EP2666971A1 - Strömungsmaschine mit Abstandssteuerungsfähigkeit - Google Patents

Strömungsmaschine mit Abstandssteuerungsfähigkeit Download PDF

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Publication number
EP2666971A1
EP2666971A1 EP13167700.7A EP13167700A EP2666971A1 EP 2666971 A1 EP2666971 A1 EP 2666971A1 EP 13167700 A EP13167700 A EP 13167700A EP 2666971 A1 EP2666971 A1 EP 2666971A1
Authority
EP
European Patent Office
Prior art keywords
movable portion
turbomachine
blade
rotatable cam
cam
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Withdrawn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
EP13167700.7A
Other languages
English (en)
French (fr)
Inventor
Joseph Anthony Cotroneo
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 EP2666971A1 publication Critical patent/EP2666971A1/de
Withdrawn legal-status Critical Current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
    • F01D11/20—Actively adjusting tip-clearance
    • F01D11/22—Actively adjusting tip-clearance by mechanically actuating the stator or rotor components, e.g. moving shroud sections relative to the rotor
    • 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
    • F05D2230/644—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins for adjusting the position or the alignment, e.g. wedges or eccenters

Definitions

  • the subject matter disclosed herein relates generally to turbomachines and, more particularly, to turbomachines having clearance control capability.
  • a typical turbomachine such as a gas turbine engine, a steam turbine engine and a compressor, includes a compressor section, a combustor section and a turbine section.
  • the compressor section compresses inlet air and transmits the compressed inlet air to the combustor section.
  • the combustor section combusts the compressed inlet air along with fuel to produce high energy fluids, which are transferred to the turbine section where they are expanded in power generation operations.
  • the high energy fluids aerodynamically interact with successive stages of turbine blades, which are encompassed within a turbine casing with clearances provided between the casing and the tips of the blades.
  • the high energy fluids impinge upon the turbine blades and induce rotation of the turbine blades about a rotor. Since the high energy fluids have high temperatures and pressures, the turbine blades and the casing often undergo thermal deformation (i.e., expansion or contraction) based on a type of turbine operation being conducted. Such deformation can be accounted for by setting the clearances in accordance with worst case scenarios. Under normal operating conditions, however, clearances set in accordance with worst case scenarios may be excessive and could lead to degraded performance due to leakages between the casing and the tips of the blades.
  • a turbomachine having clearance control capability includes a turbine stage including a blade configured to rotate around a centerline, a movable portion of a casing circumferentially surrounding the turbine stage and a rotatable cam operably coupled to the movable portion and thereby configured to control an axial position of the movable portion.
  • a radially outermost tip of the blade and an interior surface of the movable portion are sloped with respect to the centerline such that the controlled axial position of the movable portion is determinative of a clearance between the blade and the movable portion.
  • a turbomachine having clearance control capability includes a turbine stage including a blade configured to rotate around a centerline, a casing circumferentially surrounding the turbine stage and including forward, aft and movable portions, the movable portion being axially interposed and secured between the forward and aft portions and defining a cam seat in a radially exterior surface thereof and a rotatable cam received within and operably coupled to the cam seat of the movable portion, the rotatable cam being thereby configured to control an axial position of the movable portion in accordance with rotation thereof.
  • a radially outermost tip of the blade and an interior surface of the movable portion are sloped with respect to the centerline such that the controlled axial position of the movable portion is determinative of a clearance between the blade and the movable portion.
  • a system providing a turbomachine with clearance control capability includes at least one or more turbine stages, each of the at least one or more turbine stages including a blade configured to rotate around a centerline, a movable portion of a casing circumferentially surrounding the at least one or more turbine stages, a rotatable cam operably coupled to the movable portion and thereby configured to control an axial position of the movable portion and a controller.
  • a radially outermost tip of the blade of each of the at least one or more turbine stages and an interior surface of the movable portion are sloped with respect to the centerline such that the controlled axial position of the movable portion is determinative of a clearance between the blade of each of the at least one or more turbine stages and the movable portion.
  • the controller is operably coupled to the rotatable cam and thereby configured to control operations of the rotatable cam.
  • the portion of the turbomachine 10 includes a turbine stage 20 that is normally defined with a stationary blade row (i.e., nozzles) and a rotating blade row (i.e., buckets), a casing 40, a rotatable cam 60 and a controller 80.
  • the turbine stage 20 may be any one of at least one or more of several turbine stages disposed at various axial locations along the turbomachine 10, including, but not limited to, the last turbine stage.
  • the turbine stage 20 includes a blade 21 that is configured to rotate along with a blade row around a centerline 22.
  • the blade 21 may be provided as a plurality of blades that is arranged in a circumferential array 210 around the centerline 22.
  • Each blade 21 has an airfoil shape such that aerodynamic interactions between the blade 21 and a working fluid flowing through the turbine stage 20 induces rotation of the blade 21 around the centerline 22.
  • Each blade 21 also includes a sloped tip 23 at a radially outermost edge thereof.
  • the casing 40 is provided to circumferentially surround the turbine stage 20 and, in some cases, additional stages as shown in FIG. 5 , which is described below.
  • the casing 40 includes an annular forward portion 41, an annular aft portion 42 and an annular movable portion 43.
  • the annular movable portion 43 is axially interposed and secured between the annular forward portion 41 and the annular aft portion 42 and includes an annular central body 44, a first annular flange 45, a second annular flange 46, a sloped interior facing surface 47 and a radially exterior surface 48.
  • the annular forward portion 41 is formed to define an aft facing recess 410 and the annular aft portion 42 is similarly formed to define a forward facing recess 420.
  • the first annular flange 45 extends in a forward axial direction from the annular central body 44 and is movably receivable within the aft facing recess 410.
  • the second annular flange 46 extends in an aft axial direction from the annular central body 44 and is movably receivable in the forward facing recess 420.
  • the first annular flange 45 penetrates relatively deeply into the aft facing recess 410 while the second annular flange 46 recedes from but does not exit the forward facing recess 420.
  • the first annular flange 45 recedes from but does not exit the aft facing recess 410 while the second annular flange 46 penetrates relatively deeply into the forward facing recess 420.
  • Anti-rotation features such as annularly discrete tabs 49 may be disposed on the movable portion 43 at, for example, either or both of the first annular flange 45 and the second annular flange 46.
  • Such annularly discrete tabs 49 are receivable in secondary recesses 430 defined in the annular forward portion 41 and the annular aft portion 42.
  • the annularly discrete tabs 49 penetrate relatively deeply into and recede from the secondary recesses 430. While receding, the annularly discrete tabs 49 do not exit the secondary recesses 430.
  • the sloped interior facing surface 47 of the annular movable portion 43 is disposable radially outwardly from the sloped tip 23 of the blade 21 at a distance that is defined by the controlled clearance between the blade 21 and the annular movable portion 43.
  • the sloped tip 23 and the sloped interior facing surface 47 may be provided substantially in parallel with one another and slope away from the centerline 22 with increasing distance in the aft axial direction, D.
  • the sloped tip 23 provides for improved boundary layer conditions downstream from the turbine stage 20 and thereby allows for relatively aggressive exhaust diffuser performance.
  • the rotatable cam 60 is operably coupled to the annular movable portion 43 and is thereby configured to control an axial position of the annular movable portion 43.
  • the controlled axial position of the annular movable portion 43 is determinative of a controlled amount of clearance between the blade 21 and the annular movable portion 43 or, more specifically, between the sloped tip 23 and the sloped interior facing surface 47. This control allows for improved efficiency and output for the turbine stage 20 in the unshrouded condition and could be similarly applicable and useful for shrouded turbine stages as well.
  • the rotatable cam 60 includes a drive shaft 61, which may be operably coupled to the controller 80 to be described in greater detail below, and a head portion 62.
  • the head portion 62 may be generally circular, for example, and may be coupled in an off-center condition to the drive shaft 61. As the drive shaft 61 rotates about longitudinal axis 610, the head portion 62 bobs back and forth on either side of the drive shaft 61.
  • the radially exterior surface 48 of the annular movable portion 43 is formed to define a cam seat 90.
  • the cam seat 90 is receptive of the head portion 62 of the rotatable cam 60 such that the drive shaft 61 appears to extend, for example, radially outwardly from the annular movable portion 43.
  • the cam seat 90 is configured to mechanically interfere with the head portion 62 such that, as the rotatable cam 60 rotates in first or second opposite directions about the longitudinal axis 610, the annular movable portion 43 correspondingly moves in first or second opposite axial directions, respectively.
  • the cam seat 90 may include a recess 91 formed in the radially exterior surface 48, which is bounded on forward and aft sides by a pair of substantially parallel circumferential wall surfaces 92.
  • the head portion 62 sits tightly within the recess 91 such that its sidewalls abut each of the wall surfaces 92 in opposite directions.
  • the rotatable cam 60 rotates about the longitudinal axis 610, the forward and aft sides of the head portion 62 impinge upon the wall surfaces 92 and, therefore, force the annular movable portion 43 to movably reciprocate in forward and aft directions.
  • the head portion 62 and the cam seat 90 are described above as being a generally circular element and as a recess 91 that is bounded by wall surfaces 92, it is to be understood that this is merely exemplary and that other embodiments exist.
  • the cam seat 90 may also be provided as a circular or polygonal recess defined within the radially exterior surface 48.
  • the controller 80 is provided as a component of a system for providing the turbomachine 10 with clearance control capability.
  • the controller 80 is operably coupled to the rotatable cam 60 and is configured to control operations of the rotatable cam 60. That is, the controller 80 could cause the rotatable cam 60 to rotate about the longitudinal axis 610 such that, at various operational conditions such as start-up conditions, turn-down conditions, transient conditions and base-load condition, the controlled amount of clearance between the blade 21 and the annular movable portion 43 has various predefined and/or appropriate values.
  • the controller 80 may be further configured to sense or otherwise measure current clearance amounts and, if such current clearance amounts are excessive or decreased given current operational conditions, to correct the current clearance amounts by selectively operating the rotatable cam 60 accordingly.
  • each rotatable cam 60 may each be operably coupled to the controller 80 and disposed circumferentially about the centerline 22. With such a configuration, each rotatable cam 60 may be jointly or separately operable based on current conditions.
  • a turbomachine 100 is provided with clearance control capability.
  • the turbomachine 100 includes several of the features mentioned above, which need not be described in detail again, such as the turbine stage 20, the blade 21 and the movable portion 43.
  • a rotatable cam 101 is operably disposed at a location that is axially adjacent to the movable portion 43 and is configured to urge the movable portion 43 against a bias of elastic element 102 by rotating about drive shaft 103.
  • the elastic element 102 may be a compression spring where the elastic element 102 is disposed on an opposite side of the movable portion 43 from the rotatable cam 101 or a tension spring in an opposite configuration. As shown in FIG.
  • an anti-rotation feature 104 may be disposed on a radially exterior surface of the movable portion 43 and a torsional spring 105 may be provided on the rotatable cam 101 to bias the movable portion 43 toward increased clearance to avoid rubbing in case of failure of control algorithms and systems.
  • the casing 40 and particularly the movable portion 43 may be configured to circumferentially surround at least one or more turbine stages.
  • the movable portion 43 may circumferentially surround first turbine stage 200 and second turbine stage 210.
  • the first and second turbine stages 200 and 210 may be disposed sequentially with respect to one another with the second turbine stage 210 downstream from the first turbine stage 200.
  • the first turbine stage 200 includes a stationary blade row (i.e., nozzles) 201 and a rotating blade row (i.e., buckets) 202 and the second turbine stage 210 includes a stationary blade row (i.e., nozzles) 211 and a rotating blade row (i.e., buckets) 212.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
EP13167700.7A 2012-05-22 2013-05-14 Strömungsmaschine mit Abstandssteuerungsfähigkeit Withdrawn EP2666971A1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US13/477,839 US20130315716A1 (en) 2012-05-22 2012-05-22 Turbomachine having clearance control capability and system therefor

Publications (1)

Publication Number Publication Date
EP2666971A1 true EP2666971A1 (de) 2013-11-27

Family

ID=48446123

Family Applications (1)

Application Number Title Priority Date Filing Date
EP13167700.7A Withdrawn EP2666971A1 (de) 2012-05-22 2013-05-14 Strömungsmaschine mit Abstandssteuerungsfähigkeit

Country Status (5)

Country Link
US (1) US20130315716A1 (de)
EP (1) EP2666971A1 (de)
JP (1) JP2013241932A (de)
CN (1) CN103422904A (de)
RU (1) RU2013123018A (de)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015094990A1 (en) * 2013-12-18 2015-06-25 Siemens Aktiengesellschaft Adjustable clearance control system for airfoil tip in gas turbine engine
US10221717B2 (en) 2016-05-06 2019-03-05 General Electric Company Turbomachine including clearance control system

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* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8973373B2 (en) * 2011-10-31 2015-03-10 General Electric Company Active clearance control system and method for gas turbine
US9970315B2 (en) * 2015-02-12 2018-05-15 Hamilton Sundstrand Corporation Movable vane control system
US10323536B2 (en) * 2015-04-09 2019-06-18 United Technologies Corporation Active clearance control for axial rotor systems
US10697241B2 (en) * 2015-10-28 2020-06-30 Halliburton Energy Services, Inc. Downhole turbine with an adjustable shroud
US11008882B2 (en) * 2019-04-18 2021-05-18 Rolls-Royce North American Technologies Inc. Blade tip clearance assembly
US11092030B2 (en) * 2019-04-18 2021-08-17 Raytheon Technologies Corporation Adaptive case for a gas turbine engine
DE112021003960T5 (de) * 2020-11-10 2023-05-11 Mitsubishi Heavy Industries, Ltd. Überwachungsvorrichtung, überwachungsprogramm undüberwachungsverfahren für rotationsmaschine sowierotationsmaschinenausrüstung
US11434777B2 (en) 2020-12-18 2022-09-06 General Electric Company Turbomachine clearance control using magnetically responsive particles
US20240018878A1 (en) * 2022-07-12 2024-01-18 General Electric Company Active clearance control of fan blade tip closure using a variable sleeve system

Citations (6)

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DE1178253B (de) * 1962-03-03 1964-09-17 Maschf Augsburg Nuernberg Ag Axial-durchstroemte Kreiselradmaschine mit einstellbarem Deckband
GB2042646A (en) * 1979-02-20 1980-09-24 Rolls Royce Rotor blade tip clearance control for gas turbine engine
US20020071763A1 (en) * 2000-12-07 2002-06-13 Herbert Brandl Device for setting the gap dimension for a turbomachine
DE10108559A1 (de) * 2001-02-22 2002-09-05 Alstom Switzerland Ltd Adaptive Spitzendichtung für eine axial durchströmte Turbomaschine
EP1243756A1 (de) * 2001-03-23 2002-09-25 Siemens Aktiengesellschaft Turbine
EP2487333A2 (de) * 2011-02-09 2012-08-15 Siemens Aktiengesellschaft Turbine mit relativ zueinander einstellbaren Rotor und Turbinengehäuse

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DE102008014743A1 (de) * 2008-03-18 2009-09-24 Rolls-Royce Deutschland Ltd & Co Kg Verdichterstator mit Teildeckband
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Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1178253B (de) * 1962-03-03 1964-09-17 Maschf Augsburg Nuernberg Ag Axial-durchstroemte Kreiselradmaschine mit einstellbarem Deckband
GB2042646A (en) * 1979-02-20 1980-09-24 Rolls Royce Rotor blade tip clearance control for gas turbine engine
US20020071763A1 (en) * 2000-12-07 2002-06-13 Herbert Brandl Device for setting the gap dimension for a turbomachine
DE10108559A1 (de) * 2001-02-22 2002-09-05 Alstom Switzerland Ltd Adaptive Spitzendichtung für eine axial durchströmte Turbomaschine
EP1243756A1 (de) * 2001-03-23 2002-09-25 Siemens Aktiengesellschaft Turbine
EP2487333A2 (de) * 2011-02-09 2012-08-15 Siemens Aktiengesellschaft Turbine mit relativ zueinander einstellbaren Rotor und Turbinengehäuse

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO2015094990A1 (en) * 2013-12-18 2015-06-25 Siemens Aktiengesellschaft Adjustable clearance control system for airfoil tip in gas turbine engine
US10221717B2 (en) 2016-05-06 2019-03-05 General Electric Company Turbomachine including clearance control system

Also Published As

Publication number Publication date
CN103422904A (zh) 2013-12-04
JP2013241932A (ja) 2013-12-05
US20130315716A1 (en) 2013-11-28
RU2013123018A (ru) 2014-11-27

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