EP2554797A2 - Système et procédé permettant de commander passivement le jeu dans un moteur de turbine à gaz - Google Patents

Système et procédé permettant de commander passivement le jeu dans un moteur de turbine à gaz Download PDF

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Publication number
EP2554797A2
EP2554797A2 EP12177897A EP12177897A EP2554797A2 EP 2554797 A2 EP2554797 A2 EP 2554797A2 EP 12177897 A EP12177897 A EP 12177897A EP 12177897 A EP12177897 A EP 12177897A EP 2554797 A2 EP2554797 A2 EP 2554797A2
Authority
EP
European Patent Office
Prior art keywords
engine
control member
assembly
gap control
rotor assembly
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Withdrawn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
EP12177897A
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German (de)
English (en)
Inventor
James Adaickalasamy
Hariharan Sundaram
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of EP2554797A2 publication Critical patent/EP2554797A2/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Withdrawn legal-status Critical Current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
    • F01D11/00—Preventing or minimising internal leakage of working-fluid, e.g. between stages
    • F01D11/08—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator
    • F01D11/14—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing
    • F01D11/16—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means
    • F01D11/18—Adjusting or regulating tip-clearance, i.e. distance between rotor-blade tips and stator casing by self-adjusting means using stator or rotor components with predetermined thermal response, e.g. selective insulation, thermal inertia, differential expansion
    • 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 subject matter disclosed herein relates to clearance control systems for gas turbine engines, and more particularly, to a system and method for controlling operating clearance between a stationary shroud surface of a turbine engine and an adjacent rotating assembly.
  • Gas turbine engines typically include a rotating assembly housed within a static assembly.
  • the rotating assembly typically includes sets of compressor blades (i.e., airfoils) and turbine blades.
  • the compressor blades compress incoming air, and the turbine blades extract power from the air, usually after the addition of heat.
  • the static assembly surrounds the rotating assembly and helps to define the flow path of the engine.
  • a static assembly includes a series of shroud segments providing an inner surface to cooperate with outer surfaces (i.e., tips) of the blades of an adjacent rotating assembly.
  • Efficiency of a turbine engine depends, at least in part, on the clearance or gap between the shroud surface and the adjacent rotating blades.
  • the term axial refers to the direction of the central axis of a gas turbine engine, i.e., about which axis the turbo-machinery rotates.
  • the term radial refers to a direction that is substantially perpendicular to the central axis, and the term circumferential refers to a set of locations and directions that do not intersect the central axis but that lie in one or more radial planes.
  • Complicating clearance problems in such apparatus is the well known fact that clearances between the rotor assembly and the static assembly of a turbine engine typically change with engine operating conditions such as acceleration, deceleration, or other changing thermal or centrifugal force conditions experienced by the cooperating members during engine operation.
  • Clearance control mechanisms for such assemblies sometimes referred to as active or passive clearance control systems, have included mechanical systems or systems based on thermal expansion and contraction characteristics of materials for the purpose of maintaining selected clearance conditions during engine operation. Such systems generally require use of substantial amounts of air for heating or cooling at the expense of such air otherwise being used in the engine operating cycle.
  • a system for passively controlling clearance in a gas turbine engine comprises a static assembly arranged circumferentially about an engine rotor assembly and defining a gap between a tip end of the rotor assembly and an inner surface of the static assembly adjacent to the tip end.
  • the system includes a gap control member that defines the inner surface, is exposed to the engine working fluid, and comprises a shape memory material selected and preconditioned to deform in a pre-selected manner in response to a temperature of the engine working fluid.
  • the system may further comprise a rotor assembly having a plurality of airfoil blades, each blade having a tip end.
  • the rotor assembly is surrounded by the static assembly comprising a plurality of shroud segments arranged circumferentially about the rotor assembly, each shroud segment having an inner surface adjacent to the tip end, and the inner surfaces of the shroud segments and the tip ends of the airfoil blades defining a radial gap between the tip ends and the inner surfaces.
  • Each airfoil blade includes the gap control member that forms the tip end, the gap control member comprising a shape memory material selected and preconditioned to deform in a pre-selected manner in response to a temperature of the engine working fluid.
  • a method for passively controlling clearance in a gas turbine engine comprises assembling the turbine engine so as to define an initial set of build clearances between a stationary shroud surface of the turbine engine and an adjacent rotor assembly of the turbine engine.
  • the assembled engine is operated throughout a range of engine operating conditions, and an operating clearance is observed at one or more of the engine operating conditions.
  • a gap control member is formulated and configured comprising a shape memory material selected and preconditioned to deform in a pre-selected manner in response to a temperature of the engine working fluid.
  • the engine is re-assembled with the gap control member so as to define a revised set of build clearances between the stationary shroud surface and the adjacent rotor assembly.
  • FIG. 1 shows a portion of a gas turbine engine 100 comprising a rotating assembly 170 housed within a static assembly 160.
  • Rotor assembly 170 carries a rotating blade 110, which has a tip end 112 and an apposing hub end 118.
  • Rotating blade 110 also has a leading edge 114 and a trailing edge 116.
  • rotating blade is a turbine blade, but it should be appreciated that the features shown could be applied to a compressor.
  • Static assembly 160 includes stator 180, which guides a working fluid, such as air or steam or air mixed with fuel, toward the leading edge 114.
  • Static assembly also includes shroud segments 120 that guide the working fluid through rotating blade 110 so that rotating blade 110 can extract energy (i.e., torque) from the fluid (or, in the case of a compressor, so that the blade can perform work on the fluid).
  • Each shroud segment 120 has an inner shroud surface 122 on which gap control member 130 is attached.
  • Gap control member 130 is exposed to the working fluid and has an inner controlled surface 132 facing radially inward toward tip end 112.
  • static assembly 160 includes means for adjusting the radial position of shroud segment 120, including radial adjustment member 124, and shims 126.
  • Gap control member 130 comprises a shape memory material.
  • a suitable shape memory material may comprise an alloy or a polymer or another material known in the art for providing a desired shape memory behavior characteristic.
  • a metallic shape memory alloy SMA is a metal alloy that changes from an initial shape to a second shape upon exposure to a transition temperature and changes back to the initial shape upon re-cooling. SMA materials that exhibit such shape changes with temperature typically undergo a solid state micro-structural phase change. This characteristic enables an article made from SMA to change from one physical shape to at least another physical shape and to return to the original shape. These changes in shape are much more dramatic than simple thermal expansion and contraction.
  • transition temperature of the material In addition, with SMA, most or all of the changes in shape occur over a relatively small temperature range known as the transition temperature of the material.
  • a metallic SMA material is a titanium nickel alloy, also known as Nitinol alloy.
  • Other metallic SMA materials may comprise ruthenium alloyed with niobium and/or tantalum. Transition temperatures of exemplary shape memory materials depend upon the particular composition of the material and can be configured to occur at temperatures between approximately 25 degrees C and about 1400 degrees C, with the transition temperature depending upon the specific formulation of the material.
  • the article In the manufacture (from such a metallic SMA or other shape memory material) of an article intended to change during operation from one shape to at least one other shape, the article is provided in a first shape intended for operating use at or above the transition temperature.
  • first shape is developed by working and annealing an article comprising the alloy or other material at or above the transition temperature, at which the solid state micro-structural phase change occurs.
  • such an alloy or other material may be malleable such that the article of the first shape can be deformed into a desired second shape, for example, to facilitate inclusion at substantially room temperature in an assembly.
  • the article in the second shape is heated at or above its critical temperature, it undergoes a micro-structural phase change that results in it returning to the first shape.
  • gap control member 130 comprises a shape memory material and is exposed to the working fluid at its axial location in the flow-path. Therefore, while gap control member 130 may exchange some heat with shroud segment 120, the temperature of gap control member 130, under steady-state conditions, will approximate the temperature of the working fluid at its axial location. Thus, by formulating the material used to make gap control member 130, its shape can be programmed to change depending upon the flow-path temperature without requiring parasitic extraction of working fluid.
  • radial adjustment member 124 which may also comprise shape memory material, is not typically directly exposed to the working fluid at its axial location. Instead, radial adjustment member 124 may be exposed to a mixture of fluid sources, enabling the temperature of the fluid to be actively controlled, and thereby enabling the shape of radial adjustment member 124 to be controlled. Yet, while the shape of radial adjustment member 124 may thus be controlled, doing so requires parasitic extraction of working fluid, which may mitigate performance gains that would otherwise be realized through the active clearance control scheme.
  • the size of clearance gap 150 depends upon a number of factors including initial build clearance, thermal expansion and/or contraction of static assembly 160 and rotor assembly 170, centrifugal stresses resulting from the rotational speed of the rotor assembly 170, external loads, aerodynamic loads, and other effects. These factors can cause the size of clearance gap 150 to change throughout the operational envelope of engine 100.
  • the size of clearance gap 150 adjacent to leading edge 114 may not be equal to the size of clearance gap 150 adjacent to trailing edge 114.
  • the shape of static assembly 160 may not be round, and thus the circumferential surface defined by the combination of inner controlled surfaces 132 may also not be round, the size of clearance gap 150 may vary from one shroud segment to another.
  • both the first shape and the second shape of gap control member 130 and the transition temperature of the shape memory material can be configured to contribute to a system for reducing the size of clearance gap 150.
  • Other elements of an exemplary system may optionally include one or more active clearance control mechanisms such as radial adjustment member 124.
  • Other passive elements may also be included such as shims 126.
  • an engine may be assembled with relatively open clearances, and then operated throughout a range of operating conditions while detecting the operating clearances. Then, based on the observed data, one or more clearance adjustment mechanisms may be implemented so as to achieve a desired level of clearances.
  • inner controlled surface 132 of gap control member 130 may exhibit a planar shape. In another embodiment, inner controlled surface 132 of gap control member 130 may exhibit a non-planar shape. In an exemplary embodiment, gap control member 130 may be configured to retain a first shape at temperatures less than 100 degrees C. In another exemplary embodiment, gap control member 130 may be configured to retain a first shape at temperatures less than 200 degrees C. In another exemplary embodiment, gap control member 130 may be configured to retain a first shape at temperatures less than 300 degrees C. Other embodiments of gap control member 130 may be formulated to change shape at temperatures of approximately 400 degrees C, 500 degrees C, 600 degrees C, 700 degrees C, 800 degrees C, or any other operating temperature where it is advantageous to change the shape of gap control member 130.
  • static assembly 260 may include an abradable layer 240 disposed between gap control member 230 and blade 210.
  • abradable layer 240 may comprise a coating applied to a radially inward surface of gap control member 230 and may comprise a material that can deform or be abraded in the event of contact with tip end 212 without damaging tip end 212 or blade 210. Incorporation of abradable layer 240 will allow for closer clearances and offsetting the need to account for thermal expansion as well and changes in concentricity due to shock loading events.
  • Abradable layer 240 may be applied through thermal spraying, sintering, casting or any other suitable means known in the art.
  • Thermal spraying involves sprayed application of melted or heated material.
  • Sintering involves application of powdered metal followed by heating of the composite article.
  • a gap control member 330 may also be applied to a tip end 312 of blade 310.
  • FIG. 4 shows an enlarged view of the region of a gas turbine engine between a static assembly 420 and a rotor assembly 410.
  • Gap control member 430 is attached to an inner shroud surface 422 of static assembly 420, and an abradable layer 440 is attached to gap control member 430 adjacent to tip end 412.
  • clearance gap 450 is relatively open, corresponding to a first shape of gap control member 430 that is relatively thin.
  • a first shape of gap control member 430 occurs when the operating temperature of the working fluid is below the transition temperature of gap control member 430.
  • FIG. 5 shows an enlarged view of the same region as Fig. 4 , wherein clearance gap 550 is relatively closed, corresponding to a second shape of gap control member 530 that is relatively thick.
  • a second shape of gap control member 530 occurs when the operating temperature of the working fluid is above the transition temperature of gap control member 530.
  • FIG. 6 shows an enlarged view of a portion of a gas turbine engine wherein exemplary shroud segments 620 include gap control members 630 configured to compensate for eccentricity or other non-circularity in the assembled static assembly 660.
  • exemplary shroud segments 620 include gap control members 630 configured to compensate for eccentricity or other non-circularity in the assembled static assembly 660.
  • a relatively thin and constant clearance gap 650 is provided between blade 610 and inner shroud surface 622 by incorporation of gap control members 630.
  • gap control members at 632 are relatively thin compared to gap control members at 634.
  • FIG. 7 is a flow chart showing an exemplary method for reduced operating clearance between a stationary shroud surface of a turbine engine and an adjacent rotating assembly.
  • an engine is assembled (step 710) comprising a static assembly and a rotor assembly.
  • the engine is operated (step 720) throughout a range of operating conditions, and clearances are measured (step 730) at those operating conditions.
  • a clearance control strategy is devised (step 740) considering available clearance control methods.
  • shape memory materials are formulated and configured (step 750) so as to configure customized gap control members that are capable of achieving desired shape changes at defined engine operating temperatures.
  • the strategy is then implemented (step 760) and may comprise adjusting control schedules so as to maintain a desired level of clearances without rebuilding the engine or otherwise re-shimming or adjusting the static assembly of the engine.
  • clearances can again be evaluated (step 780) to determine the effectiveness of the implemented strategy.
  • steps 740 through this step may be repeated (step 790) until a desirable clearance profile has been achieved.
  • the invention provides an improved system and method for reducing clearances and thereby improving gas turbine performance and efficiency.
  • shape memory materials are preconditioned to deform only upon achieving a predetermined temperature level, such as steady-state operating temperatures.
  • a predetermined temperature level such as steady-state operating temperatures.
  • the gap control members that comprise the shape memory materials are positioned in or near to the working fluid, there is no external actuation medium required to actuate the gap control members.
  • the invention provides a simple method for addressing eccentricity or other non-circularity in static assemblies and in operation of rotor assemblies and can be applied to compressor and turbine sections.
  • the invention can be applied to address transient differences in dimensions of static assemblies and rotor assemblies and to address variations in manufacturing.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP12177897A 2011-08-01 2012-07-25 Système et procédé permettant de commander passivement le jeu dans un moteur de turbine à gaz Withdrawn EP2554797A2 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/195,273 US20130034423A1 (en) 2011-08-01 2011-08-01 System and method for passively controlling clearance in a gas turbine engine

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EP2554797A2 true EP2554797A2 (fr) 2013-02-06

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EP12177897A Withdrawn EP2554797A2 (fr) 2011-08-01 2012-07-25 Système et procédé permettant de commander passivement le jeu dans un moteur de turbine à gaz

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US (1) US20130034423A1 (fr)
EP (1) EP2554797A2 (fr)
CN (1) CN102913290A (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3022398A4 (fr) * 2013-07-15 2017-03-01 United Technologies Corporation Régulation d'espacement de turbine à l'aide d'un matériau à faible alpha
GB2596139A (en) * 2020-06-19 2021-12-22 Rolls Royce Plc Fan blade tip operating clearance optimisation

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2531521B (en) * 2014-10-20 2019-03-27 Rolls Royce Plc A fluid conduit for a gas turbine engine
CN106089324B (zh) * 2016-06-07 2018-05-01 中国南方航空工业(集团)有限公司 静子机匣密封结构
US10794213B2 (en) * 2016-06-21 2020-10-06 Rolls-Royce North American Technologies Inc. Blade tip clearance control for an axial compressor with radially outer annulus
US20180221958A1 (en) * 2017-02-07 2018-08-09 General Electric Company Parts and methods for producing parts using hybrid additive manufacturing techniques
US10774668B2 (en) * 2017-09-20 2020-09-15 General Electric Company Intersage seal assembly for counter rotating turbine
US10458267B2 (en) * 2017-09-20 2019-10-29 General Electric Company Seal assembly for counter rotating turbine assembly
DE102019201658A1 (de) * 2019-02-08 2020-08-13 MTU Aero Engines AG Verfahren zum erneuern eines einlaufbelags eines mantelstromtriebwerks
US11420755B2 (en) * 2019-08-08 2022-08-23 General Electric Company Shape memory alloy isolator for a gas turbine engine
US11808157B1 (en) 2022-07-13 2023-11-07 General Electric Company Variable flowpath casings for blade tip clearance control

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2970808A (en) * 1957-10-30 1961-02-07 Westinghouse Electric Corp Bimetallic shroud structure for rotor blades
US3146992A (en) * 1962-12-10 1964-09-01 Gen Electric Turbine shroud support structure
JPS58206807A (ja) * 1982-05-28 1983-12-02 Hitachi Ltd 軸流タ−ビンの動翼先端すき間制御装置
JPS5915605A (ja) * 1982-07-15 1984-01-26 Toshiba Corp ガスタ−ビン
US6036437A (en) * 1998-04-03 2000-03-14 General Electric Co. Bucket cover geometry for brush seal applications
FR2831637B1 (fr) * 2001-10-25 2004-01-30 Snecma Moteurs Joint d'etancheite a deux levres concentriques
US7367776B2 (en) * 2005-01-26 2008-05-06 General Electric Company Turbine engine stator including shape memory alloy and clearance control method
EP1715140A1 (fr) * 2005-04-21 2006-10-25 Siemens Aktiengesellschaft Aube de turbine ayant une bande couvrante et une couche de protection sur la bande couvrante
GB2437298B (en) * 2006-04-18 2008-10-01 Rolls Royce Plc A Seal Between Rotor Blade Platforms And Stator Vane Platforms, A Rotor Blade And A Stator Vane
US8052380B2 (en) * 2008-10-29 2011-11-08 General Electric Company Thermally-activated clearance reduction for a steam turbine
US8678753B2 (en) * 2009-11-30 2014-03-25 Rolls-Royce Corporation Passive flow control through turbine engine

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
None

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP3022398A4 (fr) * 2013-07-15 2017-03-01 United Technologies Corporation Régulation d'espacement de turbine à l'aide d'un matériau à faible alpha
GB2596139A (en) * 2020-06-19 2021-12-22 Rolls Royce Plc Fan blade tip operating clearance optimisation

Also Published As

Publication number Publication date
US20130034423A1 (en) 2013-02-07
CN102913290A (zh) 2013-02-06

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