EP0638725A1 - Vorrichtung zur Sekundärluftentnahme aus einem Axialverdichter - Google Patents

Vorrichtung zur Sekundärluftentnahme aus einem Axialverdichter Download PDF

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Publication number
EP0638725A1
EP0638725A1 EP94111013A EP94111013A EP0638725A1 EP 0638725 A1 EP0638725 A1 EP 0638725A1 EP 94111013 A EP94111013 A EP 94111013A EP 94111013 A EP94111013 A EP 94111013A EP 0638725 A1 EP0638725 A1 EP 0638725A1
Authority
EP
European Patent Office
Prior art keywords
slot
compressor
mini
guide vane
removal slot
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
EP94111013A
Other languages
German (de)
English (en)
French (fr)
Inventor
Thomas Meindl
Pierre Meylan
Thomas Dr. Zierer
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.)
ABB AG Germany
Original Assignee
ABB Management AG
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 ABB Management AG filed Critical ABB Management AG
Publication of EP0638725A1 publication Critical patent/EP0638725A1/de
Ceased 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially 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
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/52—Casings; Connections of working fluid for axial pumps
    • F04D29/522—Casings; Connections of working fluid for axial pumps 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
    • F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
    • F04D27/02—Surge control
    • F04D27/0207—Surge control by bleeding, bypassing or recycling fluids
    • F04D27/023—Details or means for fluid extraction

Definitions

  • the invention relates to a device for extracting secondary air from an axial compressor, a circumferential slot being used for the removal.
  • Secondary air is taken from the turbine to supply cooling air to the compressors.
  • a certain total pressure is necessary.
  • a peripheral slot is usually used to extract the secondary air. The extracted air passes through the extraction slot into the extraction plenum and from there via the extraction pipe into the cooling system of the turbine. Unfortunately, a large part of the dynamic pressure is lost during removal.
  • the invention tries to avoid this disadvantage. It is the object of the invention to provide a device for taking secondary air from an axial compressor using a circumferential removal slot, which is at least partially designed as a diagonal diffuser, in which the total pressure loss is minimized.
  • the means for converting the kinetic energy of the peripheral component of the flow velocity is a mini-baffle which is arranged directly in the entry region of the removal slot which has a constant height. The circumferential speed is thereby converted into static pressure and thus the total pressure loss is minimized.
  • the mini guide vane is arranged on the compressor guide wheel at the entry of the removal slot, the guide guide of the compressor and the mini guide guide having different deflection angles and / or different numbers of blades.
  • mini guide vane is arranged at the end of the removal slot which is divergent over the entire length.
  • the extraction slot is advantageously designed as a diagonal diffuser, which merges into a spiral, the spiral opening directly into the extraction tube.
  • part of the peripheral speed is converted into static pressure and part of the peripheral speed becomes a transport component.
  • Fig. 1 a partial longitudinal section of a gas turbine compressor is shown. Between the stator 1 and the impeller 2 of the compressor, a circumferential removal slot 4 is arranged in the gas turbine housing 3, which opens into a removal plenum 5. The withdrawal plenum 5 is in turn connected to the withdrawal tube 6. The entry area of the removal slot 4 has a constant height. A mini guide vane 7 is arranged there. The part of the removal slot 4 that follows is designed as a diagonal diffuser 8.
  • the flow at the entry into the removal slot 4 is axially aligned by the mini guide vane 7. This becomes the peripheral component of the flow rate converted to static pressure and the total pressure loss is reduced.
  • the mini guide vane has a particularly favorable effect when there is a strong swirl in the current.
  • the removal slot 4 can be designed over the entire length as a divergent channel, at the end of which the mini guide vane is arranged.
  • FIG. 2 Another embodiment of the invention is shown in FIG. 2.
  • the mini guide vane 7 is designed here together with the guide vane of the compressor.
  • the stator 1 of the compressor is divided. The lower part is used to deflect the compressor, while the upper part represents the mini guide vane 7 for deflecting the flow in the axial direction. Since the guide grille of the compressor does not usually deflect in the axial direction, the guide grille and the mini guide grille 7 have different deflection angles.
  • the number of blades of guide and mini guide grid 7 can also be different.
  • the circumferential component of the impeller outflow in the compressor is converted into static pressure and the total pressure loss is minimized.
  • FIGS. 3 and 4 A fourth embodiment is shown in FIGS. 3 and 4.
  • the removal slot 4 is not designed as usual in the combination of the removal slot 4 / removal plenum 5 (see FIGS. 1 and 2), but the removal slot 4 designed as a diagonal diffuser 8 merges into a spiral 9.
  • This spiral 9 opens directly into the sampling tube 6. This also means that part of the peripheral component of the flow velocity is converted into static pressure with little loss, and another part becomes the transport component. The total pressure loss is reduced and, moreover, there is no outlet loss of the flow which occurs during the transition into the plenum 5 would. The efficiency of the system is thus increased compared to the prior art. If a spiral 9 is used, the mini guide vane 7 can be dispensed with.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP94111013A 1993-08-10 1994-07-15 Vorrichtung zur Sekundärluftentnahme aus einem Axialverdichter Ceased EP0638725A1 (de)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
DE4326799A DE4326799A1 (de) 1993-08-10 1993-08-10 Vorrichtung zur Sekundärluftentnahme aus einem Axialverdichter
DE4326799 1993-08-10

Publications (1)

Publication Number Publication Date
EP0638725A1 true EP0638725A1 (de) 1995-02-15

Family

ID=6494841

Family Applications (1)

Application Number Title Priority Date Filing Date
EP94111013A Ceased EP0638725A1 (de) 1993-08-10 1994-07-15 Vorrichtung zur Sekundärluftentnahme aus einem Axialverdichter

Country Status (4)

Country Link
US (1) US5531565A (ja)
EP (1) EP0638725A1 (ja)
JP (1) JPH0763199A (ja)
DE (1) DE4326799A1 (ja)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2055961A1 (en) * 2007-10-30 2009-05-06 General Electric Company Asymmetric flow extraction system
EP2103792A1 (de) 2008-03-19 2009-09-23 Rolls-Royce Deutschland Ltd & Co KG Gasturbinenverdichter mit Zapfluftentnahmevorrichtung
EP2987967A1 (de) * 2014-08-20 2016-02-24 Siemens Aktiengesellschaft Verdichtergehäuse für eine Gasturbine
CN106321516A (zh) * 2015-07-01 2017-01-11 航空技术空间股份有限公司 轴流式涡轮发动机的压缩机的带穿孔鼓部

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19515926A1 (de) * 1995-05-02 1996-11-07 Abb Management Ag Axial durchströmte Turbomaschine
DE69936939T2 (de) * 1998-02-26 2008-05-15 Allison Advanced Development Co., Indianapolis Zapfsystem für eine kompressorwand sowie betriebsverfahren
DE19814627C2 (de) * 1998-04-01 2001-02-22 Man Turbomasch Ag Ghh Borsig Kühlluftentnahme aus dem Diffusorteil eines Kompressors einer Gasturbine
US6109868A (en) * 1998-12-07 2000-08-29 General Electric Company Reduced-length high flow interstage air extraction
US6231301B1 (en) 1998-12-10 2001-05-15 United Technologies Corporation Casing treatment for a fluid compressor
US6574965B1 (en) 1998-12-23 2003-06-10 United Technologies Corporation Rotor tip bleed in gas turbine engines
GB0206880D0 (en) * 2002-03-23 2002-05-01 Rolls Royce Plc A vane for a rotor arrangement for a gas turbine engine
US8292567B2 (en) * 2006-09-14 2012-10-23 Caterpillar Inc. Stator assembly including bleed ports for turbine engine compressor
US8950069B2 (en) * 2006-12-29 2015-02-10 Rolls-Royce North American Technologies, Inc. Integrated compressor vane casing
EP2058524A1 (en) * 2007-11-12 2009-05-13 Siemens Aktiengesellschaft Air bleed compressor with variable guide vanes
GB0810883D0 (en) * 2008-06-16 2008-07-23 Rolls Royce Plc A bleed valve arrangement
JP5129052B2 (ja) * 2008-07-23 2013-01-23 株式会社日立製作所 ガスタービン圧縮機
US8092145B2 (en) * 2008-10-28 2012-01-10 Pratt & Whitney Canada Corp. Particle separator and separating method for gas turbine engine
DE102010002114A1 (de) * 2010-02-18 2011-08-18 Rolls-Royce Deutschland Ltd & Co KG, 15827 Gasturbine mit einer Zapflufteinrichtung für den Verdichter
GB201015029D0 (en) * 2010-09-10 2010-10-20 Rolls Royce Plc Gas turbine engine
US10072522B2 (en) 2011-07-14 2018-09-11 Honeywell International Inc. Compressors with integrated secondary air flow systems
EP2679776A1 (en) * 2012-06-28 2014-01-01 Alstom Technology Ltd Cooling system and method for an axial flow turbine
US9528391B2 (en) 2012-07-17 2016-12-27 United Technologies Corporation Gas turbine engine outer case with contoured bleed boss
US20140338360A1 (en) * 2012-09-21 2014-11-20 United Technologies Corporation Bleed port ribs for turbomachine case
US9677472B2 (en) * 2012-10-08 2017-06-13 United Technologies Corporation Bleed air slot
JP6188069B2 (ja) * 2013-10-17 2017-08-30 三菱重工業株式会社 圧縮機、及びガスタービン
JP6037996B2 (ja) * 2013-10-17 2016-12-07 三菱重工業株式会社 圧縮機、及びガスタービン
EP3037674A1 (en) * 2014-12-22 2016-06-29 Alstom Technology Ltd Engine and method for operating said engine
JP6689105B2 (ja) * 2016-03-14 2020-04-28 三菱重工業株式会社 多段軸流圧縮機及びガスタービン
US10227930B2 (en) * 2016-03-28 2019-03-12 General Electric Company Compressor bleed systems in turbomachines and methods of extracting compressor airflow
US11635030B2 (en) * 2017-06-13 2023-04-25 General Electric Company Compressor bleed apparatus for a turbine engine
CN111734679A (zh) * 2020-07-02 2020-10-02 中国航发常州兰翔机械有限责任公司 一种带放气孔的航空发动机压气机内机匣及其加工方法

Citations (7)

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Publication number Priority date Publication date Assignee Title
US3142438A (en) * 1961-04-21 1964-07-28 Rolls Royce Multi-stage axial compressor
GB987625A (en) * 1963-10-14 1965-03-31 Rolls Royce Improvements in or relating to axial flow compressors, for example for aircraft gas turbine engines
DE2031612A1 (de) * 1969-09-30 1971-04-15 Gen Electric Vielstufiger Axialkompressor mit einem Luftableitsystem als Zwischen stufe
FR2349740A1 (fr) * 1976-04-26 1977-11-25 Boeing Co Berceau de turboreacteur a double flux a portes de contournement de stators
US4182595A (en) * 1978-01-30 1980-01-08 Westinghouse Electric Corp. Discharge assembly for an axial flow compressor
JPS62168999A (ja) * 1986-01-20 1987-07-25 Hitachi Ltd 軸流圧縮機の抽気装置
DE4038353A1 (de) * 1990-04-09 1991-10-10 Gen Electric Verfahren und einrichtung zur kompressorluftextraktion

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GB531254A (en) * 1939-05-17 1941-01-01 Brevets Aero Mecaniques Improvements in and relating to centrifugal air and like compressors
CH219739A (de) * 1941-01-16 1942-02-28 Oerlikon Maschf Kreiselfördermaschine mit Spiralgehäuse.
GB936635A (en) * 1961-04-21 1963-09-11 Rolls Royce Multi-stage axial-flow compressor
US3966355A (en) * 1975-06-24 1976-06-29 Westinghouse Electric Corporation Steam turbine extraction system
SU953231A1 (ru) * 1980-07-11 1982-08-23 Ленинградский Ордена Ленина Кораблестроительный Институт Отсек паровой турбины
US4463552A (en) * 1981-12-14 1984-08-07 United Technologies Corporation Combined surge bleed and dust removal system for a fan-jet engine
GB2192229B (en) * 1986-07-04 1990-05-02 Rolls Royce Plc A compressor and air bleed system

Patent Citations (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3142438A (en) * 1961-04-21 1964-07-28 Rolls Royce Multi-stage axial compressor
GB987625A (en) * 1963-10-14 1965-03-31 Rolls Royce Improvements in or relating to axial flow compressors, for example for aircraft gas turbine engines
DE2031612A1 (de) * 1969-09-30 1971-04-15 Gen Electric Vielstufiger Axialkompressor mit einem Luftableitsystem als Zwischen stufe
FR2349740A1 (fr) * 1976-04-26 1977-11-25 Boeing Co Berceau de turboreacteur a double flux a portes de contournement de stators
US4182595A (en) * 1978-01-30 1980-01-08 Westinghouse Electric Corp. Discharge assembly for an axial flow compressor
JPS62168999A (ja) * 1986-01-20 1987-07-25 Hitachi Ltd 軸流圧縮機の抽気装置
DE4038353A1 (de) * 1990-04-09 1991-10-10 Gen Electric Verfahren und einrichtung zur kompressorluftextraktion

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 12, no. 4 (M - 657) 8 January 1988 (1988-01-08) *

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2055961A1 (en) * 2007-10-30 2009-05-06 General Electric Company Asymmetric flow extraction system
US8388308B2 (en) 2007-10-30 2013-03-05 General Electric Company Asymmetric flow extraction system
EP2103792A1 (de) 2008-03-19 2009-09-23 Rolls-Royce Deutschland Ltd & Co KG Gasturbinenverdichter mit Zapfluftentnahmevorrichtung
US8220276B2 (en) 2008-03-19 2012-07-17 Rolls-Royce Deutschland Ltd & Co Kg Gas-turbine compressor with bleed-air tapping
EP2987967A1 (de) * 2014-08-20 2016-02-24 Siemens Aktiengesellschaft Verdichtergehäuse für eine Gasturbine
CN106321516A (zh) * 2015-07-01 2017-01-11 航空技术空间股份有限公司 轴流式涡轮发动机的压缩机的带穿孔鼓部
CN106321516B (zh) * 2015-07-01 2020-09-01 赛峰航空助推器股份有限公司 轴流式涡轮发动机的压缩机的带穿孔鼓部

Also Published As

Publication number Publication date
US5531565A (en) 1996-07-02
JPH0763199A (ja) 1995-03-07
DE4326799A1 (de) 1995-02-16

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