The nature of wakes in multistage axial flow compressors

Abstract

This paper describes the measurement and processing of unsteady turbulence data from a multistage low-speed compressor. In this study, a two-element hot-wire probe was traversed along a circumferential path downstream of the third rotor row of a large-scale low-speed four-stage facility. Simultaneous circumferential and axial velocity measurements were made. Three flow conditions were measured: peak efficiency with blade Re = 200000. peak efficiency with blade Re = 55 000 and close to stall with blade Re = 200 000. Ensemble averaging has been used to deduce the periodic components of the velocity. In addition, measurements have been made of turbulence intensity, turbulence length scale and turbulent shear stress (Reynolds stress).

Keywords

wakes multistage axial flow compressors unsteady turbulence

Get full access to this article

View all access options for this article.

References

Swoboda

Ivey

P. C.

Wenger

Gummer

An experimental examination of cantilevered and shrouded stators in a multistage axial compressor. In Proceedings of the International Gas Turbine and Aeroengine Congress and Exhibition, June 1998; ASME paper 98-GT-282, 1998.

Azimian

Elder

R. L.

Cross hot wire calibration with emphasis on support effects. Research report TR/87/8, Cranfield Institute of Technology, June 1987.

Hodson

H. P.

Hot wire theory and computer programs. Report, Whittle Laboratories, April 1985.

Addison

J. S.

Hodson

H. P.

Unsteady transition in an axial-flow turbine. Part 1: measurements on the turbine rotor. J. Turbomachinery, April 1990, 12, 206–214; ASME paper 89-GT-289, 1989.

Read

Transition to turbulence in a turbomachinery environment. PhD thesis, University of Cranfield, August 1997.

Andrew

P. L.

W.-F.

Turbulence characteristics in a supersonic cascade wake flow. J. Turbomachinery October 1994, 116, 586–596; ASME paper 93-GT-348, 1993.

Deutsch

Zierke

W. C.

The measurement of boundary layers on a compressor blade in cascade. Part 3: pressure surface boundary layers and the near wake. J. Turbomachinery January 1988, 110, 146–152; ASME paper 87-GT-250, 1987.

Shreeve

R. P.

Elazar

Dreon

J. W.

Baydar

Wake measurements and loss evaluation in a controlled-diffusion compressor cascade. J. Turbomachinery, October 1991, 113, 591–599; ASME paper 90-GT-129, 1990.

Stauter

R. C.

Dring

R. P.

Carta

F. O.

Temporally and spatially resolved flow in a two-stage axial compressor. Part 1: experiment. J. Turbomachinery, April 1991, 113, 219–226; ASME paper 90-GT-259, 1990.

10.

Gundy-Burlet

K. L.

Rai

M. M.

Stauter

R. C.

Dring

R. P.

Temporally and spatially resolved flow in a two-stage axial compressor. Part 2: computational assessment. J. Turbomachinery, April 1991, 113, 227–232; ASME paper 90-GT-299, 1990.

11.

Y. H.

Lakshminarayana

Computation of unsteady viscous flow through turbomachinery blade row due to upstream rotor wakes. J. Turbomachinery, October 1995, 117, 541–552; ASME paper 93-GT-321, 1993.