主燃烧室冲击/发散双层壁冷却方式壁温验证试验研究
Rig Test of Impingement/Effusion Double Wall Cooling Methods for the Main Combustor
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摘要: 为检验冲击/发散双层壁冷却方式在真实工况下的冷却效果,在单头部高温高压燃烧试验台上对3种结构的冲击/发散双层壁实验件进行单头部高温高压综合验证考核试验。实验参数模拟推比10一级发动机燃烧室设计点参数进行综合考核验证。实验结果表明冲击/发散双层壁火焰筒冷却气量约为20%,总冷却效率在0.85~0.96之间,壁温低于1150K。Abstract: For the investigation, a combustor sector with one burner head was used.Three different test pieces with impingement/effusion double wall cooling were selected for testing under high-temperature and high-pressure working conditions,which were equivalent to that of engines with a thrust/weight ratio of 10.The liner temperatures were measured using thermocouples.The test result shows that the amount of cooling airflow of double-layer wall combustor is 20% of the overall airflow,and the overall cooling effectiveness is in the range of 0.85 to 0.96.The wall temperatures of all test pieces are lower than 1 150 K.
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Key words:
- aerospace propulsion system /
- aero-engine /
- main combustor /
- impingement cooling /
- effusion cooling /
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