US20060198726A1 - Apparatus for eliminating compressor stator vibration induced by tip leakage vortex bursting - Google Patents

Apparatus for eliminating compressor stator vibration induced by tip leakage vortex bursting Download PDF

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Publication number
US20060198726A1
US20060198726A1 US11/072,249 US7224905A US2006198726A1 US 20060198726 A1 US20060198726 A1 US 20060198726A1 US 7224905 A US7224905 A US 7224905A US 2006198726 A1 US2006198726 A1 US 2006198726A1
Authority
US
United States
Prior art keywords
stator
compressor
tip
tip leakage
blades
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
US11/072,249
Other languages
English (en)
Inventor
Steve Schirle
Robert Zacharias
James Cencula
Nicholas Martin
Thomas Tipton
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 US11/072,249 priority Critical patent/US20060198726A1/en
Assigned to GENERAL ELECTRIC COMPANY reassignment GENERAL ELECTRIC COMPANY ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: MARTIN, NICHOLAS, SCHIRLE, STEVE M., CENCULA, JAMES E., TIPTON, THOMAS R., ZACHARIAS, ROBERT M.
Priority to JP2006057059A priority patent/JP2006250147A/ja
Priority to EP06251185A priority patent/EP1707744A3/en
Priority to CNA2006100594378A priority patent/CN1831297A/zh
Publication of US20060198726A1 publication Critical patent/US20060198726A1/en
Priority to US12/155,101 priority patent/US20090123275A1/en
Abandoned legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/08—Sealings
    • F04D29/16—Sealings between pressure and suction sides
    • F04D29/161—Sealings between pressure and suction sides especially adapted for elastic fluid pumps
    • F04D29/164—Sealings between pressure and suction sides especially adapted for elastic fluid pumps of an axial flow wheel
    • 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
    • F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
    • F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • F01D5/143—Contour of the outer or inner working fluid flow path wall, i.e. shroud or hub contour
    • 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
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/60—Mounting; Assembling; Disassembling
    • F04D29/64—Mounting; Assembling; Disassembling of axial pumps
    • F04D29/644—Mounting; Assembling; Disassembling of axial pumps especially adapted for elastic fluid pumps

Definitions

  • the present invention relates to stator vanes in a compressor between inner and outer stationary components and particularly relates to apparatus for minimizing or eliminating tip leakage vortex bursting.
  • stator vanes are typically mounted on a fixed or stationary casing surrounding a compressor rotor mounting buckets.
  • air flowing into the compressor is compressed and heated for flow to various components of the turbine.
  • stator vanes fixed to the outer stationary component are cantilevered in a radial inward direction and have tips spaced from an inner stationary component.
  • These stator vanes at the aft end of the compressor are typically used to straighten the flow from the compressor.
  • a portion of the compressed air flows about the tip of the cantilevered stator vanes from the high pressure side to the low pressure side of each of vane, i.e.
  • a compressor comprising: inner and outer stationary casings; and a plurality of stator vanes extending between and secured at radially opposite ends to said inner and outer casings thereby eliminating tip leakage between opposite sides of each stator vane and stator vane vibration induced by tip leakage vortex bursting
  • a compressor comprising: a stator vane segment including a plurality of stator blades and inner and outer stationary shrouds about the blades eliminating tip leakage along the inner shroud and between opposite sides of the inner ends of the stator blades.
  • a compressor comprising: a stator vane segment including a plurality of stator blades and a radial outer shroud, a stationary inner casing spaced from a tip of the stator blades and having a contoured surface exposed to the flow path for converging the flow in a downstream direction.
  • FIG. 1 is a fragmentary schematic cross-sectional illustration of a compressor and turbine
  • FIG. 2 is a fragmentary cross-sectional view of a configuration of a compressor at the aft end of the compressor according to the prior art
  • FIG. 3 is a fragmentary cross-sectional view illustrating a stator vane between stationary components according to an aspect of the present invention
  • FIG. 4 is a view similar to FIG. 3 illustrating a further aspect of the present invention.
  • FIG. 5 is a perspective view of a compressor vane segment according to an aspect of the present invention.
  • FIG. 6 is a view similar to FIG. 4 illustrating a further aspect of the present invention.
  • FIG. 1 there is illustrated a compressor section generally designated 10 and a turbine section generally designated 12 .
  • the compressor 10 compresses and heats air for use by various portions of the turbine 12 .
  • one of a plurality of combustor cans 14 wherein a portion of the compressed air from compressor section 10 is mixed with fuel and combusted for flow into the various stages of the turbine 12 .
  • the turbine converts the pressurized heated combusted gases into mechanical rotational energy whereby the rotation of the turbine rotor can perform useful work, e.g., when coupled to a generator to generate electricity. A portion of that generated work is used to rotate the rotor 16 of the compressor 10 to initially compress the air supplied to the turbine.
  • the rotor 16 of the compressor mounts a plurality of buckets 18 for rotation therewith and a plurality of stator vanes 20 fixed to the outer casing 22 of the compressor.
  • At the aft end of the compressor there are one or more arrays of stator blades 24 cantilevered from and fixed to the outer casing 22 .
  • the stator vanes 24 cantilevered between the stationary outer casing 22 and the stationary inner casing 26 have tips which are closely spaced from the inner casing 26 as illustrated in FIG. 2 .
  • the gap between the tips and the inner casing 26 permit flow from the high pressure concave sides of the stator vanes 24 to the low pressure convex sides of the stator vanes 24 causing the formation of vortices.
  • These vortices have been found to have a back and forth frequency component which under certain aerodynamic conditions may reinforce the natural frequency of the stator vanes 24 . Should this occur, there is an enhanced possibility that the stator vanes can fail.
  • stator vane 40 comprising one of a plurality of stator blades or vanes in an annular array of such vanes about the axis of the compressor.
  • the vanes 40 are disposed between the outer fixed stationary casing 42 and an inner fixed cylindrical casing 44 .
  • the opposite ends of the stator vanes are fixed to the casings 42 and 44 , respectively. Consequently, the gap between the tip of the stator vane and the stationary inner casing illustrated in FIG. 2 is closed. This prevents the formation of vortices resulting from passage of air between opposite sides of each vane about the tip of the vane and hence entirely eliminates vortex bursting and potential resultant sympathetic vibration.
  • the vanes 46 extend between a fixed outer casing 48 and a fixed inner part 50 .
  • Each vane 46 may comprise one of a plurality of vanes of a compressor vane segment generally designated 52 in FIG. 5 .
  • the segment 52 includes an outer shroud or band 54 and an inner shroud or band 56 .
  • the vanes 46 extend between the two bands 54 and 56 .
  • Each segment 52 may comprise any number of vanes dependent upon the total blade count in the stage. Consequently, and referring back to FIG. 4 , the segment 52 is secured to the outer casing 48 with the vanes and inner band 56 cantilevered from the outer casing 48 .
  • the radial outer surface of the inner band 56 is preferably contoured. That is, the radially outer surface 58 of the inner band 56 converges in a radial outward and downstream direction relative to the flowpath of the compressed air defined between the outer and inner casings.
  • each stator vane 46 may be fixed to both the outer and inner bands and hence tip leakage is avoided thereby also eliminating the excitation source, i.e., the tip leakage vortex, it is also possible to minimize the occurrence of stator vane tip leakage vortex vibration induced vane failure notwithstanding a gap between tips of cantilevered stator vanes and the opposed inner casing. That is, the stator vanes 46 can remain cantilevered with tips spaced from the inner casing provided the inner casing is contoured to preclude lift off of the tip leakage vortex.
  • the inner casing 60 has an inner flow surface 62 shaped to converge the flow in a radial outward and downstream direction. The flow convergence prevents lift off of the tip leakage vortex notwithstanding that the tip of stator blade 64 is spaced from casing 60 . This minimizes the excitation source which otherwise may potentially cause stator blade failure.
US11/072,249 2005-03-07 2005-03-07 Apparatus for eliminating compressor stator vibration induced by tip leakage vortex bursting Abandoned US20060198726A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US11/072,249 US20060198726A1 (en) 2005-03-07 2005-03-07 Apparatus for eliminating compressor stator vibration induced by tip leakage vortex bursting
JP2006057059A JP2006250147A (ja) 2005-03-07 2006-03-03 圧縮機
EP06251185A EP1707744A3 (en) 2005-03-07 2006-03-06 Stator vane with inner and outer shroud
CNA2006100594378A CN1831297A (zh) 2005-03-07 2006-03-07 用于消除由端部泄漏涡流爆发诱发的压缩机定子振动的设备
US12/155,101 US20090123275A1 (en) 2005-03-07 2008-05-29 Apparatus for eliminating compressor stator vibration induced by TIP leakage vortex bursting

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/072,249 US20060198726A1 (en) 2005-03-07 2005-03-07 Apparatus for eliminating compressor stator vibration induced by tip leakage vortex bursting

Related Child Applications (1)

Application Number Title Priority Date Filing Date
US12/155,101 Continuation US20090123275A1 (en) 2005-03-07 2008-05-29 Apparatus for eliminating compressor stator vibration induced by TIP leakage vortex bursting

Publications (1)

Publication Number Publication Date
US20060198726A1 true US20060198726A1 (en) 2006-09-07

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Family Applications (2)

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US11/072,249 Abandoned US20060198726A1 (en) 2005-03-07 2005-03-07 Apparatus for eliminating compressor stator vibration induced by tip leakage vortex bursting
US12/155,101 Abandoned US20090123275A1 (en) 2005-03-07 2008-05-29 Apparatus for eliminating compressor stator vibration induced by TIP leakage vortex bursting

Family Applications After (1)

Application Number Title Priority Date Filing Date
US12/155,101 Abandoned US20090123275A1 (en) 2005-03-07 2008-05-29 Apparatus for eliminating compressor stator vibration induced by TIP leakage vortex bursting

Country Status (4)

Country Link
US (2) US20060198726A1 (ja)
EP (1) EP1707744A3 (ja)
JP (1) JP2006250147A (ja)
CN (1) CN1831297A (ja)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070079506A1 (en) * 2005-10-06 2007-04-12 General Electric Company Method of providing non-uniform stator vane spacing in a compressor
US20110236195A1 (en) * 2010-03-29 2011-09-29 Hitachi, Ltd. Compressor
US20130142640A1 (en) * 2011-12-02 2013-06-06 David P. Houston Alternate shroud width to provide mistuning on compressor stator clusters
US9115594B2 (en) 2010-12-28 2015-08-25 Rolls-Royce Corporation Compressor casing treatment for gas turbine engine
US20220381150A1 (en) * 2021-05-26 2022-12-01 General Electric Company Split-line stator vane assembly

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2218918A1 (de) * 2009-02-13 2010-08-18 Siemens Aktiengesellschaft Axialturboverdichter für eine Gasturbine mit geringen Spaltverlusten und Diffusorverlusten
EP2218876A1 (de) * 2009-02-16 2010-08-18 Siemens Aktiengesellschaft Dichtungsring zum Abdichten eines Radialspalts in einer Gasturbine
JP5192507B2 (ja) 2010-03-19 2013-05-08 川崎重工業株式会社 ガスタービンエンジン
JP5342579B2 (ja) 2011-02-28 2013-11-13 三菱重工業株式会社 回転機械の静翼ユニット、回転機械の静翼ユニットの製造方法及び回転機械の静翼ユニットの結合方法
US20180080454A1 (en) * 2016-09-16 2018-03-22 United Technologies Corporation Segmented stator vane

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US3265290A (en) * 1964-09-01 1966-08-09 Anthony J Cali Axial flow compressors for jet engines
US4022540A (en) * 1975-10-02 1977-05-10 General Electric Company Frangible airfoil structure
US5639212A (en) * 1996-03-29 1997-06-17 General Electric Company Cavity sealed compressor

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US3300121A (en) * 1965-02-24 1967-01-24 Gen Motors Corp Axial-flow compressor
US3861823A (en) * 1973-01-15 1975-01-21 Caterpillar Tractor Co Compressor with retractable guide vanes
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US6312219B1 (en) * 1999-11-05 2001-11-06 General Electric Company Narrow waist vane
US6338609B1 (en) * 2000-02-18 2002-01-15 General Electric Company Convex compressor casing
DE10355240A1 (de) * 2003-11-26 2005-07-07 Rolls-Royce Deutschland Ltd & Co Kg Strömungsarbeitsmaschine mit Fluidentnahme
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Publication number Priority date Publication date Assignee Title
US3265290A (en) * 1964-09-01 1966-08-09 Anthony J Cali Axial flow compressors for jet engines
US4022540A (en) * 1975-10-02 1977-05-10 General Electric Company Frangible airfoil structure
US5639212A (en) * 1996-03-29 1997-06-17 General Electric Company Cavity sealed compressor

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20070079506A1 (en) * 2005-10-06 2007-04-12 General Electric Company Method of providing non-uniform stator vane spacing in a compressor
US7743497B2 (en) * 2005-10-06 2010-06-29 General Electric Company Method of providing non-uniform stator vane spacing in a compressor
US20110236195A1 (en) * 2010-03-29 2011-09-29 Hitachi, Ltd. Compressor
US9534613B2 (en) 2010-03-29 2017-01-03 Mitsubishi Hitachi Power Systems, Ltd. Compressor
US9115594B2 (en) 2010-12-28 2015-08-25 Rolls-Royce Corporation Compressor casing treatment for gas turbine engine
US20130142640A1 (en) * 2011-12-02 2013-06-06 David P. Houston Alternate shroud width to provide mistuning on compressor stator clusters
US20220381150A1 (en) * 2021-05-26 2022-12-01 General Electric Company Split-line stator vane assembly
US11629606B2 (en) * 2021-05-26 2023-04-18 General Electric Company Split-line stator vane assembly

Also Published As

Publication number Publication date
EP1707744A3 (en) 2009-05-27
US20090123275A1 (en) 2009-05-14
CN1831297A (zh) 2006-09-13
EP1707744A2 (en) 2006-10-04
JP2006250147A (ja) 2006-09-21

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AS Assignment

Owner name: GENERAL ELECTRIC COMPANY, NEW YORK

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNORS:SCHIRLE, STEVE M.;ZACHARIAS, ROBERT M.;CENCULA, JAMES E.;AND OTHERS;REEL/FRAME:016358/0894;SIGNING DATES FROM 20041217 TO 20050214

STCB Information on status: application discontinuation

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