EP1574667A1 - Diffuseur pour compresseur - Google Patents

Diffuseur pour compresseur Download PDF

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Publication number
EP1574667A1
EP1574667A1 EP04004895A EP04004895A EP1574667A1 EP 1574667 A1 EP1574667 A1 EP 1574667A1 EP 04004895 A EP04004895 A EP 04004895A EP 04004895 A EP04004895 A EP 04004895A EP 1574667 A1 EP1574667 A1 EP 1574667A1
Authority
EP
European Patent Office
Prior art keywords
diffuser
constriction
housing
gas turbine
turbine
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.)
Granted
Application number
EP04004895A
Other languages
German (de)
English (en)
Other versions
EP1574667B1 (fr
Inventor
Christian Dr. Cornelius
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.)
Siemens AG
Original Assignee
Siemens 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 Siemens AG filed Critical Siemens AG
Priority to EP20040004895 priority Critical patent/EP1574667B1/fr
Publication of EP1574667A1 publication Critical patent/EP1574667A1/fr
Application granted granted Critical
Publication of EP1574667B1 publication Critical patent/EP1574667B1/fr
Anticipated expiration legal-status Critical
Expired - Lifetime 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

Definitions

  • the invention relates to a gas turbine with a compressor diffuser and there a measure to optimize a radial Mass flow distribution at the inlet of the compressor diffuser.
  • the invention also relates to a diffuser itself.
  • Diffuser Gas turbines with compressor diffuser, hereinafter referred to as Diffuser referred to, are well known.
  • a diffuser is known in its most general form a component of a Pipe in which the cross section grows gradually. This Increase in the cross-section causes a decrease in speed of the medium flowing through, while the static Pressure increases at the same time.
  • a combustion chamber and a turbine is a Diffuser usually at the output of the gas turbine, in particular immediately after the turbine, and / or at the exit arranged the compressor.
  • the invention is concerned with the mass flow or total pressure distribution, the for optimal operation of the diffuser is required.
  • a use of freestanding vanes leads in particular For larger radial gaps to a significant drop in speed the flowing working medium, ie the heated Gas, in the hub area of a turbine shaft at the outlet a Nachleitrades.
  • the speed drop goes accompanied by a total pressure drop.
  • the speed and pressure distribution is especially then unfavorable if a cross-sectional widening within the Diffusers exclusively via a reduction of the hub radius the hub-side inner contour of the diffuser takes place.
  • a weakened Speed profile in the area of the hub side Inner contour then leads to lossy flow separation on the inner contour of the diffuser. This significantly limits the pressure recovery of the diffuser and thus its Overall efficiency.
  • the invention is therefore based on the object, with regard to to avoid or reduce the above Disadvantages to specify optimized gas turbine with a diffuser.
  • the advantage of the invention is that by the modification the inner contour of the diffuser housing straight at a Ver Whyrdiffuser by the constriction redistribution the mass flow towards the hub of the turbine rotor is caused. This increases in the area of the hub Speed level.
  • the constriction is located on the inside of the outer wall of the diffuser housing.
  • the constriction can be caused by the fact that material on the inside of the outer wall of the diffuser housing is attached. Another way of training one Such constriction is that of an adapted, the Constriction-containing shaping of the outer wall of the diffuser housing is selected.
  • the constriction in the interior of the diffuser in Flow direction of the medium flowing through gradually so that the constriction of the intended operation of the Diffusers (speed reduction and pressure increase for the medium flowing through) not or only negligibly negative affected.
  • the constriction occurs at the inlet of the diffuser not abruptly but continuously and in a kind and Way in which in the direction of the medium flowing through a Increase in constriction up to a maximum constriction such that the increase in constriction to the maximum Constriction is significantly greater than the decrease in Constriction following the maximum constriction.
  • a gas turbine has a compressor for combustion air, a combustion chamber and a turbine to drive both the compressor as well as a work machine, z. B. a generator, on.
  • the combustion chamber is equipped with at least one burner for Combustion of a liquid or gaseous fuel equipped.
  • the compressor as well as the turbine each have a number of rotatable blades connected to the turbine shaft on.
  • the blades are crowned on the turbine shaft arranged and thus form a number of blade rows.
  • both the compressor comprises also the turbine has a number of fixed vanes, which also coronal under the formation of rows of vanes on an inner wall of the housing of compressor or Turbine are attached.
  • the vanes serve to guide the flow of the working medium between two each in the flow direction of the working medium seen consecutive blade rows or blade rings.
  • a successive pair of one Wreath of vanes or a vane row and out a wreath of blades or a row of blades is also used as a turbine stage or as a compressor stage designated.
  • the compressor or Turbine housing remains a radial gap whose size so is dimensioned that during operation of the gas turbine even with thermal expansions the respective materials a touch the blades on the respective inner housing excluded is.
  • a radial gap remains between the fixed vanes and the turbine shaft a radial gap. This is also such that a contact between the vanes and the turbine shaft is excluded.
  • the diffuser housing 2 has in one Connection area 3, ie in the area of the transition from the compressor the gas turbine to the diffuser 1, one the inner radius of the housing 2 reducing constriction 5.
  • One to the connection area 3 belonging portion of the diffuser 1 is as Inlet 4 of the diffuser 1 denotes.
  • the inlet 4 has a Ring space contour on. The dimensions of the inlet 4 are in Essentially determined by its inner radius.
  • the flow space of the diffuser 1 is radially outward by an outer wall of the diffuser housing 2 and radially inwardly by a hub side Inner contour limited.
  • the constriction 5 is located on the inside of an outer wall of the housing 2. It results from the difference of a conventional Annular space contour 6 of the diffuser housing 2 and a causing the constriction, modified annular space contour 7.
  • the constriction 5 is either material attachment on the inside of the outside wall or through an adapted one Shape of the outer wall caused.
  • the constriction 5 increases within the diffuser 1 in the flow direction of the medium flowing through, that is to say the compressed one Air, gradually.
  • the flow direction In the illustration in FIG 1 runs the flow direction from left to right.
  • At the inlet 4 of the diffuser 1 takes place - also in the direction of the flowing through Medium - an increase in constriction up to one maximum constriction 5 such that the increase in Constriction to maximum constriction 5 much larger is considered the decrease of constriction following the maximum Constriction 5.
  • the length of a route along the outer contour of the Diffuser housing 2 parallel to the flow direction of the medium, while the constriction to the maximum constriction 5 is less than one fifth of the length a route, during which the constriction starting decreases again from the maximum constriction 5.
  • the increase of the near-level speed level causes the hub boundary layer against can run a much higher pressure, so the Pressure recovery and the overall efficiency of the compressor is improved.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP20040004895 2004-03-02 2004-03-02 Diffuseur pour compresseur Expired - Lifetime EP1574667B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
EP20040004895 EP1574667B1 (fr) 2004-03-02 2004-03-02 Diffuseur pour compresseur

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP20040004895 EP1574667B1 (fr) 2004-03-02 2004-03-02 Diffuseur pour compresseur

Publications (2)

Publication Number Publication Date
EP1574667A1 true EP1574667A1 (fr) 2005-09-14
EP1574667B1 EP1574667B1 (fr) 2013-07-17

Family

ID=34814245

Family Applications (1)

Application Number Title Priority Date Filing Date
EP20040004895 Expired - Lifetime EP1574667B1 (fr) 2004-03-02 2004-03-02 Diffuseur pour compresseur

Country Status (1)

Country Link
EP (1) EP1574667B1 (fr)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2194231A1 (fr) * 2008-12-05 2010-06-09 Siemens Aktiengesellschaft Diffuseur annulaire pour une turbomachine axiale
DE102012215412A1 (de) * 2012-08-30 2014-03-06 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine und Verfahren zur Herstellung einer solchen Baugruppe
CN115962154A (zh) * 2023-03-17 2023-04-14 潍柴动力股份有限公司 过渡段子午流道在机匣侧变窄的压气机、发动机和汽车

Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1448244A (fr) * 1965-06-23 1966-08-05 Procédé et dispositif pour l'exploitation d'une installation de turbine à vapeur
US3625630A (en) * 1970-03-27 1971-12-07 Caterpillar Tractor Co Axial flow diffuser
US3879939A (en) * 1973-04-18 1975-04-29 United Aircraft Corp Combustion inlet diffuser employing boundary layer flow straightening vanes
US4180972A (en) * 1978-06-08 1980-01-01 General Motors Corporation Combustor support structure
GB2057672A (en) * 1979-07-04 1981-04-01 Rolls Royce Gas turbine combustion chamber
US4315715A (en) * 1978-07-26 1982-02-16 Nissan Motor Company, Limited Diffuser for fluid impelling device
SU1657672A1 (ru) * 1986-07-28 1991-06-23 Производственное объединение "Невский завод" им.В.И.Ленина Диффузор турбомашины
US6035964A (en) * 1998-01-28 2000-03-14 Alstom Energy Systems Gmbh Gas turbine muffler with diffusor
JP2000356139A (ja) * 1999-06-15 2000-12-26 Mitsubishi Heavy Ind Ltd ガスタービン圧縮機吐出空気の抽気方法
US20020078690A1 (en) * 2000-12-22 2002-06-27 Peter Stuttaford Fuel air premixer having a diffuser assembly and upstream fuel manifold rings
EP1227217A2 (fr) * 2001-01-25 2002-07-31 Mitsubishi Heavy Industries, Ltd. Turbine à gaz
EP1253295A2 (fr) * 2001-04-27 2002-10-30 Mitsubishi Heavy Industries, Ltd. Turbine axiale ayant un gradin dans un passage d'échappement

Patent Citations (12)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1448244A (fr) * 1965-06-23 1966-08-05 Procédé et dispositif pour l'exploitation d'une installation de turbine à vapeur
US3625630A (en) * 1970-03-27 1971-12-07 Caterpillar Tractor Co Axial flow diffuser
US3879939A (en) * 1973-04-18 1975-04-29 United Aircraft Corp Combustion inlet diffuser employing boundary layer flow straightening vanes
US4180972A (en) * 1978-06-08 1980-01-01 General Motors Corporation Combustor support structure
US4315715A (en) * 1978-07-26 1982-02-16 Nissan Motor Company, Limited Diffuser for fluid impelling device
GB2057672A (en) * 1979-07-04 1981-04-01 Rolls Royce Gas turbine combustion chamber
SU1657672A1 (ru) * 1986-07-28 1991-06-23 Производственное объединение "Невский завод" им.В.И.Ленина Диффузор турбомашины
US6035964A (en) * 1998-01-28 2000-03-14 Alstom Energy Systems Gmbh Gas turbine muffler with diffusor
JP2000356139A (ja) * 1999-06-15 2000-12-26 Mitsubishi Heavy Ind Ltd ガスタービン圧縮機吐出空気の抽気方法
US20020078690A1 (en) * 2000-12-22 2002-06-27 Peter Stuttaford Fuel air premixer having a diffuser assembly and upstream fuel manifold rings
EP1227217A2 (fr) * 2001-01-25 2002-07-31 Mitsubishi Heavy Industries, Ltd. Turbine à gaz
EP1253295A2 (fr) * 2001-04-27 2002-10-30 Mitsubishi Heavy Industries, Ltd. Turbine axiale ayant un gradin dans un passage d'échappement

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
PATENT ABSTRACTS OF JAPAN vol. 2000, no. 15 6 April 2001 (2001-04-06) *

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2507421C2 (ru) * 2008-12-05 2014-02-20 Сименс Акциенгезелльшафт Кольцевой диффузор для осевой турбинной машины, система для осевой турбинной машины, а также осевая турбинная машина
WO2010063583A1 (fr) 2008-12-05 2010-06-10 Siemens Aktiengesellschaft Diffuseur annulaire pour turbomachine axiale
JP2012511115A (ja) * 2008-12-05 2012-05-17 シーメンス アクティエンゲゼルシャフト 軸流ターボ機械のための環状拡散器、軸流ターボ機械のための配列および軸流ターボ機械
EP2455585A1 (fr) * 2008-12-05 2012-05-23 Siemens Aktiengesellschaft Agencement pour une turbomachine axiale et turbomachine axiale
CN102536912A (zh) * 2008-12-05 2012-07-04 西门子公司 用于轴流式涡轮机的环形扩压器、装置和轴流式涡轮机
RU2485358C2 (ru) * 2008-12-05 2013-06-20 Сименс Акциенгезелльшафт Кольцевой диффузор для осевой турбинной машины, система для осевой турбинной машины, а также осевая турбинная машина
EP2194231A1 (fr) * 2008-12-05 2010-06-09 Siemens Aktiengesellschaft Diffuseur annulaire pour une turbomachine axiale
US8721272B2 (en) 2008-12-05 2014-05-13 Siemens Aktiengesellschaft Ring diffuser for an axial turbomachine
US8721273B2 (en) 2008-12-05 2014-05-13 Siemens Aktiengesellschaft Ring diffuser for an axial turbomachine
CN102536912B (zh) * 2008-12-05 2015-07-08 西门子公司 用于轴流式涡轮机的环形扩压器、装置和轴流式涡轮机
DE102012215412A1 (de) * 2012-08-30 2014-03-06 Rolls-Royce Deutschland Ltd & Co Kg Baugruppe einer Axialturbomaschine und Verfahren zur Herstellung einer solchen Baugruppe
US9366148B2 (en) 2012-08-30 2016-06-14 Rolls-Royce Deutschland Ltd & Co Kg Assembly of an axial turbomachine and method for manufacturing an assembly of this type
CN115962154A (zh) * 2023-03-17 2023-04-14 潍柴动力股份有限公司 过渡段子午流道在机匣侧变窄的压气机、发动机和汽车

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Publication number Publication date
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