1) for controlling the blades (6) supplied air flow.
- the blading of a gas turbine engine includes vanes and blades.
- the vanes or stator vanes fixedly mounted in the housing of the compressor or turbine direct the air or hot gas at a predetermined angle onto the shaft-connected blades or rotor blades, at which the flow energy supplied by the vanes is converted into a circumferential force.
- the known devices for controlling angle-adjustable stator blades provided at the air inlet of the compressors of gas turbine engines usually have a control member in the form of a ring, which is arranged around the housing of the turbomachine, and which is arranged on a plurality of hinged thereto control levers with external, in the pivot axis of the vanes provided pivot is firmly connected.
- the synchronized change in the angular position of the vanes is achieved by rotating the ring about the axis of the turbomachine.
- Such a mechanical one operated adjusting mechanism for angular adjustment of the vanes is, for example, in the US 3325087 described.
- the actuated by mechanical means actuators for the vanes are arranged for reasons of space and because of there still low, the function of the actuators not obstructing temperatures in the front part of the compressor.
- the mechanical adjusting mechanisms In the downstream spatially limited areas of the compressor and the - also exposed to very high temperatures - turbine is completely dispensed with the angle-adjustable design of the vanes from the outset for the reasons mentioned above, especially since the mechanical adjusting mechanisms also have a high weight and are expensive.
- the engine is to be maintained at a certain low speed, for example in the landing phase, it may cause stalling of the blades and so-called pumping of the engine, even with front-mounted angle adjustable vanes, so that the efficiency of the engine and its stable function is not guaranteed.
- the air flow in the rear of the compressor can be reduced, resulting in a stall and ultimately a power loss of the engine.
- the invention is therefore based on the object to provide a equipped with angle-adjustable vanes gas turbine engine, which ensures efficient operation and stable operation at different flight conditions.
- the basic idea of the invention consists in the adjustable design of the guide vanes also in the downstream, narrow and high temperatures exposed areas of the compressor and the turbine, so that even in different flight phases such as takeoff, landing or cruise a stable function and efficient operation of the Engine with low fuel consumption and sufficient generator power is guaranteed.
- the respectively required change in the angle of attack ⁇ of the guide vanes takes place as a function of the temperature prevailing in the respective stage of the compressor or the turbine with temperature-dependent expanding, that is stretching, enlarging or deforming control elements, which consist of materials with temperature-dependent expansion or deformation behavior.
- control elements can be arranged in the narrowest space in the rear stages of the compressors and turbines and even very high temperatures are not precluding their functionality.
- the adjusting elements may be connected to the upstream or downstream side of the guide vane or be operatively connected to both sides, but in opposite directions.
- the guide vanes are each connected to a holding plate whose downstream and upstream end portions are each pivotally mounted in a groove of the inner housing and rotatable about a pivot point.
- the actuator may be a bimetallic pin which is either axially aligned and fixed with its End is held on the inner housing or a fixed to this component, or which is aligned radially and is fixed with its fixed end to the outer housing or a fixed thereto component, while the free, moving under heat end on the pivotable side of the vane or the holding plate attacks.
- the outer housing provided with radially aligned pins can serve as an actuator due to a temperature and / or material-related different expansion behavior relative to the inner housing.
- a formed at the free end of the adjusting pin, transversely to the axial direction obliquely extending end portion engages in an equally oblique recess of the vane, so that the angle of attack ⁇ of the vane changes at a conditional change due to heating between the inner and outer housing.
- the actuating element can also be a radially outwardly guided on the outer housing with an expansion clearance expansion collar with transverse to the axial direction at its inner periphery obliquely extending recesses, in each of which an outgoing from the vane oblique actuating pin engages.
- the actuating element is a circumferentially extending, connected to the respective vane and the inner housing expansion pin from a variable in temperature change in length material.
- This expansion pin can also be integral with the vane, for example on an end face the holding plate of the vane, be formed, while the free end is in operative connection with the inner housing.
- Fig. 1 shows a vane 1, which is held by means of a holding plate 2 connected thereto in recesses 3 of the inner housing 4 of a compressor or a turbine of a gas turbine engine.
- the guide vane 1 or the stator vane or stator formed from a plurality of vanes is located between upstream and downstream arranged on a rotor disk 5 mounted blades 6, wherein the stationary vanes 1, the air or hot gas flow in one of the operating condition of the engine or the respective flight phase, namely start, increase, cruise, landing, adjusted - optimal - angle and thus a corresponding angular position of the guide vanes 1 to the blades 6 should lead to a stable and efficient Operation of the engine, that is to ensure with each flight phase stable air flow and low fuel consumption and simultaneous generation of the required electrical energy.
- Fig. 1 and the in Fig. 2 shown plan view of an employed at an angle ⁇ holding plate 2 and the guide vane 1 embody the basic idea of the present invention, according to which in each case in the recesses 3 of the inner housing 4 movably mounted opposite end portions 7.1, 7.2 of the holding plate 2 in each case an actuating element 8 attacks, due to a by the prevailing in the respective position in the compressor or the turbine temperature changes its shape or length and transmits this change in shape on one of the two end sections 7.1 or 7.2 - or in the opposite direction - to both end sections 7.1 and 7.2, so that the guide vanes. 1 be automatically adjusted about its longitudinal axis depending on the temperature prevailing in each case in the compressor or the turbine in the respective stage.
- Fig. 2 is indicated by the arrows A, in which direction the adjusting elements 8 change their position and the angular position of the holding plate 2 and the guide vane 1 to ensure optimum flow downstream of the downstream blades 6 and thus a stable and efficient engine operation.
- the holding plate 2 is held at the downstream first end portion 7.1 in the recess 4 by means of an engaging in a rear groove 9 in the flow direction 9.1 fixing pin hinged.
- the above-mentioned adjusting element 8 is designed here as an axially arranged bimetallic pin 11, which is firmly anchored on the side of the rear end portion 7.1 in the flow direction on the inner housing 4 and the opposite free end in a formed at the upstream front end portion 7.2 front groove 9.2 intervenes.
- the bimetallic pin 11 bends according to its temperature behavior and changes the angle of attack ⁇ of the guide blade 1 in accordance with the respective temperature change.
- Fig. 5 shows yet another embodiment of the adjustment of the guide vanes 1 by means of a designed as a bimetal 11 actuator 8.
- the space required for the adjusting element 8, here the bimetallic rod 11, is very small, so that the adjusting element can also be arranged in the areas of the compressor or turbine which are very narrow and have smaller components, especially since their function is not due to the high temperatures prevailing there is impaired and the control elements also have a low weight.
- the temperature-dependent effective actuator 8 is an integrally connected to the outer housing 12, radially inwardly directed adjusting pin 13 with an oblique end portion 14 which engages in an oblique recess 22 of the front end portion 7.2 of the support plate 2.
- the holding plate 2 is held articulated as in the previously described embodiments by means of an engaging in the rear groove 9.1 fixing pin 10.
- the oblique end portion 14 of the adjusting pin 13 is moved in the radial direction. In this case, the holding plate 2 is moved along the slope and thus the angle of attack of the guide vane 1 is temperature-dependent.
- the adjusting element is an expansion adjusting ring 15 which increases in temperature increase and which is formed on the outer circumference with peripheral grooves 16, into which guide pieces 17 provided on the inner circumference of the outer housing 12 engage.
- the downstream end portion 7.1 of the holding plate 2 is in turn articulated via a fixing pin 10 on the inner housing 4.
- the expansion ring 15 increases or decreases with a change in temperature and the inclined adjusting groove 18 changes its radial position relative to the inner housing 4, the oblique positioning groove 18 acts on the guided in this setting pin 19, so that the guide vane 1 to one or the other side a vertical axis is angularly adjusted.
- FIGS. 10 to 12 A further embodiment for the angular adjustment of the guide vanes 1 with a temperature-dependent actuating element is in the FIGS. 10 to 12 shown.
- the guide vane 1 is again with the aid of the fixing pin 10 held articulated.
- an actuating element forming, under heat a certain length engaging Dehnungsw 20 hinged, which is connected at the opposite end to the inner housing 4 and changes its temperature when changing its length and thus causes an angular adjustment of the guide vane 1.
- the angle adjustment according to the variant described above can also be carried out with an integrally formed on the holding plate 2 expansion pin 21.
- the invention is not limited to the previously described embodiments.
- a gas turbine engine in any areas of the compressor and / or the turbine which are exposed in particular to very narrow and high temperatures is equipped with adjusting elements for variably adjusting the angle of attack of the guide vanes
- Adjusting elements respectively used materials cause an angular adjustment of the vanes
- different materials with different thermal expansion behavior can be used for the adjusting elements, which can also be effective in the opposite direction at the rear end section 7.1 or at both end sections.
- the actuators are effective in response to the prevailing temperatures according to the respective operating conditions and only because of their thermal expansion behavior, they require little space and can also be placed in narrow and high temperature exposed areas of the compressor and the turbine, thus providing their according to the operating conditions stable operation and economical operation of the engine.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Control Of Turbines (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
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Abstract
Description
Die Erfindung betrifft ein Gasturbinentriebwerk mit den Laufschaufeln zugeordneten, mittels Stellelementen um ihre Längsachse winkelverstellbaren Leitschaufeln (1) zur Regelung des den Laufschaufeln (6) zugeführten Luftstroms.The invention relates to a gas turbine engine with the blades associated, by means of adjusting elements about its longitudinal axis angle-adjustable guide vanes (1) for controlling the blades (6) supplied air flow.
Die Beschaufelung eines Gasturbinentriebwerks umfasst Leit- und Laufschaufeln. Die fest im Gehäuse des Verdichters bzw. der Turbine angebrachten Leitschaufeln oder Statorschaufeln leiten die Luft oder das Heißgas in einem vorgegebenen Winkel auf die mit einer Welle verbundenen Laufschaufeln oder Rotorschaufeln, an denen die von den Leitschaufeln zugeführte Strömungsenergie in eine Umfangskraft umgewandelt wird. Um die Luft den Laufschaufeln des Kompressors tatsächlich in einem an die jeweiligen Betriebsverhältnisse angepassten optimalen Winkel zuzuführen und dadurch die Leistung der Turbomaschine zu verbessern und den Brennstoffverbrauch zu senken, ist es bekannt, die Leitschaufeln von Turbomaschinen am Lufteintritt von Kompressoren winkelverstellbar anzuordnen.The blading of a gas turbine engine includes vanes and blades. The vanes or stator vanes fixedly mounted in the housing of the compressor or turbine direct the air or hot gas at a predetermined angle onto the shaft-connected blades or rotor blades, at which the flow energy supplied by the vanes is converted into a circumferential force. In order to supply the air to the blades of the compressor actually in an adapted to the respective operating conditions optimum angle and thereby to improve the performance of the turbomachine and to reduce fuel consumption, it is known to arrange the guide vanes of turbomachinery on the air inlet of compressors angle-adjustable.
Die bekannten Vorrichtungen zur Steuerung von am Lufteintritt der Kompressoren von Gasturbinentriebwerken vorgesehenen winkelverstellbaren Statorschaufeln weisen üblicherweise ein Steuerorgan in Form eines Ringes auf, der um das Gehäuse der Turbomaschine herum angeordnet ist, und der über eine Vielzahl von an diesem angelenkten Steuerhebeln mit außen liegenden, in der Drehachse der Leitschaufeln vorgesehenen Drehzapfen fest verbunden ist. Die synchronisierte Veränderung der Winkelposition der Leitschaufeln wird dabei durch Drehen des Ringes um die Achse der Turbomaschine erreicht. Ein derart mechanisch betätigter Stellmechanismus zur Winkelverstellung der Leitschaufeln wird beispielsweise in der
Die mit mechanischen Mitteln betätigten Stelleinrichtungen für die Leitschaufeln sind aus Platzgründen und wegen der dort noch geringen, die Funktion der Stellorgane nicht behindernden Temperaturen im vorderen Teil des Verdichters angeordnet. In den stromab liegenden räumlich begrenzten Bereichen des Kompressors und der - zudem sehr hohen Temperaturen ausgesetzten - Turbine wird aus den oben erwähnten Gründen von vornherein vollständig auf die winkelverstellbare Ausbildung der Leitschaufeln verzichtet, zumal die mechanischen Stellmechanismen auch ein hohes Gewicht haben und kostenaufwendig sind. Wenn das Triebwerk auf einer bestimmten - niedrigen - Drehzahl gehalten werden soll, beispielsweise in der Landephase, kann es selbst bei im vorderen Bereich angeordneten winkelverstellbaren Leitschaufeln zum Strömungsabriss an den Schaufeln und zum sogenannten Pumpen des Triebwerks kommen, so dass die Effizienz des Triebwerks und dessen stabile Funktion nicht gewährleistet ist. Auch in der Startund Anstiegsphase kann die Luftströmung im hinteren Bereich des Verdichters vermindert werden und einen Strömungsabriss und letztlich einen Leistungsverlust des Triebwerks zur Folge haben.The actuated by mechanical means actuators for the vanes are arranged for reasons of space and because of there still low, the function of the actuators not obstructing temperatures in the front part of the compressor. In the downstream spatially limited areas of the compressor and the - also exposed to very high temperatures - turbine is completely dispensed with the angle-adjustable design of the vanes from the outset for the reasons mentioned above, especially since the mechanical adjusting mechanisms also have a high weight and are expensive. If the engine is to be maintained at a certain low speed, for example in the landing phase, it may cause stalling of the blades and so-called pumping of the engine, even with front-mounted angle adjustable vanes, so that the efficiency of the engine and its stable function is not guaranteed. Even in the startup and rise phase, the air flow in the rear of the compressor can be reduced, resulting in a stall and ultimately a power loss of the engine.
Der Erfindung liegt daher die Aufgabe zugrunde, ein mit winkelverstellbaren Leitschaufeln ausgerüstetes Gasturbinentriebwerk anzugeben, das bei unterschiedlichen Flugbedingungen einen effizienten Betrieb und eine stabile Funktion gewährleistet.The invention is therefore based on the object to provide a equipped with angle-adjustable vanes gas turbine engine, which ensures efficient operation and stable operation at different flight conditions.
Erfindungsgemäß wird die Aufgabe mit einem gemäß den Merkmalen des Patentanspruchs 1 ausgebildeten Triebwerk gelöst. Weitere Merkmale und zweckmäßige Ausgestaltungen der Erfindung sind Gegenstand der Unteransprüche.According to the invention the object is achieved with a trained according to the features of
Der Grundgedanke der Erfindung besteht in der verstellbaren Ausbildung der Leitschaufeln auch in den stromab gelegenen, engen und hohen Temperaturen ausgesetzten Bereichen des Kompressors und auch der Turbine, so dass auch in unterschiedlichen Flugphasen wie Start, Landung oder Reiseflug eine stabile Funktion und ein effizienter Betrieb des Triebwerks mit geringem Brennstoffverbrauch und ausreichender Generatorleistung gewährleistet ist. Die jeweils erforderliche Änderung des Anstellwinkels α der Leitschaufeln erfolgt in Abhängigkeit von der in der jeweiligen Stufe des Kompressors oder der Turbine herrschenden Temperatur mit sich temperaturabhängig ausdehnenden, das heißt streckenden, vergrößernden oder verformenden Stellelementen, die aus Werkstoffen mit temperaturabhängigem Dehnungs- oder Formänderungsverhalten bestehen. Derartige Stellelemente können auch auf engstem Raum in den hinteren Stufen der Kompressoren und Turbinen angeordnet werden und selbst sehr hohe Temperaturen stehen deren Funktionsfähigkeit nicht entgegen.The basic idea of the invention consists in the adjustable design of the guide vanes also in the downstream, narrow and high temperatures exposed areas of the compressor and the turbine, so that even in different flight phases such as takeoff, landing or cruise a stable function and efficient operation of the Engine with low fuel consumption and sufficient generator power is guaranteed. The respectively required change in the angle of attack α of the guide vanes takes place as a function of the temperature prevailing in the respective stage of the compressor or the turbine with temperature-dependent expanding, that is stretching, enlarging or deforming control elements, which consist of materials with temperature-dependent expansion or deformation behavior. Such control elements can be arranged in the narrowest space in the rear stages of the compressors and turbines and even very high temperatures are not precluding their functionality.
Die Stellelemente können mit der stromauf oder der stromab liegenden Seite der Leitschaufel verbunden sein oder mit beiden Seiten, jedoch in jeweils entgegen gesetzter Richtung wirkend, in Wirkverbindung stehen.The adjusting elements may be connected to the upstream or downstream side of the guide vane or be operatively connected to both sides, but in opposite directions.
Vorzugsweise sind die Leitschaufeln jeweils mit einer Halteplatte verbunden, deren stromab und stromauf liegende Endabschnitte jeweils in einer Nut des Innengehäuses verschwenkbar bzw. um einen Drehpunkt drehbar gehalten sind.Preferably, the guide vanes are each connected to a holding plate whose downstream and upstream end portions are each pivotally mounted in a groove of the inner housing and rotatable about a pivot point.
Das Stellelement kann ein Bimetallstift sein, der entweder axial ausgerichtet ist und mit seinem feststehenden Ende am Innengehäuse oder einem an diesem fixierten Bauteil gehalten ist, oder der radial ausgerichtet ist und mit seinem feststehenden Ende am Außengehäuse oder einem an diesem fixierten Bauteil befestigt ist, während das freie, sich unter Wärmeeinwirkung bewegende Ende an der verschwenkbaren Seite der Leitschaufel bzw. der Halteplatte angreift.The actuator may be a bimetallic pin which is either axially aligned and fixed with its End is held on the inner housing or a fixed to this component, or which is aligned radially and is fixed with its fixed end to the outer housing or a fixed thereto component, while the free, moving under heat end on the pivotable side of the vane or the holding plate attacks.
In weiterer Ausbildung der Erfindung kann auch das mit radial ausgerichteten Stellstiften versehene Außengehäuse aufgrund eines temperatur- und/oder werkstoffbedingt unterschiedlichen Dehnungsverhaltens gegenüber dem Innengehäuse als Stellelement dienen. Ein an dem freien Ende des Stellstiftes ausgebildeter, quer zur Axialrichtung schräg verlaufender Endabschnitt greift in eine gleichermaßen schräg gerichtete Ausnehmung der Leitschaufel ein, so dass sich der Anstellwinkel α der Leitschaufel bei einer durch Erwärmung bedingten Abstandsänderung zwischen Innen- und Außengehäuse ändert.In a further embodiment of the invention, the outer housing provided with radially aligned pins can serve as an actuator due to a temperature and / or material-related different expansion behavior relative to the inner housing. A formed at the free end of the adjusting pin, transversely to the axial direction obliquely extending end portion engages in an equally oblique recess of the vane, so that the angle of attack α of the vane changes at a conditional change due to heating between the inner and outer housing.
In weiterer Ausbildung der Erfindung kann das Stellelement auch ein am Außengehäuse mit einem Dehnungsspiel radial geführter Dehnungsstellring mit an dessen Innenumfang quer zur Axialrichtung schräg verlaufenden Ausnehmungen sein, in die jeweils ein von der Leitschaufel ausgehender schräg verlaufender Stellstift eingreift. Durch die temperaturabhängige Dehnung des Dehnungsstellringes kann somit der Anstellwinkel α der Leitschaufeln verstellt werden.In a further embodiment of the invention, the actuating element can also be a radially outwardly guided on the outer housing with an expansion clearance expansion collar with transverse to the axial direction at its inner periphery obliquely extending recesses, in each of which an outgoing from the vane oblique actuating pin engages. As a result of the temperature-dependent expansion of the expansion adjusting ring, the angle of attack α of the guide vanes can thus be adjusted.
In weiterer Ausbildung der Erfindung ist das Stellelement ein in Umfangsrichtung verlaufender, mit der jeweiligen Leitschaufel und dem Innengehäuse verbundener Dehnungsstift aus einem bei Temperaturänderung in der Länge veränderlichen Werkstoff. Dieser Dehnungsstift kann auch integral an die Leitschaufel, beispielsweise an eine Stirnseite der Halteplatte der Leitschaufel, angeformt sein, während dessen freies Ende mit dem Innengehäuse in Wirkverbindung steht.In a further embodiment of the invention, the actuating element is a circumferentially extending, connected to the respective vane and the inner housing expansion pin from a variable in temperature change in length material. This expansion pin can also be integral with the vane, for example on an end face the holding plate of the vane, be formed, while the free end is in operative connection with the inner housing.
Ausführungsbeispiele der Erfindung werden anhand der Zeichnung näher erläutert. Es zeigen:
- Fig. 1
- eine das Erfindungsprinzip wiedergebende Seitenansicht einer zwischen zwei Laufschaufeln am Innengehäuse gehaltenen und mittels Stellelementen um eine vertikale Achse verschwenkbaren Leitschaufel;
- Fig. 2
- eine Draufsicht auf die Halteplatte (Plattform) der Leitschaufel mit den beiden an dieser wirksamen Stellelementen;
- Fig. 3
- eine Seitenansicht einer mittels Bimetallstift verschwenkbaren Leitschaufel;
- Fig. 4
- eine Draufsicht auf die mit dem Bimetallstift verbundene Schaufelplattform nach
Fig. 3 ; - Fig. 5
- eine Seitenansicht einer mit einem am Außengehäuse gehaltenen Bimetallstift verschwenkbaren Leitschaufel;
- Fig. 6
- eine Seitenansicht einer am Innengehäuse verschwenkbar gehaltenen Leitschaufel, die mit einem am Außengehäuse befestigen Stellstift in Wirkverbindung steht;
- Fig. 7
- einen Schnitt DD nach
Fig. 6 , der das Eingreifen einer mit dem Stellstift verbundenen Schräge in eine Nut der Halteplatte wiedergibt; - Fig. 8
- eine Seitenansicht einer am Innengehäuse verschwenkbar gehaltenen Leitschaufel mit an dieser vorgesehenem schrägen Stellstift, der in eine schräg verlaufenden Stellnut eines am Außengehäuse gehaltenen Dehnungsstellrings eingreift;
- Fig. 9
- eine detaillierte Darstellung nach
Fig. 8 ; - Fig. 10
- eine Seitenansicht einer am Innengehäuse schwenkbar gehaltenen Leitschaufel, deren Halteplatte über einen Dehnungsstift am Innengehäuse angelenkt ist;
- Fig. 11
- eine Draufsicht auf die Halteplatte der Leitschaufel mit dem an diese angelenkten Dehnungsstift nach
Fig. 10 ; und - Fig. 12
- eine Draufsicht einer Ausführungsvariante nach
Fig. 10 , wonach der Dehnungsstift einstückig an die Halteplatte angeformt ist.
- Fig. 1
- a principle of the invention reproducing a side view held between two blades on the inner housing and pivotable by means of adjusting elements about a vertical axis guide vane;
- Fig. 2
- a plan view of the holding plate (platform) of the vane with the two effective on this actuating elements;
- Fig. 3
- a side view of a bimetallic pin pivotable vane;
- Fig. 4
- a plan view of the connected to the bimetal pin blade platform after
Fig. 3 ; - Fig. 5
- a side view of a pivotable with a bimetallic pin held on the outer housing guide vane;
- Fig. 6
- a side view of a pivotally supported on the inner housing vane, which is operatively connected to a fixing pin on the outer housing;
- Fig. 7
- a section DD after
Fig. 6 which reproduces the engagement of a bevel with the adjusting pin in a groove of the holding plate; - Fig. 8
- a side view of a pivotally supported on the inner housing vane with oblique actuating pin provided on this, which engages in an obliquely extending adjusting groove of an outer housing held Dehnungsstellrings;
- Fig. 9
- a detailed representation after
Fig. 8 ; - Fig. 10
- a side view of a pivotally supported on the inner housing vane, the retaining plate is articulated via an expansion pin on the inner housing;
- Fig. 11
- a plan view of the holding plate of the vane with the hinged to this expansion pin
Fig. 10 ; and - Fig. 12
- a plan view of an embodiment according to
Fig. 10 , after which the expansion pin is integrally formed on the holding plate.
Wie die
Gemäß der in den
Bei einer noch anderen, in den
Eine weitere Ausführungsvariante zur Winkelverstellung der Leitschaufeln 1 mit einem temperaturabhängig wirksamen Stellelement ist in den
Die Erfindung ist nicht auf die zuvor erläuterten Ausführungsvarianten beschränkt. Im Rahmen des Grundgedankens der Erfindung, wonach ein Gasturbinentriebwerk in beliebigen, insbesondere auch sehr engen und hohen Temperaturen ausgesetzten Bereichen des Kompressors und/oder der Turbine mit Stellelementen zur variablen Einstellung des Anstellwinkels der Leitschaufeln ausgerüstet ist, die allein aufgrund des thermischen Verhaltens der für die Stellelemente jeweils eingesetzten Werkstoffe eine Winkelverstellung der Leitschaufeln bewirken, sind weitere Modifikationen denkbar. Insbesondere können für die Stellelemente, die auch am hinteren Endabschnitt 7.1 oder an beiden Endabschnitten in entgegen gesetzter Richtung wirksam sein können, unterschiedliche Werkstoffe mit unterschiedlichem thermischem Ausdehnungsverhalten eingesetzt werden. Da die Stellelemente in Abhängigkeit von den entsprechend den jeweiligen Betriebsbedingungen herrschenden Temperaturen und nur aufgrund ihres thermischen Ausdehnungsverhaltens wirksam sind, benötigen sie wenig Platz und können auch in engen und hohen Temperaturen ausgesetzten Bereichen des Kompressors und der Turbine angeordnet werden und sorgen so für deren entsprechend den jeweiligen Betriebsbedingungen stabile Funktion und einen wirtschaftlichen Betrieb des Triebwerks.The invention is not limited to the previously described embodiments. In the context of the basic idea of the invention, according to which a gas turbine engine in any areas of the compressor and / or the turbine which are exposed in particular to very narrow and high temperatures is equipped with adjusting elements for variably adjusting the angle of attack of the guide vanes Adjusting elements respectively used materials cause an angular adjustment of the vanes, further modifications are conceivable. In particular, different materials with different thermal expansion behavior can be used for the adjusting elements, which can also be effective in the opposite direction at the rear end section 7.1 or at both end sections. Since the actuators are effective in response to the prevailing temperatures according to the respective operating conditions and only because of their thermal expansion behavior, they require little space and can also be placed in narrow and high temperature exposed areas of the compressor and the turbine, thus providing their according to the operating conditions stable operation and economical operation of the engine.
- 11
- Leitschaufelvane
- 22
- HalteplatteRetaining plate
- 33
- Ausnehmungen in 4Recesses in 4
- 44
- Innengehäuseinner housing
- 55
- Rotorscheiberotor disc
- 66
- Laufschaufelblade
- 7.17.1
- stromab liegender Endabschnitt v. 2downstream end section v. 2
- 7.27.2
- stromauf liegender Endabschnitt v. 2upstream end section v. 2
- 88th
-
Stellelement (
Fig. 1, 2 )Adjusting element (Fig. 1, 2 ) - 9.19.1
- stromab liegende Nut von 7.1downstream groove of 7.1
- 9.29.2
- stromauf liegende Nut von 9.2upstream groove of 9.2
- 1010
- Fixierstift v. 9.1Fixing pin v. 9.1
- 1111
- Bimetallstift (radial o. axial ausgerichtet)Bimetal pin (radially or axially aligned)
- 1212
- Außengehäuseouter casing
- 1313
- Stellstift von 12Stellstift of 12
- 1414
- schräger Endabschnitt v. 13oblique end section v. 13
- 1515
- DehnungsstellringStretch collar
- 1616
- Umfangsnut v. 15Circumferential groove v. 15
- 1717
- Führungsstück v. 12Guide piece v. 12
- 1818
- schräge Stellnut v. 15oblique Stellnut v. 15
- 1919
- schräger Stellstift v. 1oblique Stellstift v. 1
- 2020
- Dehnungsstiftelongation pin
- 2121
- integraler Dehnungsstift v. 1integral strain pin v. 1
- 2222
- schräge Ausnehmung v. 7.2oblique recess v. 7.2
Claims (13)
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
DE102008033560A DE102008033560A1 (en) | 2008-07-17 | 2008-07-17 | Gas turbine engine with adjustable vanes |
Publications (2)
Publication Number | Publication Date |
---|---|
EP2146056A2 true EP2146056A2 (en) | 2010-01-20 |
EP2146056A3 EP2146056A3 (en) | 2015-09-09 |
Family
ID=40848201
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
EP09164130.8A Withdrawn EP2146056A3 (en) | 2008-07-17 | 2009-06-30 | Gasturbine engine with variable stator vanes |
Country Status (3)
Country | Link |
---|---|
US (1) | US8257021B2 (en) |
EP (1) | EP2146056A3 (en) |
DE (1) | DE102008033560A1 (en) |
Cited By (1)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3339608A3 (en) * | 2012-08-27 | 2018-09-05 | United Technologies Corporation | Shiplap cantilevered stator |
Families Citing this family (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP2815485B1 (en) | 2012-02-16 | 2021-04-07 | Rolls-Royce North American Technologies, Inc. | Gas turbine engine and electric machine |
US9932851B2 (en) * | 2013-12-30 | 2018-04-03 | Rolls-Royce North American Technologies, Inc. | Active synchronizing ring |
FR3094696B1 (en) * | 2019-04-02 | 2022-07-01 | Liebherr Aerospace Toulouse Sas | TWO-TURBINE AIR CONDITIONING SYSTEM |
US11719111B1 (en) | 2022-06-29 | 2023-08-08 | Pratt & Whitney Canada Corp. | Variable guide vane system |
Citations (1)
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US3325087A (en) | 1965-04-28 | 1967-06-13 | David R Davis | Stator casing construction for gas turbine engines |
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US2970808A (en) * | 1957-10-30 | 1961-02-07 | Westinghouse Electric Corp | Bimetallic shroud structure for rotor blades |
GB1381277A (en) * | 1971-08-26 | 1975-01-22 | Rolls Royce | Sealing clearance control apparatus for gas turbine engines |
GB1510629A (en) * | 1974-08-08 | 1978-05-10 | Penny Turbines Ltd N | Centrifugal compressor or centripetal turbine |
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DE2618779C2 (en) * | 1976-04-29 | 1985-12-19 | Daimler-Benz Ag, 7000 Stuttgart | Turbine of an exhaust gas turbocharger for internal combustion engines |
JPS5893903A (en) * | 1981-11-30 | 1983-06-03 | Hitachi Ltd | Variable inlet guide vane |
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DE3542762A1 (en) * | 1985-12-04 | 1987-06-11 | Mtu Muenchen Gmbh | DEVICE FOR CONTROLLING OR CONTROLLING GAS TURBINE ENGINES OR GAS TURBINE JET ENGINES |
GB2206381B (en) * | 1987-06-30 | 1991-10-09 | Rolls Royce Plc | A variable stator vane arrangement for a compressor |
DE3913102C1 (en) * | 1989-04-21 | 1990-05-31 | Mtu Muenchen Gmbh | |
IT1248305B (en) * | 1990-05-29 | 1995-01-05 | Gen Electric | AUTOMATIC VARIABLE GEOMETRY VORTIC FORMER |
DE19516382A1 (en) * | 1995-05-04 | 1996-11-07 | Deutsche Forsch Luft Raumfahrt | Adjustment ring |
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US6227798B1 (en) * | 1999-11-30 | 2001-05-08 | General Electric Company | Turbine nozzle segment band cooling |
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US7125223B2 (en) * | 2003-09-30 | 2006-10-24 | General Electric Company | Method and apparatus for turbomachine active clearance control |
GB0326544D0 (en) * | 2003-11-14 | 2003-12-17 | Rolls Royce Plc | Variable stator vane arrangement for a compressor |
GB2416194B (en) * | 2004-07-15 | 2006-08-16 | Rolls Royce Plc | A spacer arrangement |
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2008
- 2008-07-17 DE DE102008033560A patent/DE102008033560A1/en not_active Withdrawn
-
2009
- 2009-06-30 EP EP09164130.8A patent/EP2146056A3/en not_active Withdrawn
- 2009-07-06 US US12/498,089 patent/US8257021B2/en not_active Expired - Fee Related
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US3325087A (en) | 1965-04-28 | 1967-06-13 | David R Davis | Stator casing construction for gas turbine engines |
Cited By (2)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
EP3339608A3 (en) * | 2012-08-27 | 2018-09-05 | United Technologies Corporation | Shiplap cantilevered stator |
US10309235B2 (en) | 2012-08-27 | 2019-06-04 | United Technologies Corporation | Shiplap cantilevered stator |
Also Published As
Publication number | Publication date |
---|---|
EP2146056A3 (en) | 2015-09-09 |
US20100014960A1 (en) | 2010-01-21 |
DE102008033560A1 (en) | 2010-01-21 |
US8257021B2 (en) | 2012-09-04 |
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