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research-article

EXPERIMENTAL EVIDENCE OF TEMPERATURE RATIO EFFECT ON TURBINE BLADE TIP HEAT TRANSFER

[+] Author and Article Information
Hongmei Jiang

University of Michigan-Shanghai Jiao Tong University Joint Institute, Shanghai Jiao Tong University, Shanghai, China
jianghm188@163.com

Qiang Zhang

City University London, London, UK
qiang.zhang.1@city.ac.uk

Li He

University of Oxford, Oxford, UK
li.he@eng.ox.ac.uk

Shaopeng Lu

School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai, China
lusp@sjtu.edu.cn

Lipo Wang

University of Michigan-Shanghai Jiao Tong University Joint Institute, Shanghai Jiao Tong University, Shanghai, China
lipo.wang@sjtu.edu.cn

Jinfang Teng

School of Aeronautics and Astronautics, Shanghai Jiao Tong University, Shanghai, China
tjf@sjtu.edu.cn

1Corresponding author.

ASME doi:10.1115/1.4041811 History: Received January 25, 2018; Revised October 17, 2018

Abstract

Determination of a scalable Nusselt numberhas been the main research objective of most existing heat transfer experimental researches for turbine blade tip. They were mostly carried out at near adiabatic condition without matching the engine realistic wall-to-gas low Temperature Ratio (TR). This practice is based on the assumption that the wall thermal boundary conditions do not affect the over-tip-leakage (OTL) flow field, the aerodynamics and heat transfer can be studied separately. Recent numerical studies raised a question on the validity of this conventional practice. Due to the relatively low thermal inertia of the leakage fluids contained within the thin clearance, the fluids transport properties vary greatly with the wall thermal boundary condition and the two-way coupling between OTL aerodynamics and heat transfer cannot be neglected. The issue could become more severe when the gas turbine manufacturers are making effort to achieve much tighter clearance. However, there has been no experimental evidence to back up these numerical findings. In this study, transient thermal measurements were conducted in a high-temperature linear cascade rig for a range of tip clearances. Surface temperature history was captured by Infrared Thermography at a range of wall-to-gas TRs. Heat Transfer Coefficient (HTC) distributions were obtained based on a conventional data processing technique. The profound influence of tip surface thermal boundary condition on heat transfer and OTL flow was revealed by the first-of-its-kind experimental data obtained in the present study.

Copyright (c) 2018 by ASME
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