### 塞锥后体气膜冷却对轴对称塞式喷管红外辐射和气动性能的影响

1. 1. 南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;
2. 先进航空发动机协同创新中心, 北京 100191
• 收稿日期:2015-03-31 修回日期:2015-05-04 出版日期:2015-08-15 发布日期:2015-05-14
• 通讯作者: 张靖周 男, 博士, 教授。《航空学报》第七、八届编委。主要研究方向: 强化传热、强化冷却和红外辐射特征控制。Tel: 025-84895909 E-mail: zhangjz@nuaa.edu.cn E-mail:zhangjz@nuaa.edu.cn
• 作者简介:王旭 男, 硕士研究生。主要研究方向: 红外辐射特征控制。Tel: 025-84895909 E-mail: 736913151@qq.com;单勇 男, 博士, 副教授。主要研究方向: 强化冷却和红外辐射特征控制。Tel: 025-84895909 E-mail: nuaasy@nuaa.edu.cn

### Effects of plug rear-body film cooling on infrared radiation and aerodynamic performance of axisymmetric plug nozzle

ZHANG Jingzhou1,2, WANG Xu1, SHAN Yong1

1. 1. Jiangsu Province Key Laboratory of Aerospace Power System, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;
2. Collaborative Innovation Center of Advanced Aero-Engine, Beijing 100191, China
• Received:2015-03-31 Revised:2015-05-04 Online:2015-08-15 Published:2015-05-14
• Contact: 10.7527/S1000-6893.2015.0119 E-mail:zhangjz@nuaa.edu.cn

Abstract:

A series of computations is conducted to investigate the effects of plug rear-body film cooling on the infrared radiation and aerodynamic performance of axisymmetric plug nozzle under the primary flow conditions (primary mass flow rate of 130 kg/s and total temperature of 920 K) as well as the cooling flow temperature of 480 K. The film-hole arrangement, film-holes inclination angle (ranging from 15° to 30°) and cooling air usage (limited in 3% of primary mass flow rate) are chosen as the influencing factors for comparison. The results show that the film cooling on plug rear-body has a very weak influence on the nozzle thrust coefficient. The cooling action on plug rear-body with cooling air usage of one percent of the primary mass flow rate is capable of having approximately 50% infrared radiation intensity reduction relative to the un-cooled nozzle. As the cooling air usage is increased to 3% of the primary mass flow rate, 60% infrared radiation intensity reduction is achieved; however, the total pressure recovery coefficient is decreased more significantly. Given the same cooling air usage, the multi-holes arrangement with small row-pitch seems to be more reasonable because it results in the nearly same infrared radiation suppression but low total pressure recovery coefficient reduction in comparison with the multi-hole arrangement with large row-pitch. The decrease of film-hole inclination angle from 30° to 15° has little influence on reducing surface temperature of the plug rear-body as well as improving total pressure recovery coefficient of the nozzle.