C conjugate heat transfer simulation of swirl internal cooling on blade leading edge-Reference-Cited by-同舟云学术

C conjugate heat transfer simulation of swirl internal cooling on blade leading edge

Published:2023-11-29 Issue:0 Volume:0 Page:
ISSN:0334-0082
Container-title:International Journal of Turbo & Jet-Engines
language:en
Short-container-title:

Author:

Jiang Yuting¹,Zhang Haosu¹,Huang Kang²³,Liu Biao¹,Tan Yibin¹,Yu Hai¹

Affiliation:

1. College of Power and Energy Engineering, Harbin Engineering University , Harbin , 150001 , China

2. State Key Laboratory of Aerodynamics, China Aerodynamics Research and Development Center , Mianyang , 621000 , China

3. Aerospace Technology Institute, China Aerodynamics Research and Development Center , Mianyang , 621000 , China

Abstract

Abstract Swirl cooling can not only increase the area of the heat exchange wall covered by the coolant, but also improve the average heat transfer intensity and uniformity of the target surface. SST k-ω turbulence model is utilized in the conjugate heat transfer numerical simulation. Based on C3X blades, leading edge swirl cooling structure of the corresponding areas are modified. The flow and heat transfer characteristics of swirl cooling are analyzed at different cross-sections and positions. It is found that there exists an optimal aspect ratio and hole spacing to minimize the temperature gradient on the swirl cavity wall. The swirling motion in the swirl cavity can significantly increase the heat transfer coefficient of the wall surface.

Funder

State Key Laboratory of Aerodynamics

National Natural Science Foundation of China

Natural Science Foundation of Heilongjiang Province of China-Outstanding Youth Foundation

China Postdoctoral Science Foundation

Publisher

Walter de Gruyter GmbH

Subject

Aerospace Engineering

Link

https://www.degruyter.com/document/doi/10.1515/tjj-2023-0051/pdf

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