Flowfield Calculation in Compressor Operating With Distorted Inlet Flow PUBLIC ACCESS

[+] Author Affiliations
H. Joubert

SNECMA Villaroche, Moissy-Cramayel, France

Paper No. 90-GT-212, pp. V001T01A065; 10 pages
  • ASME 1990 International Gas Turbine and Aeroengine Congress and Exposition
  • Volume 1: Turbomachinery
  • Brussels, Belgium, June 11–14, 1990
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 978-0-7918-7904-7
  • Copyright © 1990 by ASME


In order to improve the air inlet engine compatibility, SNECMA has carried out since several years an important effort to predict the effect of distorted inlet flow on compressor stability.

Two different methods are developed:

In the first one, the Euler equations are integrated in 2D blade to blade surface with a distorted inlet flow. This method is used to compare different profiles, in particular influence of the chord length is presented.

In the second one, the aerodynamic behaviour of a multistage compressor operating in distorted inlet flow is calculated with a three dimensional method. This model is based on Euler equations resolution outside the rows.

An actuator disk model is used to represent the response of the blade rows.

The behaviour of a three stage axial compressor has been studied. The loss of surge margin and the pressure distortion transfer are compared with experimental data.

Copyright © 1990 by ASME
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