Adiabatic Wall Temperature Evaluation in a High Speed Turbine-Reference-Cited by-同舟云学术

Adiabatic Wall Temperature Evaluation in a High Speed Turbine

Published:2012-07-09 Issue:9 Volume:134 Page:
ISSN:0022-1481
Container-title:Journal of Heat Transfer
language:en
Short-container-title:

Author:

Pinilla V.¹,Solano J. P.¹,Paniagua G.¹,Anthony R. J.²

Affiliation:

1. von Karman Institute for Fluid Dynamics, Turbomachinery and Propulsion Department, Chaussée de Waterloo 72, 1640 Rhode Saint Genèse, Belgium

2. Air Force Research Laboratory, Propulsion Directorate, Wright Patterson Air Force Base, OH 45433

Abstract

Engine development requires accurate estimates of the heat loads. Estimates of the convective heat fluxes are particularly vital to assess the thermomechanical integrity of the turbomachinery components. This paper reports an experimental heat transfer research in a one and a half turbine stage, composed of a high-pressure turbine and a low-pressure vane. Measurements were performed in a compression tube facility at the von Karman Institute, able to reproduce engine representative Reynolds and Mach numbers. Double-layered thin film gauges were used to monitor the time-dependent temperature distribution around the airfoil. Several tests at different metal temperatures were performed to derive the adiabatic wall temperature. This research allowed quantifying the independent effects on the unsteady heat flux of the gas temperature fluctuations and boundary layer unsteadiness.

Publisher

ASME International

Subject

Mechanical Engineering,Mechanics of Materials,Condensed Matter Physics,General Materials Science

Link

http://asmedigitalcollection.asme.org/heattransfer/article-pdf/doi/10.1115/1.4006313/5917666/091601_1.pdf

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