摘要
为研究不同冷却方式对航空发动机中心锥冷却效果的影响,建立了发动机低压涡轮后部件的物理模型,采用流固耦合的方法计算得到中心锥表面温度分布,重点研究了在不同冷却方式下冷却流量比、锥面气膜入射角度等参数对冷却效果的影响。研究表明:腔体引气对中心锥前段与末端的冷却效果较好,对中段双排孔之前部分的冷却效果较差,在有限范围内增加冷却空气流量能够提高冷却效果;当流量比不变时,采用腔体引气/锥面气膜结合方式时中段双排孔之前锥面温度比仅采用腔体引气冷却时降低了40%。
In order to investigate the influence of different cooling methods on cooling efficiency of center cone in turbo-fan engine,the physical models of components after low turbine are established in the paper,and distribution of temperature in cone is simulated and calculated by coupling method of fluid and solid,the study focused on the influence of cooling flux ratios and injection angle when different cooling methods are adopted.The results show that importing air to cavity cools cone efficiently except for middle section before double row holes,improving flux ratio in a certain range can improve the cooling effectiveness;compared with cooling by importing air to cavity,method that compound importing air to cavity and full coverage film cooling can reduce the temperature on middle section before double row holes by 40percent while the flow ratio remains constant.
出处
《空军工程大学学报（自然科学版）》
CSCD
北大核心
2013年第5期5-8,共4页
Journal of Air Force Engineering University(Natural Science Edition)
基金
国家自然科学基金资助项目(51105374)
关键词
中心锥冷却
腔体引气
复合冷却
流量比
入射角度
cone cooling
cavity air importing
compound cooling
flux ratio
injection angle
