EP1330607A1 - Turbocompresseur a ecoulement axial - Google Patents

Turbocompresseur a ecoulement axial

Info

Publication number
EP1330607A1
EP1330607A1 EP01983877A EP01983877A EP1330607A1 EP 1330607 A1 EP1330607 A1 EP 1330607A1 EP 01983877 A EP01983877 A EP 01983877A EP 01983877 A EP01983877 A EP 01983877A EP 1330607 A1 EP1330607 A1 EP 1330607A1
Authority
EP
European Patent Office
Prior art keywords
rotor
flow
rotor blade
section
axial
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Withdrawn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
EP01983877A
Other languages
German (de)
English (en)
Inventor
Rolf Alexis Jacobsson
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.)
Atlas Copco Industrial Technique AB
Original Assignee
Atlas Copco Tools AB
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 Atlas Copco Tools AB filed Critical Atlas Copco Tools AB
Publication of EP1330607A1 publication Critical patent/EP1330607A1/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Withdrawn legal-status Critical Current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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow 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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/321—Rotors specially for elastic fluids for axial flow pumps for axial flow compressors
    • F04D29/324—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
    • F04D19/00—Axial-flow pumps
    • F04D19/02—Multi-stage 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
    • F04D29/544—Blade shapes

Definitions

  • the invention relates to a turbo compressor of the axial flow type comprising a stator with at least one axial section including a circumferential array of flow directing guide vanes and a rotor with at least one axial section including a circumferential array of rotor blades, wherein between the guide vanes and the rotor blades and between an inner peripheral wall and an outer peripheral wall there are formed parallel flow paths, and between successive rotor blades there are formed rotor flow passages through which the flow paths extend.
  • the main object of the invention is to accomplish a compressor of the above type working at subsonic air flow velocities and where the air flow passages through the compressor are improved in such a way that the mean air flow velocity through the stator and rotor sections may be increased considerably without risking the Mach number reaching the 1,0 level.
  • Fig. 1 shows the geometry of the flow path through a rotor blade passage.
  • Fig. 2 shows a side view of the rotor blade passage of Fig.
  • FIG. 3 shows a fractional longitudinal section through a compressor according to the invention.
  • Fig. 4 shows a spread-out view of the rotor blades and stator guide vanes of the compressor illustrated in Fig. 1.
  • Fig. 1 there is illustrated a flow path relative to the rotor which extends through a passage between two successive rotor blades A and B.
  • the medium flow is deflected in a direction opposite the movement direction ⁇ of the rotor blades by an angle ⁇ x , which is the difference between the original flow path angle ⁇ x and the new flow path angle ⁇ _ .
  • This deflection of the flow causes a sidewise contraction of the flow path and follows a curvature which may be theoretically calculated via a well recognised method, see for instance: Eckert/Schnell "Axial- und Radialkompressoren” , 2:nd edition, page 264, or "Dubbel Taschenbuch fur den Maschinenbau” , 1974, page 334.
  • the curvature has a shape which is close to a circle line with a radius R.
  • the diffusor region C When reaching a section a 2 at a certain distance upstream of the leading edge of the second rotor blade B or slightly downstream of the leading edge of the first rotor blade A the flow path passes through a diffusor region C which extends in the flow direction to a section a 3 approximately at the leading edge of the second rotor blade B. Accordingly, the diffusor region C has an entrance section a 2 and an exit section a 3 , wherein the entrance section a 2 has a cross sectional area which is smaller than that of the exit section a 3 .
  • the entrance section a 2 of the diffusor region C is also the narrowest cross section of the entire flow path between a x and a 4 .
  • the flow path Downstream of the diffusor region C, the flow path extends through a transition region D which has a substantially non-increasing or slightly .decreasing cross sectional area all the way from section a 3 to an exit section a 4 .
  • the radial extent of the rotor blades i.e. the radial distance between the inner peripheral wall 28 and the outer peripheral wall 29, has to be reduced so as to keep the cross sectional area substantially constant throughout the transition region D. See Fig. 2. In some cases it might be advantageous to have a slight acceleration of the flow through the transition region D.
  • the flow path Upstream of the diffusor region C, the flow path has a substantially constant cross sectional area, from an initial section a x to the diffusor region entrance section a 2 so as to generate a non-increasing flow velocity. As illustrated in Fig. 2, this is accomplished by forming the inner and/or the outer peripheral walls 28,29 of the rotor and the stator, respectively, with diverging surfaces F and G. These diverging surfaces F, G compensate for the sidewise contraction of the flow path, as described above, and serves to keep down the Mach-number of the flow velocity and prevent shock waves to occur in the medium flow.
  • each guide vane 10 has a different flow deflection angle at its top end compared to its bottom end. See Fig. 4. Thereby, there is obtained optimum flow directions for generating an equal flow velocity at all radial locations on each rotor blade in the initial compressor stage.
  • FIGs. 3 and 4 there is illustrated a preferred embodiment of the invention including the flow path characteristics illustrated in Fig. 1.
  • FIG. 3 there is shown a sectional view of an inlet nozzle for the initial stage of the compressor including guide vanes 10 rigidly mounted in a housing 11. Downstream of the nozzle 10 there is a rotor section 12 with a rotor blade 13 followed by a stator section 14 having a guide vane 15 secured to the housing 11, and another rotor section 16 with a rotor blade 17.
  • Rotor flow paths 20 extend between two adjacent rotor blades 13,17, and stator flow paths 21 are formed between two adjacent guide vanes 15.
  • the flow paths 20, 21 are also defined by an inner peripheral surface 28 and an outer peripheral surface 29.
  • annular air flow passages 22, 23 and 24 Between the stator sections and the rotor sections there are provided axial gaps which form annular air flow passages 22, 23 and 24.
  • the main character of the air flow passage through the compressor is successively converging from the inlet nozzle end toward the outlet end. As illustrated in Fig. 3, the cross sectional area of the air passage decreases step- wise. In the air flow paths 20 between the rotor blades 13 as well as the flow paths between the guide vanes 15 the radial extent of the flow passage decreases, whereas in the flow passages 22, 23 and 24 located between the stator sections 14 and the rotor sections 12 the radial extent of the flow passage increases.
  • a characteristic feature of the invention is the provision of the axial gaps between the stator and rotor sections forming the flow passages 22, 23 and 24. The reason for introducing these axially extended and radially diverging passages 22, 23 and 24 is to accomplish a velocity reducing diffusor region with the purpose to reduce flow losses and increase the compressor efficiency.
  • an air flow approaching the rotor flow path 20 between two rotor blades 13,17 has a converging shape, because depending on a difference in direction between the incoming air flow and the direction of the rotor blades 13,17, the air flow has to change direction.
  • the direction of the incoming air flow path forms an angle to a radial plane and is denoted ⁇ x . This angle is larger than the angle of the rotor blades 13,17, which is denoted ⁇ . Due to this change in flow direction, the air flow path is subjected to a tangential contraction, which causes an increased flow velocity.
  • This undesirable acceleration of the air flow is omitted by increasing the available cross sectional area in the flow passage, i.e. by the introduction of the intermediate and radially diverging flow passages 22, 23 and 24.
  • the increase in the radial extent of the flow passages 22, 23 and 24 should be at least 20%.
  • the radial extent of the passages increases from h x at the entrance to h 2 at the exit end.
  • the increase in radial extent of the intermediate passages 22, 23 and 24 has to be accomplished over a certain passage length.
  • the passages 22, 23 and 24 should have an axial length exceeding 30% of the rotor blade and guide vane length, respectively.
  • the passage length could be 50% or more of the length of the blades and vanes, respectively.

Landscapes

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

Abstract

L'invention concerne un turbocompresseur à écoulement axial comprenant une ou plusieurs parties stator espacées axialement (14) ayant chacune un réseau circonférentiel d'aubes directrices (15), et une ou plusieurs parties rotor (12, 16) ayant chacune un réseau circonférentiel d'ailettes de rotor (13, 17; A, B). Entre les ailettes de rotor successives (A, B), on trouve des chemins d'écoulement, tandis qu'entre les parties stator et rotor, on trouve des espaces axiaux (22, 23, 24) dont la configuration diverge, de façon à former dans chaque chemin d'écoulement, une zone de diffusion (C) qui s'étend de la section transversale la plus étroite (a2) du chemin d'écoulement situé à une certaine distance en amont du bord d'attaque d'une seconde ailette de rotor (B) à une section transversale plus large (a3) située approximativement sur le bord d'attaque de la seconde ailette de rotor (B), chaque chemin d'écoulement comprenant une zone de transition (D) d'une zone de section transversale n'augmentant sensiblement pas qui s'étend de la section transversale plus large (a3) aux bords arrière des ailettes de rotor (A, B).
EP01983877A 2000-11-02 2001-11-02 Turbocompresseur a ecoulement axial Withdrawn EP1330607A1 (fr)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
SE0004001 2000-11-02
SE0004001A SE0004001D0 (sv) 2000-11-02 2000-11-02 Axial flow compressor
PCT/SE2001/002409 WO2002036965A1 (fr) 2000-11-02 2001-11-02 Turbocompresseur a ecoulement axial

Publications (1)

Publication Number Publication Date
EP1330607A1 true EP1330607A1 (fr) 2003-07-30

Family

ID=20281668

Family Applications (1)

Application Number Title Priority Date Filing Date
EP01983877A Withdrawn EP1330607A1 (fr) 2000-11-02 2001-11-02 Turbocompresseur a ecoulement axial

Country Status (9)

Country Link
US (1) US20050175448A1 (fr)
EP (1) EP1330607A1 (fr)
JP (1) JP2004520517A (fr)
KR (1) KR20030063369A (fr)
CN (1) CN1481479A (fr)
AU (1) AU2002215273A1 (fr)
CA (1) CA2427600A1 (fr)
SE (1) SE0004001D0 (fr)
WO (1) WO2002036965A1 (fr)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102004036594A1 (de) * 2004-07-28 2006-03-23 Mtu Aero Engines Gmbh Strömungsstruktur für eine Gasturbine
PL2126367T3 (pl) * 2007-01-17 2014-07-31 Ansaldo Energia Spa Wielostopniowa sprężarka układu turbogazowego
KR101059086B1 (ko) * 2011-03-18 2011-08-24 (주)대주기계 공기 압축기 용량 조절용 가변 목 장치
SE537871C2 (sv) * 2011-12-13 2015-11-03 Xylem Ip Holdings Llc Propellerpump samt pumpstation
EP2696042B1 (fr) * 2012-08-09 2015-01-21 MTU Aero Engines GmbH Turbomachine avec au moins un stator
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
US11428241B2 (en) * 2016-04-22 2022-08-30 Raytheon Technologies Corporation System for an improved stator assembly
TWI678471B (zh) * 2018-08-02 2019-12-01 宏碁股份有限公司 散熱風扇

Family Cites Families (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CH216489A (de) * 1940-04-04 1941-08-31 Sulzer Ag Mehrstufiger Axialverdichter.
US2846137A (en) * 1955-06-03 1958-08-05 Gen Electric Construction for axial-flow turbomachinery

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See references of WO0236965A1 *

Also Published As

Publication number Publication date
SE0004001D0 (sv) 2000-11-01
CA2427600A1 (fr) 2002-05-10
CN1481479A (zh) 2004-03-10
JP2004520517A (ja) 2004-07-08
WO2002036965A1 (fr) 2002-05-10
KR20030063369A (ko) 2003-07-28
US20050175448A1 (en) 2005-08-11
AU2002215273A1 (en) 2002-05-15

Similar Documents

Publication Publication Date Title
US6419448B1 (en) Flow by-pass system for use in steam turbine exhaust hoods
US5203674A (en) Compact diffuser, particularly suitable for high-power gas turbines
US20100014956A1 (en) Fluid flow machine featuring a groove on a running gap of a blade end
MXPA02002479A (es) Sistema desturbulenciador para compresor centrifugo.
GB2245312A (en) Axial flow compressor surge margin improvement
JPH07259796A (ja) 遠心圧縮機
EP2582918B1 (fr) Diffuseur annulaire d'une turbine a gaz
EP3483395B1 (fr) Conduits inter-turbine comportant des mécanismes de régulation d'écoulement
CA2927037C (fr) Assemblage de rotor dote de godet
CA2927035C (fr) Assemblage de rotor dote d'un element d'usure
CA2165863A1 (fr) Distributeur supersonique pour l'admission d'une turbomachine
JPH0610610A (ja) タービンブレード組立体
US6312221B1 (en) End wall flow path of a compressor
US6705834B1 (en) Axial flow turbine type rotor machine for elastic fluid operation
US20050175448A1 (en) Axial flow turbo compressor
CN112334665A (zh) 用于制冷系统的混流式压缩机构造
EP3354848B1 (fr) Conduits inter-turbine avec de multiples pales séparatrices
CN110418896B (zh) 回引级和径流式涡轮流体能量机械
JP5232721B2 (ja) 遠心圧縮機
JPH09203394A (ja) 多段遠心圧縮機のリターンベーン
JPH01318790A (ja) 多段ポンプの水返し羽根
JPH01247798A (ja) 高速遠心圧縮機
KR20210128386A (ko) 다단 원심 유체 기계
CN110778532A (zh) 用于涡轮发动机压气机的气隙翅片
US11434773B2 (en) Secondary flow rectifier with integrated pipe

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20030516

AK Designated contracting states

Designated state(s): AT BE CH CY DE DK ES FI FR GB GR IE IT LI LU MC NL PT SE TR

RBV Designated contracting states (corrected)

Designated state(s): DE FR GB IT SE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: THE APPLICATION IS DEEMED TO BE WITHDRAWN

18D Application deemed to be withdrawn

Effective date: 20060601