EP2652337A1 - Compresseur axial - Google Patents

Compresseur axial

Info

Publication number
EP2652337A1
EP2652337A1 EP11791301.2A EP11791301A EP2652337A1 EP 2652337 A1 EP2652337 A1 EP 2652337A1 EP 11791301 A EP11791301 A EP 11791301A EP 2652337 A1 EP2652337 A1 EP 2652337A1
Authority
EP
European Patent Office
Prior art keywords
vane
vanes
stage
housing
adjacent
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Withdrawn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
EP11791301.2A
Other languages
German (de)
English (en)
Inventor
Marco Micheli
Wolfgang Kappis
Luis Federico Puerta
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.)
Ansaldo Energia IP UK Ltd
Original Assignee
Alstom Technology 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 Alstom Technology AG filed Critical Alstom Technology AG
Publication of EP2652337A1 publication Critical patent/EP2652337A1/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Withdrawn legal-status Critical Current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
    • F04D19/00—Axial-flow pumps
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/142—Shape, i.e. outer, aerodynamic form of the blades of successive rotor or stator blade-rows
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/12—Blades
    • F01D5/14—Form or construction
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • F01D5/146—Shape, i.e. outer, aerodynamic form of blades with tandem configuration, split blades or slotted blades
    • 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
    • F04D29/544—Blade shapes
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/34—Arrangement of components translated
    • 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
    • F05D2250/00—Geometry
    • F05D2250/30—Arrangement of components
    • F05D2250/38—Arrangement of components angled, e.g. sweep angle

Definitions

  • the invention relates to an axial compressor according to the preamble of claim 1.
  • Axial compressors are well known. It refers to
  • Vane rows provided to the fluid to be compressed on its way to the axially subsequent blade stage in an optimal
  • a stationary vane arrangement or cascade is provided in order to change the fluid caused by the rotor swirl flow of the fluid in a substantially axial
  • the invention is based on the recognition that aerodynamically optimized profiles of a multi-stage vane cascade behind the
  • Vane stage is arranged offset in the circumferential direction, such that caused by the vanes of the preceding stage vortex flags each flow between adjacent guide vanes of the subsequent vane stage.
  • the invention is based on the general idea of ensuring, in the case of stator vane stages arranged axially one behind the other, an as swirl-free as possible inflow in the downstream vanes.
  • the swirl vanes have a smaller distance from the convexly curved side of the one adjacent guide vane of the subsequent vane stage than from the concavely curved side of the other adjacent vane.
  • the housing of the axial compressor in a basically known manner from in
  • Context is advantageously provided to arrange a split inner wall segment at a parting plane between adjacent shell parts of the housing, in such a way that the parting plane between the segment parts coincides with the parting plane between the shell parts of the housing.
  • Fig. 1 is a schematic axial section of a conventional
  • Axial compressor with an outlet-side vane cascade which consists of so-called super-vanes,
  • Fig. 2 is a schematic axial section of an axial compressor with
  • Vane cascade a partial sectional view of a conventional two-stage vane cascade, wherein all blade profiles are shown relative to a rolled-up inner wall of the compressor housing
  • Fig. 4 is a corresponding to FIG. 3 representation of an inventive
  • Compressor housing in the area of the output side
  • a conventional axial compressor is shown. This has in a known manner a housing 1 with a rotor axis 2 to a substantially rotationally symmetrical inner wall 3.
  • the housing 1 encloses a rotor 4, which is axially between an input 5 for a to be compressed
  • Flow medium and an output 5 ' which usually leads to a combustion chamber, is arranged.
  • rotor-fixed blades 6 are arranged in a known manner, in each case in the circumferential direction of the rotor extended blade rows or blade stages. Between axially adjacent blade stages each fixed to the housing vanes 7 are arranged, in each case in
  • Circumferential direction of the housing inner wall 3 extended Leitschaufel Researchn or - stages.
  • Axial behind the rotor blade stage of the rotor 4 is a single-stage
  • Leitschaufelkaskade 8 two-stage with "normal" vanes 10 and 1 1 is constructed, which have a relatively little curved profile.
  • Figs. 3 and 4 show the differences of the invention over previous designs.
  • Fig. 3 the relative positions of the vanes 10 and 1 1 of a two-stage conventional vane cascade are shown.
  • the distances Ui and U2 have the same dimensions, so that it can be ensured by appropriate offset of the guide vanes 1 1 of the subsequent vane stage in the circumferential direction, that the vortex lugs 13 each between circumferentially adjacent vanes 1 1 pass.
  • each lower vanes 1 1 are passed.
  • a construction according to FIG. 5 is preferably provided.
  • the compressor housing is composed of shell parts, which are placed against each other, for example, at a parting plane 14.
  • the guide vanes 10 and 1 1 mounted in a conventional manner, for example, the feet ch 1 5 and 16 of the vanes 10 and 1 1 with molded-on anchors in
  • Circumferential direction are inserted into a formed in the inside of the respective shell part channel.
  • an inner wall segment is arranged in each case 1 7 or 1 8, which is dimensioned such that between the leading edges of the vanes 1 0 and 1 1, the evident from Fig. 4 radians Ui and U 2 , which have the same dimensions, are present.
  • each segmented wall segments with the segment parts 1 7 'and 1 7 "or 1 8' and 18" provided, wherein the respective segment parts 1 7 'and 1 7 "or 1 8' and 1 8" so be positioned so that its parting plane coincides with the parting plane 14 of the housing shell parts.
  • FIGS. 1 to 5 are also one or more of the rotor side
  • Blades 6 of the last blade stage shown schematically in profile, where R denotes the direction of rotation of the rotor 4.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne un compresseur axial comprenant une grille d'aube directrice à deux étages (8) sur l'extrémité côté sortie (5) du rotor (4). Les aubes directrices (11) du second étage de la grille sont décalées dans la direction périphérique par rapport aux aubes directrices (10) du premier étage, de telle manière que les traînées tourbillonnantes provoquées par les aubes directrices (10) du premier étage ne peuvent agir sur les aubes directrices (11) du second étage.
EP11791301.2A 2010-12-15 2011-12-07 Compresseur axial Withdrawn EP2652337A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CH02093/10A CH704212A1 (de) 2010-12-15 2010-12-15 Axialkompressor.
PCT/EP2011/072052 WO2012080053A1 (fr) 2010-12-15 2011-12-07 Compresseur axial

Publications (1)

Publication Number Publication Date
EP2652337A1 true EP2652337A1 (fr) 2013-10-23

Family

ID=43640279

Family Applications (1)

Application Number Title Priority Date Filing Date
EP11791301.2A Withdrawn EP2652337A1 (fr) 2010-12-15 2011-12-07 Compresseur axial

Country Status (11)

Country Link
US (1) US9810226B2 (fr)
EP (1) EP2652337A1 (fr)
JP (1) JP5818908B2 (fr)
CN (1) CN103354875B (fr)
AU (1) AU2011344469B2 (fr)
BR (1) BR112013015252A2 (fr)
CA (1) CA2821142C (fr)
CH (1) CH704212A1 (fr)
MX (1) MX336210B (fr)
RU (1) RU2564386C2 (fr)
WO (1) WO2012080053A1 (fr)

Families Citing this family (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP2698502A1 (fr) 2012-08-13 2014-02-19 Alstom Technology Ltd Procédé de mesure du jeu à froid des extrémités d'aubes d'une turbomachine et agencement de mesures du jeu des extrémités pour l'exécution de ce procédé
ITMI20130791A1 (it) * 2013-05-14 2014-11-15 Cofimco Srl Ventilatore assiale
FR3019879A1 (fr) * 2014-04-09 2015-10-16 Turbomeca Moteur d'aeronef comprenant un calage azimutal du diffuseur, par rapport a la chambre de combustion
EP3190269A1 (fr) * 2016-01-11 2017-07-12 United Technologies Corporation Étage à sillage de faible énergie
US10502220B2 (en) 2016-07-22 2019-12-10 Solar Turbines Incorporated Method for improving turbine compressor performance
AU2016277549B2 (en) * 2016-10-24 2018-10-18 Intex Holdings Pty Ltd A multi-stage axial flow turbine adapted to operate at low steam temperatures
US20180313364A1 (en) * 2017-04-27 2018-11-01 General Electric Company Compressor apparatus with bleed slot including turning vanes
WO2019204265A1 (fr) * 2018-04-17 2019-10-24 Cummins Filtration Ip, Inc. Ensemble de séparation comprenant une turbine à impulsion à deux pièces
CN109083849B (zh) * 2018-08-14 2020-06-09 成都市弘盛科技有限公司 一种轴流压气机
WO2023216742A1 (fr) * 2022-05-09 2023-11-16 追觅创新科技(苏州)有限公司 Support de ventilateur, moteur électrique et soufflante

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB628263A (en) * 1943-06-01 1949-08-25 Louis Breguet Improvements in or relating to axial flow compressors
US2798661A (en) * 1954-03-05 1957-07-09 Westinghouse Electric Corp Gas turbine power plant apparatus
US4011028A (en) * 1975-10-16 1977-03-08 Anatoly Nikolaevich Borsuk Axial-flow transsonic compressor
SU1366722A1 (ru) * 1985-04-15 1988-01-15 Университет дружбы народов им.Патриса Лумумбы Двухр дный лопаточный аппарат осевого компрессора
JPS6245397A (ja) 1985-08-23 1987-02-27 Hitachi Plant Eng & Constr Co Ltd 汚水処理装置
JPS6245397U (fr) * 1985-09-06 1987-03-19
US4874289A (en) * 1988-05-26 1989-10-17 United States Of America As Represented By The Secretary Of The Air Force Variable stator vane assembly for a rotary turbine engine
US4981414A (en) * 1988-05-27 1991-01-01 Sheets Herman E Method and apparatus for producing fluid pressure and controlling boundary layer
EP1674734A1 (fr) * 2004-12-21 2006-06-28 ALSTOM Technology Ltd Méthode d' amélioration de la stabilité de courant d' une turbomachine
EP2194234A1 (fr) * 2008-12-03 2010-06-09 Siemens Aktiengesellschaft Anneau d'isolation thermique pour contrôle passif de jeu dans une turbine à gaz
US8087249B2 (en) * 2008-12-23 2012-01-03 General Electric Company Turbine cooling air from a centrifugal compressor
EP2218876A1 (fr) * 2009-02-16 2010-08-18 Siemens Aktiengesellschaft Bague d'étanchéité destinée à rendre étanche un jeu radial dans une turbine à gaz
DE102009013399A1 (de) 2009-03-16 2010-09-23 Mtu Aero Engines Gmbh Tandemschaufelkonstruktion
DE102009023100A1 (de) * 2009-05-28 2010-12-02 Rolls-Royce Deutschland Ltd & Co Kg Strömungsmaschine mit einer Schaufelreihengruppe mit meridionalem Kantenabstand

Also Published As

Publication number Publication date
MX2013006789A (es) 2013-10-01
JP5818908B2 (ja) 2015-11-18
RU2013132197A (ru) 2015-01-20
JP2014503736A (ja) 2014-02-13
CN103354875A (zh) 2013-10-16
AU2011344469B2 (en) 2015-06-25
RU2564386C2 (ru) 2015-09-27
US20130280053A1 (en) 2013-10-24
AU2011344469A1 (en) 2013-07-11
CH704212A1 (de) 2012-06-15
CA2821142C (fr) 2015-11-24
US9810226B2 (en) 2017-11-07
BR112013015252A2 (pt) 2016-09-13
CN103354875B (zh) 2016-08-24
MX336210B (es) 2016-01-11
CA2821142A1 (fr) 2012-06-21
WO2012080053A1 (fr) 2012-06-21

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