基于新型涡轮冷却算法的航空发动机性能计算模型

推进技术 ›› 2011, Vol. 32 ›› Issue (1): 17-20.

基于新型涡轮冷却算法的航空发动机性能计算模型

黄莺,王占学,刘增文,张建东

西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072;西北工业大学动力与能源学院,陕西西安 710072

发布日期:2021-08-15
作者简介:黄莺(1986—),女,研究生,研究领域为发动机总体。E-mail:september_913@sina.com

Aero-engine performance calculation model based on a new algorithm of turbine cooling

School of Power and Energy,Northwestern Polytechnical Univ., Xian 710072, China;School of Power and Energy,Northwestern Polytechnical Univ., Xian 710072, China;School of Power and Energy,Northwestern Polytechnical Univ., Xian 710072, China;School of Power and Energy,Northwestern Polytechnical Univ., Xian 710072, China

Published:2021-08-15

摘要/Abstract

摘要： 针对气膜冷却和对流冷却两种常用的冷却方式,建立了新的涡轮冷却计算模型,并实现了与燃气涡轮发动机总体性能计算模型的耦合,得到了可考虑的不同冷却方式、适用于高涡轮前温度、大冷气量的燃气涡轮发动机总体性能计算模型,并与简化涡轮冷却模型的计算数据及试验数据作比较分析,表明新型涡轮冷却算法的可行性和能够提供更详细的涡轮部件气流参数。

关键词: 航空发动机;燃气涡轮发动机;涡轮冷却模型

Abstract: For the two commonly used cooling methods, namely film cooling and convective cooling,developed a new calculation model of turbine cooling and realized the new coupling calculation model with the overall performance calculation model of gas turbine engine. Obtained the overall performance calculation model of gas turbine engine, which takes different cooling methods into consideration and is suitable for gas turbine engine with high turbine inlet temperature and a large amount of air cooling flow. The calculation results obtained by the new turbine cooling algorithm were analyzed and compared with that of simple turbine cooling model and test data, which proved the new algorithm feasible for calculation and provided more detailed airflow parameters in turbine components.

Key words: Aircraft engine; Gas turbine engine; Turbine cooling model

黄莺,王占学,刘增文,张建东. 基于新型涡轮冷却算法的航空发动机性能计算模型[J]. 推进技术, 2011, 32(1): 17-20.