Transient experimental study on cooling performance of a radial turbine with impingement cooling in rotating state-Reference-Cited by-同舟云学术

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Transient experimental study on cooling performance of a radial turbine with impingement cooling in rotating state

Published:2024-08 Issue: Volume:151 Page:109321
ISSN:1270-9638
Container-title:Aerospace Science and Technology
language:en
Short-container-title:Aerospace Science and Technology

Author:

Ma Chao,Zhang Han,Zhang Jianjian,Wang Xiaoli

Funder

National Natural Science Foundation of China

Publisher

Elsevier BV

Reference24 articles.

1. Gas turbine endwall film cooling and heat transfer characteristics with a multi-cavity slashface gap design;Zhang;Aerosp. Sci. Technol.,2023

2. Study on film cooling for aero-engine turbine endwalls with various small-scale surface structures;Yang;Aerosp. Sci. Technol.,2022

3. Radial Turbine Cooling;Roelke,1992

4. Meitner P.L., Computer Code for Predicting Coolant Flow and Heat Transfer in Turbomachinery, 1990, NASA-Technical Paper-2985.

5. Computations of the three-dimensional flow and heat transfer within a coolant passage of a radial turbine blade;Shih;AIAA J.,1991

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