EP2146056A2 - Turbine à gaz avec aubes directrices variables - Google Patents

Turbine à gaz avec aubes directrices variables Download PDF

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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.)
Withdrawn
Application number
EP09164130A
Other languages
German (de)
English (en)
Other versions
EP2146056A3 (fr
Inventor
Stuart Lee
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.)
Rolls Royce Deutschland Ltd and Co KG
Original Assignee
Rolls Royce Deutschland Ltd and Co KG
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 Rolls Royce Deutschland Ltd and Co KG filed Critical Rolls Royce Deutschland Ltd and Co KG
Publication of EP2146056A2 publication Critical patent/EP2146056A2/fr
Publication of EP2146056A3 publication Critical patent/EP2146056A3/fr
Withdrawn legal-status Critical Current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
    • 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)
  • Supercharger (AREA)
EP09164130.8A 2008-07-17 2009-06-30 Turbine à gaz avec aubes directrices variables Withdrawn EP2146056A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DE102008033560A DE102008033560A1 (de) 2008-07-17 2008-07-17 Gasturbinentriebwerk mit verstellbaren Leitschaufeln

Publications (2)

Publication Number Publication Date
EP2146056A2 true EP2146056A2 (fr) 2010-01-20
EP2146056A3 EP2146056A3 (fr) 2015-09-09

Family

ID=40848201

Family Applications (1)

Application Number Title Priority Date Filing Date
EP09164130.8A Withdrawn EP2146056A3 (fr) 2008-07-17 2009-06-30 Turbine à gaz avec aubes directrices variables

Country Status (3)

Country Link
US (1) US8257021B2 (fr)
EP (1) EP2146056A3 (fr)
DE (1) DE102008033560A1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3339608A3 (fr) * 2012-08-27 2018-09-05 United Technologies Corporation Stator en porte-à-faux à feuillure

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2013123479A1 (fr) 2012-02-16 2013-08-22 Rolls-Royce North American Technologies, Inc. Turbine à gaz et machine électrique
US9932851B2 (en) 2013-12-30 2018-04-03 Rolls-Royce North American Technologies, Inc. Active synchronizing ring
FR3094696B1 (fr) * 2019-04-02 2022-07-01 Liebherr Aerospace Toulouse Sas Système de conditionnement d’air biturbine
US11719111B1 (en) 2022-06-29 2023-08-08 Pratt & Whitney Canada Corp. Variable guide vane system

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3325087A (en) 1965-04-28 1967-06-13 David R Davis Stator casing construction for gas turbine engines

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DE3913102C1 (fr) * 1989-04-21 1990-05-31 Mtu Muenchen Gmbh
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Publication number Priority date Publication date Assignee Title
US3325087A (en) 1965-04-28 1967-06-13 David R Davis Stator casing construction for gas turbine engines

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3339608A3 (fr) * 2012-08-27 2018-09-05 United Technologies Corporation Stator en porte-à-faux à feuillure
US10309235B2 (en) 2012-08-27 2019-06-04 United Technologies Corporation Shiplap cantilevered stator

Also Published As

Publication number Publication date
DE102008033560A1 (de) 2010-01-21
US8257021B2 (en) 2012-09-04
EP2146056A3 (fr) 2015-09-09
US20100014960A1 (en) 2010-01-21

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