US20070237629A1 - Gas turbine compressor casing flowpath rings - Google Patents

Gas turbine compressor casing flowpath rings Download PDF

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Publication number
US20070237629A1
US20070237629A1 US11/397,560 US39756006A US2007237629A1 US 20070237629 A1 US20070237629 A1 US 20070237629A1 US 39756006 A US39756006 A US 39756006A US 2007237629 A1 US2007237629 A1 US 2007237629A1
Authority
US
United States
Prior art keywords
flowpath
ring
compressor
rings
casing
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.)
Abandoned
Application number
US11/397,560
Other languages
English (en)
Inventor
Jeff Moree
Nicholas Poccia
Lynn Gagne
Raymond Goetze
David Johnson
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
Priority to US11/397,560 priority Critical patent/US20070237629A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: GAGNE, LYNN C., GOETZE, RAYMOND H., JOHNSON, DAVID MARTIN, MOREE, JEFF, POCCIA, NICHOLAS P.
Priority to JP2007097669A priority patent/JP2007278287A/ja
Priority to KR1020070033267A priority patent/KR20070100133A/ko
Priority to EP07105674A priority patent/EP1843010A2/fr
Priority to CNA200710089872XA priority patent/CN101050774A/zh
Publication of US20070237629A1 publication Critical patent/US20070237629A1/en
Abandoned 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
    • 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
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/11—Shroud seal segments

Definitions

  • the present invention relates to compressor rotors and stator casings and, more particularly, to rings set in dedicated grooves in the stator casing that define the outer flowpath and that can be easily replaced in the event of rotor airfoil tip rubbing.
  • gas turbines attain optimum performance when the clearance 22 between rotating blades 20 and the casing 12 is maintained at an optimal distance, which is generally very small, e.g., 40-80 mils at steady state temperatures.
  • This clearance must be made large enough, however, to account for part stack up tolerance, mechanical and thermal growth differences between the casing 12 and the rotating airfoil 20 .
  • a common occurrence in gas turbine compressors is rotor blades rubbing on compressor casings for various reasons. Rubbing can be caused by a number of conditions such as improper alignment between the rotor 18 and the casing, casing joint slippage at the horizontal and vertical flanges, or transient thermal response differences between the casing 12 and rotating parts.
  • the end result is airfoil 20 tip loss and/or casing flowpath wear. These conditions lead to a loss of compressor performance and surge margin. If rubs are severe enough, the casing and rotating airfoils have to be replaced. Typically, this will result in loss of service of the gas turbine for an extended period of time.
  • a flowpath ring is securable in a machined groove of a compressor stator casing.
  • the flowpath ring includes a connector section engageable with the machined groove where the connector section is shaped corresponding to the machined groove.
  • a flowpath section is disposed radially inward relative to the connector section and includes a clearance surface disposed facing a compressor rotor blade and defining a blade flowpath when secured in the compressor stator casing machined groove.
  • a gas turbine compressor in an another exemplary embodiment of the invention, includes a stator casing having airfoil grooves each supporting a plurality of stator airfoils.
  • a rotor supports a plurality of rotor blades for rotation relative to the stator casing.
  • a plurality of the noted flowpath rings are secured in respective ring grooves in the stator casing.
  • FIG. 1 is a cross-sectional view of a typical gas turbine compressor
  • FIG. 2 shows the machined stator casing including ring grooves between the stator grooves
  • FIG. 3 shows flowpath rings secured in the stator ring grooves
  • FIG. 4 illustrates the flowpath rings including air gap insulators
  • FIG. 5 shows the flowpath ring including seals to minimize back side leakage.
  • replaceable rings By utilizing easily replaceable rings installed in the casing where the rotor blades may rub the casing, flowpath repairs can be effected rapidly and efficiently. Additionally, replaceable rings (or flowpath rings) can reduce the rate of heat transfer into the casing, thereby changing the transient and steady state matching of the rotor and casing thermal growth. This allows for a passive clearance controlling design feature that permits tighter clearances between the rotor blades and the casing, adding to overall engine performance and surge margins.
  • a gas turbine includes a stator casing 12 having a plurality of airfoil grooves 14 machined therein as is conventional.
  • the airfoil grooves 14 are formed generally continuously in the inside circumference of the stator casing 12 .
  • the airfoil grooves 14 each support a plurality of stator airfoils 16 as is also conventional.
  • a rotor 18 supports a plurality of rotor blades 20 for rotation relative to the stator casing 12 .
  • gas turbines attain optimum performance when the clearance, designated by reference numeral 22 , between rotating airfoils and the stator casing 12 is maintained at an optimal distance, which is generally very small (e.g., 40-80 mils at steady state temperature).
  • a common occurrence during the operation of a gas turbine compressor is rubbing or contact between tips of the rotor blades 20 and the stator casing 12 .
  • the end result is rotor tip loss and/or casing flowpath wear, which can lead to a loss of compressor performance and surge margin.
  • the stator casing 12 and rotor blades 20 may require replacement, resulting in loss of service of the turbine for an extended period of time.
  • the stator casing 12 is machined with additional grooves 24 preferably interposed between adjacent ones of the airfoil grooves 14 .
  • the machining process for forming the ring grooves 24 is very similar to the conventional process conducted in machining the stator airfoil grooves 14 , and details of the manufacturing/machining process will not be described.
  • a plurality of flowpath rings 26 are secured in respective ring grooves 24 in the stator casing 12 .
  • the flowpath rings 26 include a connector section 28 shaped corresponding to the machined groove 24 and a flowpath section 30 disposed radially inward relative to the casing 12 (i.e., toward the rotor 18 ).
  • the flowpath section 30 includes a clearance surface 32 disposed facing the turbine rotor blades 20 and defining a blade flowpath when the flowpath rings 26 are secured in the stator casing 12 .
  • the flowpath rings 26 are each formed of a plurality of ring segments to minimize binding in the groove 24 .
  • the flowpath rings 26 can be used to optimize tip clearance by using an abradable coating 34 formed on the clearance surface 32 of the flowpath rings 26 .
  • the clearance surface 32 includes a groove 36 or the like in which the abradable coating 34 is disposed.
  • abradable coatings that can be used for this application are aluminium silicon alloy/polymer composite, nickel/graphite composite, aluminium bronze/polymer composites.
  • the flowpath rings 26 may additionally include at least one air gap insulator 38 formed on a casing side surface as shown.
  • the air gap insulators 38 are preferably machined as a groove in the casing side surface.
  • An optimum air gap on the casing side of the flowpath rings 26 can serve to insulate the casing 12 from the rapid transient response of the flowpath temperature.
  • the air gap insulators 38 control heat transfer between the flowpath rings 26 and the casing 12 to thereby control the rate of heating or cooling of the casing 12 in response to temperature changes in the flowpath.
  • Increases to the air gap insulator 38 thickness and decreases in the surface area of the points of contact will reduce the rate of heat transfer and thus reduce the casing thermal responsiveness.
  • a seal 40 ( FIG. 5 ) may be interposed between the casing side surface of the rings 26 and the stator casing 12 .
  • an additional groove or notch 42 may be formed in the casing side surface of the ring flowpath section 30 to accommodate the seal 40 .
  • the seal 40 is formed of a metallic wire/rope or other suitable material.
  • the flowpath rings are replaceable, flowpath repairs due to rotor blade tip rubbing can be quickly facilitated in a reliable and cost effective manner. Thus, even on units with heavy rubbing, original performance and compressor surge margin can be restored. Moreover, the cycle time and associated cost to replace the flowpath rings is considerably less than to replace casings. Additionally, the flowpath rings 26 allow for a better thermal match between rotors and compressor casings, allowing a designer to better match the thermal responses and thereby run with tighter clearances. As noted, the compressor casing flowpath rings can be coated with an abradable material to allow closer clearances and an improvement in compressor performance.
  • the flowpath rings can be installed in new units as a performance enhancement feature, particularly if combined with abradable coatings. Since the flowpath ring grooves can be machined into a stator casing in the same manner as stator slots with similar tolerance control, the flowpath rings can be accommodated with minimal cost and cycle impact on the casing.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
US11/397,560 2006-04-05 2006-04-05 Gas turbine compressor casing flowpath rings Abandoned US20070237629A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US11/397,560 US20070237629A1 (en) 2006-04-05 2006-04-05 Gas turbine compressor casing flowpath rings
JP2007097669A JP2007278287A (ja) 2006-04-05 2007-04-03 ガスタービン圧縮機ケーシングの流路リング及びステータケーシングの組立方法
KR1020070033267A KR20070100133A (ko) 2006-04-05 2007-04-04 압축기 고정자 케이싱의 유동 경로 링 및 고정자 케이싱의고정 방법
EP07105674A EP1843010A2 (fr) 2006-04-05 2007-04-04 Anneaux de paroi de canal d'un compresseur d'une turbine à gaz
CNA200710089872XA CN101050774A (zh) 2006-04-05 2007-04-05 燃气轮机压缩机壳体的流路环

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/397,560 US20070237629A1 (en) 2006-04-05 2006-04-05 Gas turbine compressor casing flowpath rings

Publications (1)

Publication Number Publication Date
US20070237629A1 true US20070237629A1 (en) 2007-10-11

Family

ID=38050207

Family Applications (1)

Application Number Title Priority Date Filing Date
US11/397,560 Abandoned US20070237629A1 (en) 2006-04-05 2006-04-05 Gas turbine compressor casing flowpath rings

Country Status (5)

Country Link
US (1) US20070237629A1 (fr)
EP (1) EP1843010A2 (fr)
JP (1) JP2007278287A (fr)
KR (1) KR20070100133A (fr)
CN (1) CN101050774A (fr)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8602720B2 (en) 2010-06-22 2013-12-10 Honeywell International Inc. Compressors with casing treatments in gas turbine engines
US20140003926A1 (en) * 2012-06-28 2014-01-02 Alstom Technology Ltd Compressor for a gas turbine and method for repairing and/or changing the geometry of and/or servicing said compressor

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US9643286B2 (en) * 2007-04-05 2017-05-09 United Technologies Corporation Method of repairing a turbine engine component
EP2075416B1 (fr) * 2007-12-27 2011-05-18 Techspace Aero Procédé de fabrication d'un élément de turbomachine et dispositif ainsi obtenu
US8092168B2 (en) * 2009-04-10 2012-01-10 General Electric Company Patch plug repair of a compressor case stator ring hook, near the horizontal joint
JP4916560B2 (ja) * 2010-03-26 2012-04-11 川崎重工業株式会社 ガスタービンエンジンの圧縮機
US20110299977A1 (en) * 2010-06-03 2011-12-08 General Electric Company Patch ring segment for a turbomachine compressor
US8529210B2 (en) * 2010-12-21 2013-09-10 Hamilton Sundstrand Corporation Air cycle machine compressor rotor
CN102102544B (zh) * 2011-03-11 2013-10-02 北京华清燃气轮机与煤气化联合循环工程技术有限公司 燃气轮机的涡轮转子叶片
CN102102543B (zh) * 2011-03-11 2013-05-15 北京华清燃气轮机与煤气化联合循环工程技术有限公司 燃气轮机的涡轮转子叶片
US9121301B2 (en) * 2012-03-20 2015-09-01 General Electric Company Thermal isolation apparatus
FR3011033B1 (fr) * 2013-09-25 2018-02-02 Safran Aircraft Engines Fixation de secteurs abradables maintenus par glissiere
CN112160933B (zh) * 2020-10-19 2022-06-14 杭州汽轮动力集团有限公司 轴流压气机可拆卸式叶尖密封环及安装方法
CN114017134A (zh) * 2021-11-12 2022-02-08 中国航发沈阳发动机研究所 一种通过改变机匣热容调整机匣热变形速率的方法

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Publication number Priority date Publication date Assignee Title
US994029A (en) * 1907-08-12 1911-05-30 Charles Algernon Parsons Strips for turbine-blades.
US3689174A (en) * 1971-01-11 1972-09-05 Westinghouse Electric Corp Axial flow turbine structure
US3849023A (en) * 1973-06-28 1974-11-19 Gen Electric Stator assembly
US4411594A (en) * 1979-06-30 1983-10-25 Rolls-Royce Limited Support member and a component supported thereby
US4422648A (en) * 1982-06-17 1983-12-27 United Technologies Corporation Ceramic faced outer air seal for gas turbine engines
US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
US4543039A (en) * 1982-11-08 1985-09-24 Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Stator assembly for an axial compressor
US5088775A (en) * 1990-07-27 1992-02-18 General Electric Company Seal ring with flanged end portions
US5685693A (en) * 1995-03-31 1997-11-11 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US5809772A (en) * 1996-03-29 1998-09-22 General Electric Company Turbofan engine with a core driven supercharged bypass duct
US6065756A (en) * 1997-12-10 2000-05-23 General Electric Co. Flex seal for gas turbine expansion joints
US6382632B1 (en) * 2001-02-21 2002-05-07 General Electric Company Repositionable brush seal for turbomachinery
US6450763B1 (en) * 2000-11-17 2002-09-17 General Electric Company Replaceable variable stator vane for gas turbines
US6467339B1 (en) * 2000-07-13 2002-10-22 United Technologies Corporation Method for deploying shroud segments in a turbine engine
US6602050B1 (en) * 1999-03-24 2003-08-05 Siemens Aktiengesellschaft Covering element and arrangement with a covering element and a support structure
US6609886B2 (en) * 2001-12-28 2003-08-26 General Electric Company Composite tubular woven seal for gas turbine nozzle and shroud interface
US6652227B2 (en) * 2001-04-28 2003-11-25 Alstom (Switzerland) Ltd. Gas turbine seal
US6659472B2 (en) * 2001-12-28 2003-12-09 General Electric Company Seal for gas turbine nozzle and shroud interface
US6685425B2 (en) * 2002-06-26 2004-02-03 General Electric Company Inlet bleed heater for heating inlet air to a compressor and methods of fabricating and transporting the heater
US6792691B2 (en) * 2002-11-12 2004-09-21 General Electric Company Gage for milled blade ring segments
US6807803B2 (en) * 2002-12-06 2004-10-26 General Electric Company Gas turbine exhaust diffuser
US6997673B2 (en) * 2003-12-11 2006-02-14 Honeywell International, Inc. Gas turbine high temperature turbine blade outer air seal assembly

Patent Citations (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US994029A (en) * 1907-08-12 1911-05-30 Charles Algernon Parsons Strips for turbine-blades.
US3689174A (en) * 1971-01-11 1972-09-05 Westinghouse Electric Corp Axial flow turbine structure
US3849023A (en) * 1973-06-28 1974-11-19 Gen Electric Stator assembly
US4411594A (en) * 1979-06-30 1983-10-25 Rolls-Royce Limited Support member and a component supported thereby
US4522559A (en) * 1982-02-19 1985-06-11 General Electric Company Compressor casing
US4422648A (en) * 1982-06-17 1983-12-27 United Technologies Corporation Ceramic faced outer air seal for gas turbine engines
US4543039A (en) * 1982-11-08 1985-09-24 Societe National D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." Stator assembly for an axial compressor
US5088775A (en) * 1990-07-27 1992-02-18 General Electric Company Seal ring with flanged end portions
US5913658A (en) * 1995-03-31 1999-06-22 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US5906473A (en) * 1995-03-31 1999-05-25 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US5685693A (en) * 1995-03-31 1997-11-11 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US6079943A (en) * 1995-03-31 2000-06-27 General Electric Co. Removable inner turbine shell and bucket tip clearance control
US6082963A (en) * 1995-03-31 2000-07-04 General Electric Co. Removable inner turbine shell with bucket tip clearance control
US5779442A (en) * 1995-03-31 1998-07-14 General Electric Company Removable inner turbine shell with bucket tip clearance control
US5809772A (en) * 1996-03-29 1998-09-22 General Electric Company Turbofan engine with a core driven supercharged bypass duct
US6065756A (en) * 1997-12-10 2000-05-23 General Electric Co. Flex seal for gas turbine expansion joints
US6602050B1 (en) * 1999-03-24 2003-08-05 Siemens Aktiengesellschaft Covering element and arrangement with a covering element and a support structure
US6467339B1 (en) * 2000-07-13 2002-10-22 United Technologies Corporation Method for deploying shroud segments in a turbine engine
US6450763B1 (en) * 2000-11-17 2002-09-17 General Electric Company Replaceable variable stator vane for gas turbines
US6382632B1 (en) * 2001-02-21 2002-05-07 General Electric Company Repositionable brush seal for turbomachinery
US6652227B2 (en) * 2001-04-28 2003-11-25 Alstom (Switzerland) Ltd. Gas turbine seal
US6609886B2 (en) * 2001-12-28 2003-08-26 General Electric Company Composite tubular woven seal for gas turbine nozzle and shroud interface
US6659472B2 (en) * 2001-12-28 2003-12-09 General Electric Company Seal for gas turbine nozzle and shroud interface
US6685425B2 (en) * 2002-06-26 2004-02-03 General Electric Company Inlet bleed heater for heating inlet air to a compressor and methods of fabricating and transporting the heater
US6792691B2 (en) * 2002-11-12 2004-09-21 General Electric Company Gage for milled blade ring segments
US6807803B2 (en) * 2002-12-06 2004-10-26 General Electric Company Gas turbine exhaust diffuser
US6997673B2 (en) * 2003-12-11 2006-02-14 Honeywell International, Inc. Gas turbine high temperature turbine blade outer air seal assembly

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8602720B2 (en) 2010-06-22 2013-12-10 Honeywell International Inc. Compressors with casing treatments in gas turbine engines
US20140003926A1 (en) * 2012-06-28 2014-01-02 Alstom Technology Ltd Compressor for a gas turbine and method for repairing and/or changing the geometry of and/or servicing said compressor

Also Published As

Publication number Publication date
CN101050774A (zh) 2007-10-10
JP2007278287A (ja) 2007-10-25
EP1843010A2 (fr) 2007-10-10
KR20070100133A (ko) 2007-10-10

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Legal Events

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AS Assignment

Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:MOREE, JEFF;POCCIA, NICHOLAS P.;GAGNE, LYNN C.;AND OTHERS;REEL/FRAME:017761/0340;SIGNING DATES FROM 20060328 TO 20060330

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION