EP2218918A1 - Compresseur turbo axial pour une turbine à gaz ayant des pertes de gaz et des pertes de diffuseur réduites - Google Patents

Compresseur turbo axial pour une turbine à gaz ayant des pertes de gaz et des pertes de diffuseur réduites Download PDF

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Publication number
EP2218918A1
EP2218918A1 EP09002056A EP09002056A EP2218918A1 EP 2218918 A1 EP2218918 A1 EP 2218918A1 EP 09002056 A EP09002056 A EP 09002056A EP 09002056 A EP09002056 A EP 09002056A EP 2218918 A1 EP2218918 A1 EP 2218918A1
Authority
EP
European Patent Office
Prior art keywords
shaft cover
blade
axial
tips
turbo compressor
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Withdrawn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
EP09002056A
Other languages
German (de)
English (en)
Inventor
François Dr. Benkler
Karl Dr. Klein
Torsten Matthias
Achim Schirrmacher
Oliver Dr. Schneider
Vadim Shevchenko
Ulrich Dr. Waltke
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 EP09002056A priority Critical patent/EP2218918A1/fr
Priority to US13/201,065 priority patent/US20110311355A1/en
Priority to EP10702467A priority patent/EP2396555A1/fr
Priority to CN201080008181.2A priority patent/CN102317634B/zh
Priority to JP2011549507A priority patent/JP5567036B2/ja
Priority to PCT/EP2010/050933 priority patent/WO2010091956A1/fr
Publication of EP2218918A1 publication Critical patent/EP2218918A1/fr
Withdrawn legal-status Critical Current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
    • F04D29/545—Ducts
    • F04D29/547—Ducts having a special shape in order to influence fluid flow
    • 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
    • F01D11/005—Sealing means between non relatively rotating elements
    • 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
    • F01D9/041—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector using blades
    • 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
    • F04D29/08—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
    • F04D29/40—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
    • F04D29/54—Fluid-guiding means, e.g. diffusers
    • F04D29/541—Specially adapted for elastic fluid pumps
    • F04D29/542—Bladed diffusers

Definitions

  • the invention relates to a Axialturbover Why a gas turbine, wherein the Axialturbover Why a gas turbine has low gap losses.
  • a gas turbine has a turbocompressor, for example, in axial construction.
  • the turbocompressor has a housing with a stator attached thereto and a rotor surrounded by the housing.
  • the rotor has a shaft on which the rotor is driven in rotation.
  • a shaft cover Surrounding the shaft, a shaft cover is provided, whose outer contour together with the inner contour of the housing forms part of the flow channel through the turbocompressor.
  • the flow channel has a cross section which widens in the flow direction, so that the flow channel is designed as a diffuser.
  • the rotor has a plurality of rotor stages, each formed by a row of rotor blades. Furthermore, the stator has a plurality of stator blade rows, which are arranged alternately to the rows of rotor blades when viewed in the axial direction. Conventionally, seen in the flow direction after the last row of rotor blades, a row of vanes and then a Nachleitschaufelsch arranged.
  • the rows of vanes have a plurality of blades, which are fastened with their one end respectively to the housing and with its other end pointing in the direction of the shaft.
  • a blade tip is formed, which faces the shaft cover and is disposed immediately adjacent.
  • the distance between the blade tips and the shaft cover is formed as a radial gap, which is dimensioned such that on the one hand, the blade tips do not abut the shaft cover during operation of the gas turbine and, on the other hand, the leakage flow through the radial gap that occurs during operation of the gas turbine is as low as possible.
  • This gap must therefore be designed as low as possible, so that a high efficiency can be achieved and the full blading potential of the compressor can be exploited.
  • the casing of the turbo-compressor is massively designed to withstand the pressure and temperature stresses in the operation of the gas turbine.
  • the housing is rigid, so that the load application to the housing during operation of the gas turbine has only a small deformation of the housing result.
  • the shaft cover is exposed to lower mechanical stresses during operation of the gas turbine, whereby the shaft cover is made thinner and less massive than the housing.
  • the shaft cover is formed with smaller wall thicknesses compared to the housing and typically has different material properties than the housing, the shaft cover heats up faster than the housing with the guide blade rows attached thereto. This has the consequence that for starting and stopping the gas turbine, the shaft cover and the housing have a different thermal expansion rate, so that when starting and stopping the gas turbine, the height of the radial gap changes, the radial gap when starting is temporarily smaller and larger when starting.
  • the radial gap is provided with a minimum height dimensioned such that in every operating state of the gas turbine - stationary and unsteady - the blade tips almost never touch the shaft cover. This has the consequence that at the blade tips a corresponding dimensioned radial gap is maintained, which leads to a reduction in the efficiency of the gas turbine.
  • the blockage caused by the radial gap leads to a reduction of the main flow component, whereby the pressure recovery in the diffuser is reduced and disadvantageous detachment phenomena may occur.
  • the object of the invention is to provide a Axialturbover Actually Noticer for a gas turbine, which has a high efficiency and high reliability.
  • the axial turbocompressor for a gas turbine engine comprises a vane grille formed by vanes with hub-side freestanding blade tips, and a stationary shaft cover located immediately adjacent the blade tips on the hub side and defining the flow passage of the axial compressor with a gap between the shaft cover and the blade tips is formed, which is minimally dimensioned so that just the assembling of the Axialturbover Whyrs betechnikstelligbar, and in the shaft cover a plurality of recesses is provided, each blade tip is associated with one of the recesses immediately adjacent to its associated blade tip and so is dimensioned such that during operation of the Axialturbover Whyrs each blade tip is plunged into its associated recess without one of the blade tips, the shaft cover significantly affected.
  • the gap between the blade tip and the shaft cover is set to the minimum necessary mounting gap, so that the height of the gap is reduced to the assembly-related minimum.
  • the height of the minimal necessary mounting gap is chosen such that the Einkugeln the guide vane grille, in particular the rear vane grille, can be accomplished.
  • the gap between the blade tips and the shaft cover is provided with a minimum height that is selected such that, as in all imaginable operating conditions of the gas turbine, the blade tips hardly or not touch the shaft cover. This results in the gap with such a height that flows through the gap a significant mass flow of leakage flow, which leads to an undesirable efficiency reduction of the gas turbine.
  • the gap is set to the minimum possible gap, namely to the minimum necessary assembly gap, so that the leakage flow through the gap is minimal.
  • the axial turbocompressor has a high pressure recovery in the diffuser section and thus a high efficiency.
  • the blade tips may dip into the recesses so that, although the gap is reduced to the minimum necessary assembly gap, noxious contact of the blade tips with the shaft cover during operation of the axial turbocompressor is inhibited.
  • the flow around the blade tip decreases, as a result of which the leakage flow at the blade tip also decreases.
  • the efficiency of the guide vane grille increases and losses and separations in the diffuser located downstream of the axial turbo-compressor are reduced.
  • the degree of expansion of the diffuser ie the diffuser angle of the diffuser, may be greater than would be the case with a conventional diffuser. This is accompanied by a reduction in the overall length of the gas turbine compared to a conventional gas turbine.
  • a honeycomb-like and / or felt-like structure is applied to the bottom of the depression, which can yield when touched by the blade tip.
  • the honeycomb-like structure is a honeycomb.
  • the blade tip can dip into the honeycomb-like and / or felt-like structure, whereby the blade tip is not damaged.
  • the flow around the blade tip decreases when the blade tip is immersed in its associated recess during a certain operating state and digs into the honeycomb-like and / or felt-like structure. This advantageously additionally reduces the leakage flow at the blade tip.
  • the recesses have an outline shape on the surface of the shaft cover, which is modeled after the profile of the associated vanes on the blade tip, and have a predetermined depth.
  • the material of the shaft cover is arranged around the blade tip immersed in the recess such that, on the one hand, the blade tip does not hit the shaft cover when immersed in the recess and, on the other hand, the flow around the blade tip decreases.
  • the depth of the depressions is determined such that during operation of the axial turbocompressor, the radial relative movements between the blade tips and the shaft seal can be compensated.
  • the contour of the recesses is determined such that during operation of the Axialturbover Whyrs the axial relative movements between the blade tips and the shaft seal can be compensated.
  • FIGS. 1 and 2 As it is from the FIGS. 1 and 2 As can be seen, has a Axialturbover Noticer 1 a Leitschaufelgitter 2, which is formed by a plurality of vanes 3.
  • the guide vanes 3 are arranged in a row in the circumferential direction of the axial turbo-compressor 1 and have a longitudinal extent in the radial direction of the axial turbo-compressor 1.
  • the Axialturbover Noticer 1 a housing 5, on the inside of the vanes 3 are fixed. Facing away from the housing 5, the guide vanes 3 have a blade tip 4 which points inwardly into the housing 5.
  • a shaft cover 6 is arranged directly on the blade tips 3, which is a circumferentially symmetrical Ring is formed.
  • a plurality of recesses 7 is provided at the blade tips 4 facing outside of the shaft cover 6, a plurality of recesses 7 is provided. Each recess 7 is associated with a different blade tip 4, wherein the recess 7 is located immediately adjacent to its associated vane tip 4.
  • Each recess 7 has at the blade tips 4 facing the outside of the shaft cover 6 has an outline 8, which is modeled on the profile shape of the guide vane 3 on the vane tip 4. Further, each recess 7 is provided with a depth 9 in the shaft cover 6. The shape of the outline 8 and the depth 9 are determined such that, during operation of the axial turbocompressor, each blade tip 4 can dip into its associated recess 7, whereby the blade tip 4 does not or hardly touches the wave cover 6 when immersed.
  • a honeycomb structure 10 is applied as shown in FIG. 1 is shown by way of example for the middle recess 7. If the blade tips 4 touch the honeycomb structure 10 during operation of the axial turbocompressor, the honeycomb structure 10 yields, so that the blade tip 4 presses into the honeycomb structure 10.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP09002056A 2009-02-13 2009-02-13 Compresseur turbo axial pour une turbine à gaz ayant des pertes de gaz et des pertes de diffuseur réduites Withdrawn EP2218918A1 (fr)

Priority Applications (6)

Application Number Priority Date Filing Date Title
EP09002056A EP2218918A1 (fr) 2009-02-13 2009-02-13 Compresseur turbo axial pour une turbine à gaz ayant des pertes de gaz et des pertes de diffuseur réduites
US13/201,065 US20110311355A1 (en) 2009-02-13 2010-01-27 Axial turbo compressor for a gas turbine having low radial gap losses and diffuser losses
EP10702467A EP2396555A1 (fr) 2009-02-13 2010-01-27 Turbocompresseur axial pour une turbine à gaz avec faibles pertes par les fentes radiales et les diffuseurs
CN201080008181.2A CN102317634B (zh) 2009-02-13 2010-01-27 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
JP2011549507A JP5567036B2 (ja) 2009-02-13 2010-01-27 低ギャップ損失および低拡散器損失を備えたガスタービンのための軸流ターボコンプレッサ
PCT/EP2010/050933 WO2010091956A1 (fr) 2009-02-13 2010-01-27 Turbocompresseur axial pour une turbine à gaz avec faibles pertes par les fentes radiales et les diffuseurs

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
EP09002056A EP2218918A1 (fr) 2009-02-13 2009-02-13 Compresseur turbo axial pour une turbine à gaz ayant des pertes de gaz et des pertes de diffuseur réduites

Publications (1)

Publication Number Publication Date
EP2218918A1 true EP2218918A1 (fr) 2010-08-18

Family

ID=40469901

Family Applications (2)

Application Number Title Priority Date Filing Date
EP09002056A Withdrawn EP2218918A1 (fr) 2009-02-13 2009-02-13 Compresseur turbo axial pour une turbine à gaz ayant des pertes de gaz et des pertes de diffuseur réduites
EP10702467A Withdrawn EP2396555A1 (fr) 2009-02-13 2010-01-27 Turbocompresseur axial pour une turbine à gaz avec faibles pertes par les fentes radiales et les diffuseurs

Family Applications After (1)

Application Number Title Priority Date Filing Date
EP10702467A Withdrawn EP2396555A1 (fr) 2009-02-13 2010-01-27 Turbocompresseur axial pour une turbine à gaz avec faibles pertes par les fentes radiales et les diffuseurs

Country Status (5)

Country Link
US (1) US20110311355A1 (fr)
EP (2) EP2218918A1 (fr)
JP (1) JP5567036B2 (fr)
CN (1) CN102317634B (fr)
WO (1) WO2010091956A1 (fr)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2538031A1 (fr) * 2011-06-22 2012-12-26 Siemens Aktiengesellschaft Rotor avec élément d'étanchéité pour une turbine à gaz stationnaire
US20130156559A1 (en) * 2010-06-17 2013-06-20 Snecma Compressor and a turbine engine with optimized efficiency
CN104074799A (zh) * 2013-11-17 2014-10-01 中国科学院工程热物理研究所 一种具有扩张型子午流道的轴流压气机及其设计方法
WO2023180668A1 (fr) * 2022-03-24 2023-09-28 Safran Helicopter Engines Module pour turbomachine d'aéronef

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014203605A1 (de) 2014-02-27 2015-08-27 Rolls-Royce Deutschland Ltd & Co Kg Schaufelreihengruppe
EP2977559B1 (fr) * 2014-07-25 2017-06-07 Safran Aero Boosters SA Stator de turbomachine axiale et turbomachine associée
US9988918B2 (en) * 2015-05-01 2018-06-05 General Electric Company Compressor system and airfoil assembly

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WO1995017584A1 (fr) * 1993-12-22 1995-06-29 Alliedsignal Inc. Ensemble aube de stator inserable
EP1079075A2 (fr) * 1999-08-09 2001-02-28 United Technologies Corporation Stator pour une turbomachine et agrafe pour le stator
EP1219785A1 (fr) * 2000-12-19 2002-07-03 United Technologies Corporation Ensemble de montage d'aubes de stator dans une turbine à gaz
EP1707744A2 (fr) * 2005-03-07 2006-10-04 The General Electric Company Aube avec anneau interne et externe

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GB1328426A (en) * 1971-08-28 1973-08-30 British Leyland Truck & Bus Gas turbine engines
US5226789A (en) * 1991-05-13 1993-07-13 General Electric Company Composite fan stator assembly
DE59201833D1 (de) * 1991-10-08 1995-05-11 Asea Brown Boveri Deckband für axialdurchströmte Turbine.
DE19813958C1 (de) * 1998-03-28 1999-11-25 Mtu Muenchen Gmbh Verfahren zum Herstellen eines gebauten Leitkranzes einer Gasturbine, insbesondere eines Flugtriebwerkes, sowie ein nach dem Verfahren hergestellter Leitkranz
US6543995B1 (en) * 1999-08-09 2003-04-08 United Technologies Corporation Stator vane and stator assembly for a rotary machine
US6450766B1 (en) * 1999-08-09 2002-09-17 United Technologies Corporation Stator vane blank and method of forming the vane blank
US6425736B1 (en) * 1999-08-09 2002-07-30 United Technologies Corporation Stator assembly for a rotary machine and method for making the stator assembly
EP2196629B1 (fr) * 2008-12-11 2018-05-16 Safran Aero Boosters SA Virole interne composite segmentée de redresseur de compresseur axial

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1995017584A1 (fr) * 1993-12-22 1995-06-29 Alliedsignal Inc. Ensemble aube de stator inserable
EP1079075A2 (fr) * 1999-08-09 2001-02-28 United Technologies Corporation Stator pour une turbomachine et agrafe pour le stator
EP1219785A1 (fr) * 2000-12-19 2002-07-03 United Technologies Corporation Ensemble de montage d'aubes de stator dans une turbine à gaz
EP1707744A2 (fr) * 2005-03-07 2006-10-04 The General Electric Company Aube avec anneau interne et externe

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20130156559A1 (en) * 2010-06-17 2013-06-20 Snecma Compressor and a turbine engine with optimized efficiency
US9488179B2 (en) * 2010-06-17 2016-11-08 Snecma Compressor and a turbine engine with optimized efficiency
EP2538031A1 (fr) * 2011-06-22 2012-12-26 Siemens Aktiengesellschaft Rotor avec élément d'étanchéité pour une turbine à gaz stationnaire
WO2012175274A1 (fr) * 2011-06-22 2012-12-27 Siemens Aktiengesellschaft Rotor doté d'un élément d'étanchéité pour une turbine à gaz stationnaire
CN104074799A (zh) * 2013-11-17 2014-10-01 中国科学院工程热物理研究所 一种具有扩张型子午流道的轴流压气机及其设计方法
WO2023180668A1 (fr) * 2022-03-24 2023-09-28 Safran Helicopter Engines Module pour turbomachine d'aéronef
FR3133886A1 (fr) * 2022-03-24 2023-09-29 Safran Helicopter Engines Module pour turbomachine d’aéronef

Also Published As

Publication number Publication date
JP2012518109A (ja) 2012-08-09
CN102317634A (zh) 2012-01-11
WO2010091956A1 (fr) 2010-08-19
CN102317634B (zh) 2014-06-25
EP2396555A1 (fr) 2011-12-21
JP5567036B2 (ja) 2014-08-06
US20110311355A1 (en) 2011-12-22

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