EP2396555A1 - Turbocompresseur axial pour une turbine à gaz avec faibles pertes par les fentes radiales et les diffuseurs - Google Patents

Turbocompresseur axial pour une turbine à gaz avec faibles pertes par les fentes radiales et les diffuseurs

Info

Publication number
EP2396555A1
EP2396555A1 EP10702467A EP10702467A EP2396555A1 EP 2396555 A1 EP2396555 A1 EP 2396555A1 EP 10702467 A EP10702467 A EP 10702467A EP 10702467 A EP10702467 A EP 10702467A EP 2396555 A1 EP2396555 A1 EP 2396555A1
Authority
EP
European Patent Office
Prior art keywords
shaft cover
axial
tips
vane
blade
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Withdrawn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
EP10702467A
Other languages
German (de)
English (en)
Inventor
Francois Benkler
Karl Klein
Torsten Matthias
Achim Schirrmacher
Oliver Schneider
Vadim Shevchenko
Ulrich 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 EP10702467A priority Critical patent/EP2396555A1/fr
Publication of EP2396555A1 publication Critical patent/EP2396555A1/fr
Withdrawn legal-status Critical Current

Links

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 an axial turbocompressor for a gas turbine, wherein the axial turbocharger has low radial 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 radial gap must therefore be designed as low as possible so that a high degree of efficiency can be achieved and the full blading potential of the compressor can be exploited.
  • it is also known, for example, from EP 1 079 075 A2 the hub-side ends of the blades by means of a
  • 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 temporarily smaller and larger when driving off is.
  • the radial gap is provided with such a dimensioned minimum height, that in each operating state of the gas turbine - both stationary and unsteady - the blade tips almost never touch the shaft cover. This has the consequence that at the blade tips a correspondingly sized radial gap is maintained, which leads to a reduction of 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 comprises a stator vane 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 radial gap between the shaft cover and the blade tips is formed, which is minimally dimensioned so that just the assembling of the Axialturbover Whyrs is accomplished, and in the shaft cover a plurality of blind hole-like depressions is provided, each blade tip is associated with one of the wells immediately adjacent to its associated blade tip and is dimensioned such that during operation of the Axialturbover Noners each blade tip is plunged into its associated recess without one of the blade tips, the shaft cover prevail touched.
  • the radial gap between the blade tip and the shaft cover on the minimum necessary mounting gap adjusted so that the height of the radial 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 radial gap between the blade tips and the shaft cover is provided with such a minimum necessary height that virtually as in all conceivable operating conditions of the
  • the radial gap is set to the minimum possible radial gap, namely to the minimum necessary assembly gap, so that the leakage flow through the radial 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 radial 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.
  • This increases the efficiency of the vane grille and losses and separations in the downstream of the Axialturbover confusers lying diffuser 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.
  • an 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 recesses is determined such that in the operation of the axial turbo compressor the radial relative movements between the blade tips and the shaft seal can be compensated.
  • the outline profile of the depressions is determined in such a way that, during operation of the axial turbocompressor, the axial relative movements between the blade tips and the shaft seal can be compensated.
  • Figure 1 is a perspective view of a section of the Axialturbover Whyrs is asymmetrical to the Axialturbover Whyrs is asymmetrical to the Axialturbover Whyrs is asymmetrical to the Axialturbover Whyrs is asymmetrical to the Axialturbover Whyrs is asymmetrical to the Axialturbover Whyrs is asymmetrical to the Axialturbover Noners.
  • Figure 2 is a view along the blade longitudinal axis of
  • an axial turbo-compressor 1 has a vane grille 2 formed by a plurality of vanes 3.
  • the guide vanes 3 are arranged lined up in the circumferential direction of the axial turbo-compressor 1 and have a longitudinal extension in the radial direction of the axial turbo-compressor 1. Further, 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 and is designed as a circumferentially symmetrical ring.
  • 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.
  • the recess 7 is formed like a blind hole and thus ends blind. That is, it is provided with a tightly closed ground to prevent leakage losses.
  • 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, wherein when diving the blade tip 4, the wave cover 6 is not or virtually touched.
  • a honeycomb structure 10 is applied, as shown by way of example in FIG. 1 for the central 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)

Abstract

L'invention concerne un turbocompresseur axial pour une turbine à gaz avec une grille d'aubes directrices (2) qui est formée par des aubes directrices (3) avec pointes d'aubes (4) libres côté moyeu et une couverture d'arbre (6) stationnaire qui est disposée côté moyeu à proximité immédiate des pointes d'aubes (4) et délimite le canal d'écoulement du compresseur axial (1). Entre la couverture d'arbre (6) et les pointes des aubes (4) est formée une fente radiale dont la dimension est minimisée de manière à tout juste permettre le montage du turbocompresseur axial (1). Il est prévu dans la couverture d'arbre (6) une pluralité de décrochements (7), chacune des pointes d'aubes (4) étant associée à l'un des décrochements (7) qui est immédiatement adjacent à la pointe d'aube (4) correspondante et qui est dimensionné de manière que, dans le fonctionnement du turbocompresseur axial (1), chaque pointe d'aube (1) puisse plonger dans le décrochement (7) qui lui correspond sans que l'une des pointes d'aubes (4) touche de manière notable la couverture d'arbre (6).
EP10702467A 2009-02-13 2010-01-27 Turbocompresseur axial pour une turbine à gaz avec faibles pertes par les fentes radiales et les diffuseurs Withdrawn EP2396555A1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
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

Applications Claiming Priority (3)

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
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
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

Publications (1)

Publication Number Publication Date
EP2396555A1 true EP2396555A1 (fr) 2011-12-21

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 Before (1)

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

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)

Families Citing this family (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2961564B1 (fr) * 2010-06-17 2016-03-04 Snecma Compresseur et turbomachine a rendement optimise
EP2538031A1 (fr) * 2011-06-22 2012-12-26 Siemens Aktiengesellschaft Rotor avec élément d'étanchéité pour une turbine à gaz stationnaire
CN104074799B (zh) * 2013-11-17 2017-01-18 成都中科航空发动机有限公司 一种具有扩张型子午流道的轴流压气机及其设计方法
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
FR3133886B1 (fr) * 2022-03-24 2024-03-01 Safran Helicopter Engines Module pour turbomachine d’aéronef

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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
EP0536575B1 (fr) * 1991-10-08 1995-04-05 Asea Brown Boveri Ag Bande de recouvrement pour roue de turbine axiale
US5494404A (en) * 1993-12-22 1996-02-27 Alliedsignal Inc. Insertable stator vane assembly
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
US6409472B1 (en) * 1999-08-09 2002-06-25 United Technologies Corporation Stator assembly for a rotary machine and clip member for a stator assembly
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
US6619917B2 (en) * 2000-12-19 2003-09-16 United Technologies Corporation Machined fan exit guide vane attachment pockets for use in a gas turbine
US20060198726A1 (en) * 2005-03-07 2006-09-07 General Electric Company Apparatus for eliminating compressor stator vibration induced by tip leakage vortex bursting
EP2196629B1 (fr) * 2008-12-11 2018-05-16 Safran Aero Boosters SA Virole interne composite segmentée de redresseur de compresseur axial

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Also Published As

Publication number Publication date
JP5567036B2 (ja) 2014-08-06
CN102317634B (zh) 2014-06-25
EP2218918A1 (fr) 2010-08-18
US20110311355A1 (en) 2011-12-22
CN102317634A (zh) 2012-01-11
JP2012518109A (ja) 2012-08-09
WO2010091956A1 (fr) 2010-08-19

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