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Affiliation of Author(s):能源与动力学院

Journal:Hangkong Dongli Xuebao

Abstract:Numerical simulation was carried out to study the effusion cooling on a specific transverse corrugated heat-shield used in aero-engine afterburner. Three main geometric parameters, including spanwise-to-streamwise pitch ratio, hole diameter and perforated percentage, were taken into consideration. Result showed that, in the wavy valley of transverse corrugated surface, the coolant jets ejected from adjacent holes were prone to interact each other, thus forming more coolant accumulation. Due to this feature, the adiabatic wall temperature on the wavy valley of transverse corrugated surface was relatively lower than that on the wavy peak. In general, reducing the hole diameter and enlarging the perforated percentage were illustrated to be significantly helpful to enhance the film cooling effectiveness under the same coolant usage for a given protected area, especially in the front developing zone of an effusion cooling scheme. Besides, the effusion holes arranged in a super-long-diamond mode where the streamwise hole-to-hole pitch was bigger than spanwise hole-to-hole pitch showed more favorable. However, the effect of spanwise-to-streamwise pitch ratio on the laterally-averaged adiabatic film cooling effectiveness was very weak at low blowing ratio. © 2018, Editorial Department of Journal of Aerospace Power. All right reserved.

ISSN No.:1000-8055

Translation or Not:no

Date of Publication:2018-03-01

Co-author:Qu, Lihong,TAN Xiaoming

Correspondence Author:zjz