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research-article

Investigation of thermal effect on bypass transition on a high-pressure turbine guide vane

[+] Author and Article Information
Tânia S. Cação Ferreira

Jacques Chauvin Laboratory, Turbomachinery and Propulsion Department, von Karman Institute for Fluid Dynamics, B1640 Rhode-Saint-Genèse, Belgium
cacao@vki.ac.be

Nikolaos Vasilakopoulos

Jacques Chauvin Laboratory, Turbomachinery and Propulsion Department, von Karman Institute for Fluid Dynamics, B1640 Rhode-Saint-Genèse, Belgium
nvasilakopoulos@gmail.com

Dr. Tony Arts

Jacques Chauvin Laboratory, Turbomachinery and Propulsion Department, von Karman Institute for Fluid Dynamics, B1640 Rhode-Saint-Genèse, Belgium
arts@vki.ac.be

1Corresponding author.

ASME doi:10.1115/1.4041909 History: Received October 17, 2018; Revised October 30, 2018

Abstract

The role of gas-to-wall temperature ratio on bypass transition along a highly loaded turbine guide vane is investigated through time-resolved heat flux measurements for different flow conditions. The tests are conducted in the von Karman Institute (VKI) isentropic compression tube (CT-2) facility. High response thin films mounted on the vane (VKI LS89 airfoil) coupled with analog circuits are used for the heat flux measurements. The first detectable wall heat flux fluctuations denote the onset of transition which is also evaluated by both the heat transfer coefficient and the intermittency factor distributions along the suction side. The exit Mach number is kept constant during each test by means of a downstream sonic throat while the gas-to-wall temperature ratio is varied from 1.14 to 1.51 by changing the inlet gas temperature. Four test cases are considered for different exit Mach numbers (0.52 and 0.86) and freestream turbulence intensity levels (0.8% and 5.3%) while the isentropic exit chord Reynolds number is maintained at 10^6 . In the present test campaign, the length and the evolution of the phenomenon indicate a measurable effect of the gas-to-wall temperature ratio for test cases with mild pressure gradients.

Copyright (c) 2018 by ASME
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