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Flow With Shock Waves in a Transonic Centrifugal Compressor With a Low-Solidity Cascade Diffuser Using PIV

[+] Author Affiliations
Hiroshi Hayami, Shinichiro Aramaki

Kyushu University, Fukuoka, Japan

Masahiro Hojo

Japan Aerospace Exploration Agency

Norifumi Hirata

Mitsubishi Heavy Industries, Ltd.

Paper No. GT2004-53268, pp. 709-716; 8 pages
doi:10.1115/GT2004-53268
From:
  • ASME Turbo Expo 2004: Power for Land, Sea, and Air
  • Volume 5: Turbo Expo 2004, Parts A and B
  • Vienna, Austria, June 14–17, 2004
  • Conference Sponsors: International Gas Turbine Institute
  • ISBN: 0-7918-4170-7 | eISBN: 0-7918-3739-4
  • Copyright © 2004 by ASME

abstract

A single-stage transonic centrifugal compressor with a pressure ratio greater than six was tested in a closed loop with HFC134a gas. Flow at the inducer of a rotating impeller as well as flow in a stationary low-solidity cascade diffuser was measured using a double-pulse and double-frame particle image velocimetry (PIV). Shock waves in both flows were clearly observed. The effect of flow rate on a 3D configuration of shock wave at the inducer and a so-called rotor-stator interaction between a rotating impeller and a stationary cascade were discussed based on a phase-averaged measurement technique. Furthermore, the unsteadiness of inducer shock wave and the flow in a cascade diffuser during surge were discussed based on instantaneous velocity vector maps.

Copyright © 2004 by ASME

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