EP1707744A2 - Statorschaufel mit innerem und äusserem Deckband - Google Patents

Statorschaufel mit innerem und äusserem Deckband Download PDF

Info

Publication number
EP1707744A2
EP1707744A2 EP06251185A EP06251185A EP1707744A2 EP 1707744 A2 EP1707744 A2 EP 1707744A2 EP 06251185 A EP06251185 A EP 06251185A EP 06251185 A EP06251185 A EP 06251185A EP 1707744 A2 EP1707744 A2 EP 1707744A2
Authority
EP
European Patent Office
Prior art keywords
stator
compressor
vane
blades
tip
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Withdrawn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
EP06251185A
Other languages
English (en)
French (fr)
Other versions
EP1707744A3 (de
Inventor
Steve Mark Schirle
Robert M. Zacharias
James Edward Cencula
Nicholas F. Martin
Thomas R. 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
Publication of EP1707744A2 publication Critical patent/EP1707744A2/de
Publication of EP1707744A3 publication Critical patent/EP1707744A3/de
Withdrawn legal-status Critical Current

Links

Images

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 there is illustrated a compressor section generally designated 10 and a turbine section generally designated 12. It will be appreciated that the compressor 10 compresses and heats air for use by various portions of the turbine 12. Also illustrated is 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 Figure 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 Figure 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 Figure 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 Figure 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.
EP06251185A 2005-03-07 2006-03-06 Statorschaufel mit innerem und äusserem Deckband Withdrawn EP1707744A3 (de)

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

Publications (2)

Publication Number Publication Date
EP1707744A2 true EP1707744A2 (de) 2006-10-04
EP1707744A3 EP1707744A3 (de) 2009-05-27

Family

ID=36570747

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06251185A Withdrawn EP1707744A3 (de) 2005-03-07 2006-03-06 Statorschaufel mit innerem und äusserem Deckband

Country Status (4)

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

Cited By (3)

* 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
EP3296516A1 (de) * 2016-09-16 2018-03-21 United Technologies Corporation Segmentierte statorschaufel

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7743497B2 (en) * 2005-10-06 2010-06-29 General Electric Company Method of providing non-uniform stator vane spacing in a compressor
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
JP5147886B2 (ja) * 2010-03-29 2013-02-20 株式会社日立製作所 圧縮機
US9115594B2 (en) 2010-12-28 2015-08-25 Rolls-Royce Corporation Compressor casing treatment for gas turbine engine
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
US20130142640A1 (en) * 2011-12-02 2013-06-06 David P. Houston Alternate shroud width to provide mistuning on compressor stator clusters
US11629606B2 (en) * 2021-05-26 2023-04-18 General Electric Company Split-line stator vane assembly

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1098092A2 (de) * 1999-11-05 2001-05-09 General Electric Company Leitschaufel

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2556161A (en) * 1944-03-21 1951-06-12 Power Jets Res & Dev Ltd Gas diffusers for air supplied to combustion chambers
US2693904A (en) * 1950-11-14 1954-11-09 A V Roe Canada Ltd Air bleed for compressors
US3265290A (en) * 1964-09-01 1966-08-09 Anthony J Cali Axial flow compressors for jet engines
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
CH579218A5 (de) * 1974-06-17 1976-08-31 Bbc Sulzer Turbomaschinen
US4022540A (en) * 1975-10-02 1977-05-10 General Electric Company Frangible airfoil structure
US4011028A (en) * 1975-10-16 1977-03-08 Anatoly Nikolaevich Borsuk Axial-flow transsonic compressor
US4008978A (en) * 1976-03-19 1977-02-22 General Motors Corporation Ceramic turbine structures
US4503668A (en) * 1983-04-12 1985-03-12 The United States Of America As Represented By The Secretary Of The Air Force Strutless diffuser for gas turbine engine
US5127797A (en) * 1990-09-12 1992-07-07 United Technologies Corporation Compressor case attachment means
US5333995A (en) * 1993-08-09 1994-08-02 General Electric Company Wear shim for a turbine engine
US5681142A (en) * 1993-12-20 1997-10-28 United Technologies Corporation Damping means for a stator assembly of a gas turbine engine
US5697208A (en) * 1995-06-02 1997-12-16 Solar Turbines Incorporated Turbine cooling cycle
US5639212A (en) * 1996-03-29 1997-06-17 General Electric Company Cavity sealed compressor
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
JP4328269B2 (ja) * 2004-07-28 2009-09-09 株式会社日立製作所 ガスタービン装置

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1098092A2 (de) * 1999-11-05 2001-05-09 General Electric Company Leitschaufel

Cited By (6)

* 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
WO2010091956A1 (de) * 2009-02-13 2010-08-19 Siemens Aktiengesellschaft Axialturboverdichter für eine gasturbine mit geringen radialspaltverlusten und diffusorverlusten
CN102317634A (zh) * 2009-02-13 2012-01-11 西门子公司 具有低的径向间隙损失和扩压器损失的用于燃气轮机的轴流式涡轮压缩机
CN102317634B (zh) * 2009-02-13 2014-06-25 西门子公司 具有低的径向间隙损失和扩压器损失的用于燃气轮机的轴流式涡轮压缩机
EP2218876A1 (de) * 2009-02-16 2010-08-18 Siemens Aktiengesellschaft Dichtungsring zum Abdichten eines Radialspalts in einer Gasturbine
EP3296516A1 (de) * 2016-09-16 2018-03-21 United Technologies Corporation Segmentierte statorschaufel

Also Published As

Publication number Publication date
US20090123275A1 (en) 2009-05-14
JP2006250147A (ja) 2006-09-21
US20060198726A1 (en) 2006-09-07
CN1831297A (zh) 2006-09-13
EP1707744A3 (de) 2009-05-27

Similar Documents

Publication Publication Date Title
US20090123275A1 (en) Apparatus for eliminating compressor stator vibration induced by TIP leakage vortex bursting
JP3776957B2 (ja) コンプレッサブレード用鋳造体鋳造処理
JP4482732B2 (ja) ガスタービンエンジンを組立てるための方法及び装置
US7118331B2 (en) Stator vane assembly for a turbomachine
EP2230382B1 (de) Gasturbinenrotorstufe
EP2650476B1 (de) Turbomaschinenschaufelspitzendeckband mit paralleler Gehäusekonfiguration
US10690146B2 (en) Turbofan nacelle assembly with flow disruptor
EP2518326A2 (de) Zentrifugalkompressoranordnung mit Leitschaufelreihe
EP2204533A2 (de) Verfahren, Systeme und/oder Vorrichtungen in Bezug auf Drallvorrichtungen für Turbinenantriebe
EP2613013B1 (de) Stufe und Turbine eines Gasturbinenkraftwerks
EP2586979B1 (de) Turbomaschinenschaufel mit ausgestellter Schaufelspitze
US20150176413A1 (en) Snubber configurations for turbine rotor blades
JP2006283755A (ja) 固定タービン翼形部
JP6780713B2 (ja) 軸流機械の翼
US10526899B2 (en) Turbine blade having a tip shroud
JP2017110642A (ja) ガスタービンエンジンの間隙の制御のコンプライアントなシュラウド
US10876416B2 (en) Vane segment with ribs
EP3299587B1 (de) Gasturbinenmotorschaufel
US11629722B2 (en) Impeller shroud frequency tuning rib
EP4170178A1 (de) Zentrifugalverdichter mit einer glockenmund mit versteifungselement
EP2126367B1 (de) Mehrstufiger turbogassystemverdichter
EP3901412A1 (de) Ummantelungsskonfigurationen mit dämpfern
GB2564366A (en) Air flow rectification assembly and turbomachine comprising an assembly of this type
WO2022051760A1 (en) Guide vane in gas turbine engine
CN114320481A (zh) 具有双部分跨度护罩和空气动力学特征的涡轮机桨叶

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

RIN1 Information on inventor provided before grant (corrected)

Inventor name: TIPTON, THOMAS R.

Inventor name: MARTIN, NICHOLAS F.

Inventor name: CENCULA, JAMES EDWARD

Inventor name: ZACHARIAS, ROBERT M.

Inventor name: SCHIRLE, STEVE MARK

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: GENERAL ELECTRIC COMPANY

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

17P Request for examination filed

Effective date: 20091127

17Q First examination report despatched

Effective date: 20091228

AKX Designation fees paid

Designated state(s): CH DE IT LI

RBV Designated contracting states (corrected)

Designated state(s): CH DE IT LI

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20130313