Three-dimensional flow near the blade/endwall junction of a gas turbine: application of a boundary layer fence

J. T. Chung, T. W. Simon, J. Buddhavarapu

Research output: Contribution to journalConference articlepeer-review

22 Scopus citations

Abstract

A flow management technique designed to reduce some harmful effects of secondary flow in the endwall region of a turbine passage is introduced. A boundary layer fence in the gas turbine passage is shown to improve the likelihood of efficient film cooling on the suction surface near the endwall. The fence prevents the pressure side leg of the horseshoe vortex from crossing to the suction surface and impinging on the wall. The vortex is weakened and decreased in size after being deflected by the fence. Such diversion of the vortex will prevent it from removing the film cooling flow allowing the flow of perform its cooling function. Flow visualization on the suction surface and through the passage shows the behavior of the passage vortex with and without the fence. Laser Doppler velocimetry is employed to quantify these observations.

Original languageEnglish (US)
JournalAmerican Society of Mechanical Engineers (Paper)
StatePublished - Jan 1 1991
EventInternational Gas Turbine and Aeroengine Congress and Exposition - Orlando, FL, USA
Duration: Jun 3 1991Jun 6 1991

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