EP1793089A2 - Méthode et dispositif pour réduire les fuites d' extrémité d' aubes de compresseur axial - Google Patents

Méthode et dispositif pour réduire les fuites d' extrémité d' aubes de compresseur axial Download PDF

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Publication number
EP1793089A2
EP1793089A2 EP06125091A EP06125091A EP1793089A2 EP 1793089 A2 EP1793089 A2 EP 1793089A2 EP 06125091 A EP06125091 A EP 06125091A EP 06125091 A EP06125091 A EP 06125091A EP 1793089 A2 EP1793089 A2 EP 1793089A2
Authority
EP
European Patent Office
Prior art keywords
airfoil
tip
channel
blade
air
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.)
Ceased
Application number
EP06125091A
Other languages
German (de)
English (en)
Other versions
EP1793089A3 (fr
Inventor
Zhifeng Dong
John Joseph Rahaim
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 EP1793089A2 publication Critical patent/EP1793089A2/fr
Publication of EP1793089A3 publication Critical patent/EP1793089A3/fr
Ceased 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
    • F01D11/10—Preventing or minimising internal leakage of working-fluid, e.g. between stages for sealing space between rotor blade tips and stator using sealing fluid, e.g. steam
    • 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
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/68—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers
    • F04D29/681—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps
    • F04D29/684—Combating cavitation, whirls, noise, vibration or the like; Balancing by influencing boundary layers especially adapted for elastic fluid pumps by fluid injection
    • 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
    • F05D2240/20—Rotors
    • F05D2240/30—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor
    • F05D2240/307—Characteristics of rotor blades, i.e. of any element transforming dynamic fluid energy to or from rotational energy and being attached to a rotor related to the tip of a rotor blade

Definitions

  • This invention relates to a method and apparatus for reducing axial compressor tip flow in airfoils, such as blades and vanes.
  • Blade tip flow in the compressor area of a turbine engine results in loss of compressor efficiency and stall margin.
  • flow recirculation in seal cavities along the inner flow path between the vanes and blades also degrades compressor performance.
  • One prior art solution for reducing tip flow is to reduce the blade tip clearance. This is done by a variety of means, including control of the casing and vane interface using mechanical and/or thermal methods. These methods can cause tip rubbing, excess wear and loss of engine efficiency.
  • a method of reducing air flow between a tip of a turbine airfoil rotating in a closely-spaced apart casing comprises the step of providing in the airfoil a radially-extending channel having an inlet opening proximate a base of the airfoil and an exit opening on the airfoil tip. Air is extracted and pressurized from a region proximate the base of the airfoil, introduced into the channel and conveyed through the channel to the airfoil tip. The air exits the channel through the exit openings in the airfoil tip into an area between the airfoil tip and casing under sufficient pressure to resist axial air flow from a pressure side to a suction side of the airfoil.
  • Another aspect of the invention provides a method of reducing air flow between a tip of a turbine airfoil rotating in a closely-spaced apart casing, comprising the steps of providing a first radially-extending channel having an inlet opening proximate a base of the airfoil on a leading edge side thereof, and an exit opening on the airfoil tip, and providing a second radially-extending channel having an inlet opening proximate the base of the airfoil on a trailing edge side thereof, and an exit opening on the airfoil tip.
  • the air is extracted from a region proximate the base of the airfoil into the channel and pumped through the channel to the airfoil tip.
  • the air exits the channel through the exit openings in the airfoil tip into an area between the airfoil tip and casing under sufficient pressure to resist axial air flow from a pressure side to a suction side of the airfoil.
  • a turbine machine compressor airfoil comprising a airfoil base, a airfoil tip, and an air flow channel extending radially from an air inlet opening in the airfoil proximate the airfoil base to an exit opening in the airfoil tip for providing a air blockage against an axial flow of air from the pressure side of the airfoil to the suction side of the airfoil to thereby reduce compressor airfoil tip flow.
  • FIG. 1 a partial section of the axial compressor section of a turbine engine T1 illustrating a method and apparatus for controlling axial compressor blade tip flow according to the present invention is illustrated in Figure 1.
  • the turbine engine “T1” includes compressor blades 10-14 and intermediately-positioned stator vanes 15-19 in a casing C1.
  • the compressor blades 10-14 include respective leading edges 10A-14A.
  • blade 10 is shown in enlarged detail for clarity, and is also exemplary of blades 11-14.
  • Air is extracted and pressurized from the area of the leading edge side 10A of the blade 10 through holes 10B in a disk 20.
  • the holes 10B communicate with a channel 10C that extends radially outwardly through the blade 10 to the tip where it exits through holes 10D.
  • the channel 10C may branch out before exiting the tip of the blade 10.
  • the size of the channel 10C and the location and number of the branches is determined empirically based on blade size, shape and volume, and engine performance, rating, tip clearance and similar factors. Note in the drawings that the tip clearance is sufficiently small in relation to the scale of the drawings that actual representation of the tip clearance cannot be shown.
  • a turbine engine “T2” includes compressor blades 30-34 and intermediately-positioned stator vanes 35-39 in a casing C2.
  • the compressor blades 30-34 include respective trailing edges 30A-34A.
  • blade 31 is shown in enlarged detail for clarity, and is exemplary of blades 30 and 32-34. Air is extracted from the area of the trailing edge side 31A of the blade 31 through holes 31B in the disk rim 40.
  • the holes 31B communicate with a channel 31C that extends radially outwardly through the blade 31 to the tip where it preferably branches before exiting through holes 31D.
  • a turbine engine “T3” includes compressor blades 50-54 and intermediately-positioned stator vanes 55-59 in a casing C3.
  • the compressor blades 50-54 include respective leading edges 50A-54A and respective trailing edges 50B-54B.
  • FIG. 6 illustrates a blade 52 that is shown in enlarged detail for clarity, and is exemplary of blades 51 and 52-54. Air is extracted from both the areas of the leading edge side 52A and trailing edge side 52B of blade 52 through holes 52C and 52D in the disk rim 60.
  • the holes 52C and 52D communicate with channels 52E and 52F, respectively, that extend radially outwardly through the blade 52 to the tip, where they preferably branch before exiting through holes 52G.
  • the air discharged at the blade tip reduces or prevents blade tip flow by aerodynamically blocking air flow in the region of the tip clearance between the blade tip and the casing. Air from the inner flow path is brought to the tip clearance, as described above, to form this air block. The pressure of the extracted air increases due to the compressor rotor pumping and, when exiting the blade at the tip, resists air flow across the blade tip from the pressure side to the suction side.
  • the methods described above can be applied to both low pressure compressors (boosters) and high pressure compressors. There is no chargeable flow loss when these methods are utilized. Furthermore, by reducing air flow by aerodynamic air blockage rather than by a tight running clearance between the blade tips and the casing, a larger assembly clearance between the blade tips and the casing can be established and maintained. Blade tip rubs are thus reduced, as is recirculation in the inner flow path between the vane and the blade. The extracted air is continuously pumped from the inner flow path to the blade tip, thus providing a continuous air blockage to the blade tip at all times during engine operation.
  • the methods described in this application also have application in blisk (blade integrated disk), skewed or circumferential dovetailed blades.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP06125091A 2005-11-30 2006-11-30 Méthode et dispositif pour réduire les fuites d' extrémité d' aubes de compresseur axial Ceased EP1793089A3 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/164,636 US20070122280A1 (en) 2005-11-30 2005-11-30 Method and apparatus for reducing axial compressor blade tip flow

Publications (2)

Publication Number Publication Date
EP1793089A2 true EP1793089A2 (fr) 2007-06-06
EP1793089A3 EP1793089A3 (fr) 2007-10-24

Family

ID=37685846

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06125091A Ceased EP1793089A3 (fr) 2005-11-30 2006-11-30 Méthode et dispositif pour réduire les fuites d' extrémité d' aubes de compresseur axial

Country Status (5)

Country Link
US (1) US20070122280A1 (fr)
EP (1) EP1793089A3 (fr)
JP (1) JP2007154887A (fr)
CN (1) CN101008402A (fr)
CA (1) CA2569177A1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2452297B (en) * 2007-08-30 2010-01-06 Rolls Royce Plc A compressor
CN102628452A (zh) * 2012-03-21 2012-08-08 朱晓义 一种空气压缩机及一种汽车发动机
EP2250347B1 (fr) * 2008-02-28 2017-11-29 MTU Aero Engines GmbH Compresseur axial avec un dispositif pour rediriger un courant de fuite

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20100275574A1 (en) * 2009-04-30 2010-11-04 General Electric Company Borescope plug with bristles
DE102012215895A1 (de) * 2012-09-07 2014-03-13 Robert Bosch Gmbh Schaufelrad für eine Strömungsmaschine sowie Verfahren zum Herstellen eines Turbinenrads für eine Strömungsmaschine
CN103925244B (zh) * 2014-04-02 2017-03-15 清华大学 一种用于300mw f级重型燃气轮机的大流量高负荷轴流压气机
JP6468532B2 (ja) * 2015-04-27 2019-02-13 三菱日立パワーシステムズ株式会社 圧縮機ロータ、圧縮機、及びガスタービン

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2165315A (en) 1984-10-04 1986-04-09 Rolls Royce Improvements in or relating to hollow fluid cooled turbine blades
EP0278434A2 (fr) 1987-02-06 1988-08-17 Wolfgang P. Weinhold Aube de rotor
US5688107A (en) 1992-12-28 1997-11-18 United Technologies Corp. Turbine blade passive clearance control
GB2409247A (en) 2003-12-20 2005-06-22 Rolls Royce Plc A seal arrangement

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JPS4825103U (fr) * 1971-08-06 1973-03-24
CH582305A5 (fr) * 1974-09-05 1976-11-30 Bbc Sulzer Turbomaschinen
GB1514613A (en) * 1976-04-08 1978-06-14 Rolls Royce Blade or vane for a gas turbine engine
JPS5713201A (en) * 1980-06-30 1982-01-23 Hitachi Ltd Air cooled gas turbine blade
JPS6081204U (ja) * 1983-11-10 1985-06-05 三菱重工業株式会社 タ−ビン動翼および静翼の冷却構造
US4761116A (en) * 1987-05-11 1988-08-02 General Electric Company Turbine blade with tip vent
US5667359A (en) * 1988-08-24 1997-09-16 United Technologies Corp. Clearance control for the turbine of a gas turbine engine
US5358378A (en) * 1992-11-17 1994-10-25 Holscher Donald J Multistage centrifugal compressor without seals and with axial thrust balance
US5403158A (en) * 1993-12-23 1995-04-04 United Technologies Corporation Aerodynamic tip sealing for rotor blades
US5387085A (en) * 1994-01-07 1995-02-07 General Electric Company Turbine blade composite cooling circuit
US6257830B1 (en) * 1997-06-06 2001-07-10 Mitsubishi Heavy Industries, Ltd. Gas turbine blade
JP2955252B2 (ja) * 1997-06-26 1999-10-04 三菱重工業株式会社 ガスタービン動翼チップシュラウド
US6574965B1 (en) * 1998-12-23 2003-06-10 United Technologies Corporation Rotor tip bleed in gas turbine engines
US6206638B1 (en) * 1999-02-12 2001-03-27 General Electric Company Low cost airfoil cooling circuit with sidewall impingement cooling chambers
DE19921644B4 (de) * 1999-05-10 2012-01-05 Alstom Kühlbare Schaufel für eine Gasturbine
US6382914B1 (en) * 2001-02-23 2002-05-07 General Electric Company Cooling medium transfer passageways in radial cooled turbine blades
EP1247939A1 (fr) * 2001-04-06 2002-10-09 Siemens Aktiengesellschaft Aube de turbine et son procédé de production
US6494678B1 (en) * 2001-05-31 2002-12-17 General Electric Company Film cooled blade tip
DE10205363A1 (de) * 2002-02-08 2003-08-21 Rolls Royce Deutschland Gasturbine
US7137782B2 (en) * 2004-04-27 2006-11-21 General Electric Company Turbulator on the underside of a turbine blade tip turn and related method

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2165315A (en) 1984-10-04 1986-04-09 Rolls Royce Improvements in or relating to hollow fluid cooled turbine blades
EP0278434A2 (fr) 1987-02-06 1988-08-17 Wolfgang P. Weinhold Aube de rotor
US5688107A (en) 1992-12-28 1997-11-18 United Technologies Corp. Turbine blade passive clearance control
GB2409247A (en) 2003-12-20 2005-06-22 Rolls Royce Plc A seal arrangement

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB2452297B (en) * 2007-08-30 2010-01-06 Rolls Royce Plc A compressor
EP2250347B1 (fr) * 2008-02-28 2017-11-29 MTU Aero Engines GmbH Compresseur axial avec un dispositif pour rediriger un courant de fuite
CN102628452A (zh) * 2012-03-21 2012-08-08 朱晓义 一种空气压缩机及一种汽车发动机
CN102628452B (zh) * 2012-03-21 2014-07-16 朱晓义 一种空气压缩机及一种汽车发动机

Also Published As

Publication number Publication date
US20070122280A1 (en) 2007-05-31
CN101008402A (zh) 2007-08-01
JP2007154887A (ja) 2007-06-21
CA2569177A1 (fr) 2007-05-30
EP1793089A3 (fr) 2007-10-24

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