An Investigation of Boundary Layer Development in a Multistage LP Turbine

[+] Author and Article Information
H. P. Hodson, I. Huntsman

Whittle Laboratory, Cambridge University, Cambridge, United Kingdom

A. B. Steele

Rolls-Royce plc, Derby, United Kingdom

J. Turbomach 116(3), 375-383 (Jul 01, 1994) (9 pages) doi:10.1115/1.2929424 History: Received March 12, 1993; Online June 09, 2008


This paper describes an investigation of the behavior of suction surface boundary layers in a modern multistage Low-Pressure turbine. An array of 18 surface-mounted hot-film anemometers was mounted on a stator blade of the third stage of a four-stage machine. Data were obtained at Reynolds numbers between 0.9 × 105 and 1.8 × 105 . At the majority of the test conditions, wakes from upstream rotors periodically initiated transition at about 40 percent surface length. In between these events, laminar separation occurred at about 75 percent surface length. Because the wake-affected part of the flow appeared to be only intermittently turbulent, laminar separation also occurred at about 75 percent surface length while this flow was instantaneously laminar. At all but the lowest Reynolds numbers, the time-mean boundary layer appeared to have re-attached by the trailing edge even though it was not fully turbulent. It is inferred that the effect of the wakes on the performance of the blade row is limited and that steady flow design methods should provide an adequate assessment of LP turbine performance during design.

Copyright © 1994 by The American Society of Mechanical Engineers
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