The Transonic Flow Through a Plane Turbine Cascade as Measured in Four European Wind Tunnels-Reference-Cited by-同舟云学术

The Transonic Flow Through a Plane Turbine Cascade as Measured in Four European Wind Tunnels

Published:1986-04-01 Issue:2 Volume:108 Page:277-284
ISSN:0742-4795
Container-title:Journal of Engineering for Gas Turbines and Power
language:en
Short-container-title:

Author:

Kiock R.¹,Lehthaus F.²,Baines N. C.³,Sieverding C. H.⁴

Affiliation:

1. Institute for Design Aerodynamics, DFVLR, Flughafen, D-3300 Braunschweig, West Germany

2. Institute for Experimental Fluid Mechanics, DFVLR, D-3400 Go¨ttingen, West Germany

3. Imperial College, Department of Mechanical Engineering, London SW7 2BX, United Kingdom

4. Von Karman Institute for Fluid Dynamics, B-1640 Rhode-St.-Gene`se, Belgium

Abstract

Reliable cascade data are esssential to the development of high-speed turbomachinery, but it has long been suspected that the tunnel environment influences the test results. This has now been investigated by testing one plane gas turbine rotor blade section in four European wind tunnels of different test sections and instrumentation. The Reynolds number of the transonic flow tests was Re2 = 8 × 105 based on exit flow conditions. The turbulence was not increased artificially. A comparison of results from blade pressure distributions and wake traverse measurements reveals the order of magnitude of tunnel effects.

Publisher

ASME International

Subject

Mechanical Engineering,Energy Engineering and Power Technology,Aerospace Engineering,Fuel Technology,Nuclear Energy and Engineering

Link

http://asmedigitalcollection.asme.org/gasturbinespower/article-pdf/108/2/277/5750285/277_1.pdf

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