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Influence of unsteady effects on the measurements in a transonic axial compressor

Identifieur interne : 000A97 ( PascalFrancis/Curation ); précédent : 000A96; suivant : 000A98

Influence of unsteady effects on the measurements in a transonic axial compressor

Auteurs : J. Paulon [France] ; ZHIFANG ZHANG ; PINGFANG JIA ; JINGFEI MENG

Source :

RBID : Pascal:92-0537689

Descripteurs français

English descriptors

Abstract

Interaction phenomena between rotor and stator are unavoidable in advanced compressors and their effects increase with the performance of the turbomachines. Until now, it was not possible to quantify the interaction effects, but with the development of three-dimensional unsteady computation codes in a complete stage, it is possible to know, in detail, the flow field through the machine and to make evident and to explain the difficulties encountered in measuring the flow parameters. A study has been conducted in this way at OPERA, on an axial transonic compressor stage
pA  
A01 01  1    @0 0889-504X
A02 01      @0 JOTUEI
A03   1    @0 J. turbomach.
A05       @2 114
A06       @2 3
A08 01  1  ENG  @1 Influence of unsteady effects on the measurements in a transonic axial compressor
A11 01  1    @1 PAULON (J.)
A11 02  1    @1 ZHIFANG ZHANG
A11 03  1    @1 PINGFANG JIA
A11 04  1    @1 JINGFEI MENG
A14 01      @1 Office national études rech. aérospatiales @2 Châtillon 92322 @3 FRA
A20       @1 510-516
A21       @1 1992
A23 01      @0 ENG
A43 01      @1 INIST @2 6120 A2 @5 354000020398410050
A44       @0 0000
A45       @0 11 ref.
A47 01  1    @0 92-0537689
A60       @1 P @2 C
A61       @0 A
A64   1    @0 Journal of turbomachinery
A66 01      @0 USA
C01 01    ENG  @0 Interaction phenomena between rotor and stator are unavoidable in advanced compressors and their effects increase with the performance of the turbomachines. Until now, it was not possible to quantify the interaction effects, but with the development of three-dimensional unsteady computation codes in a complete stage, it is possible to know, in detail, the flow field through the machine and to make evident and to explain the difficulties encountered in measuring the flow parameters. A study has been conducted in this way at OPERA, on an axial transonic compressor stage
C02 01  X    @0 001D12G
C03 01  X  FRE  @0 Turbomachine
C03 01  X  ENG  @0 Turbomachine
C03 01  X  SPA  @0 Turbomáquina
C03 02  X  FRE  @0 Compresseur axial
C03 02  X  ENG  @0 Axial compressor
C03 02  X  SPA  @0 Compresor axial
C03 03  X  FRE  @0 Ecoulement transsonique
C03 03  X  ENG  @0 Transonic flow
C03 03  X  SPA  @0 Flujo transónico
C03 04  X  FRE  @0 Distribution pression
C03 04  X  ENG  @0 Pressure distribution
C03 04  X  SPA  @0 Distribución presión
C03 05  X  FRE  @0 Nombre Mach
C03 05  X  ENG  @0 Mach number
C03 05  X  SPA  @0 Número Mach
C03 06  X  FRE  @0 Champ température
C03 06  X  ENG  @0 Temperature distribution
C03 06  X  SPA  @0 Campo temperatura
C03 07  X  FRE  @0 Rotor
C03 07  X  ENG  @0 Rotor
C03 07  X  SPA  @0 Rotor
C03 08  X  FRE  @0 Stator
C03 08  X  ENG  @0 Stator
C03 08  X  SPA  @0 Estator
C03 09  X  FRE  @0 Aubage
C03 09  X  ENG  @0 Blades
C03 09  X  SPA  @0 Alabe
N21       @1 300
pR  
A30 01  1  ENG  @1 International gas turbine and aeroengine congress and exposition @2 36 @3 Orlando FL USA @4 1991-06-03

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Pascal:92-0537689

Le document en format XML

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