Influence of temperature ratio on cooling efficiency of 3-in-1 hole injection film
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Influence of temperature ratio on cooling efficiency of 3-in-1 hole injection film
Thermal Power GenerationVol. 44, Issue 4, Pages: 50-55(2015)
作者机构:
1. 沈阳航空航天大学辽宁省航空推进系统先进测试技术重点实验室
2. 中国航空工业集团公司沈阳发动机设计研究所
作者简介:
基金信息:
DOI:
CLC:TK473
Published:2015
稿件说明:
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LI Guangchao, FU Jian, LIU Yongquan, et al. Influence of temperature ratio on cooling efficiency of 3-in-1 hole injection film[J]. Thermal power generation, 2015, 44(4): 50-55.
DOI:
LI Guangchao, FU Jian, LIU Yongquan, et al. Influence of temperature ratio on cooling efficiency of 3-in-1 hole injection film[J]. Thermal power generation, 2015, 44(4): 50-55.DOI:
Influence of temperature ratio on cooling efficiency of 3-in-1 hole injection film
To explore the difference of film cooling characteristics between small temperature ratio and real temperature ratio of the coolant and gas
the flow field
temperature field and film cooling efficiency of3-in-1hole injection film were studied
on the basis of Fluent software
by using the realizable k-ε model with temperature ratio of 1.1and 2.0
the blowing ratio of 0.5and 2.0.The results show that
at blowing ratio of 0.5
the diffusions of coolant with both temperature ratios are identical and the radial average cooling efficiency has little difference.At blowing ratio of 2.0
the coolant radial diffusion with temperature ratio of 2.0is better than that with temperature ratio of 1.1.The radial average cooling efficiency with temperature ratio of 2.0is about 13.4%to 55.5% higher.
Experimental investigation of film cooling efficiency on turbine blade surface with one-inlet and double-outlet hole injection
Investigation on discharge coefficient of jet from bidirectionally expanded holes
Numerical simulation on cooling effectiveness of gas film on tip of blade with groove and fins
Influence of coolant crossflow on film cooling effectiveness of one-inlet and double-outlet injection holes
Related Author
LI Guangchao
PENG Ningjian
ZHANG Wei
KOU Zhihai
MAO Xiaodong
ZHANG Guochen
WU Chaolin
KOU Zhihai
Related Institution
Liaoning Key Lab of Advanced Measurement and Test Technique for Aviation Propulsion System, Faculty of Aerospace Engineering, Shenyang Aerospace University
China Gas Turbine Research Institute of Aviation Industry Corporation of China
Liaoning Key Lab of Advanced Measurement and Test Technology for Aviation Propulsion System,Faculty of Aerospace Engineering,Shenyang Aerospace University Shenyang
Aeroengine and Energy Engineering College,Shenyang Aerospace University
Liaoning Key Lab of Advanced Test and Measurement for Aviation Propulsion System,Shenyang Aerospace University