航空学报 > 2015, Vol. 36 Issue (8): 2601-2608   doi: 10.7527/S1000-6893.2015.0119

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

张靖周1,2, 王旭1, 单勇1   

  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

摘要:

运用数值模拟方法,在主流质量流量为130 kg/s、总温为920 K和冷却空气总温为480 K的参数条件下,对比分析了塞锥后体气膜孔排布方式、气膜孔倾角(15°~30°)和气膜冷却空气用量(3%主流质量流量以内)对轴对称塞式喷管红外辐射和气动性能的影响。研究结果表明:塞锥后体的气膜冷却对喷管推力系数的影响十分微弱;对塞锥后体提供1%主流质量流量的冷却空气,喷管红外辐射强度相对无冷却喷管降低50%左右;当冷却空气用量增大至3%时,喷管红外辐射强度下降约60%,总压恢复系数降低较为显著;在相同的冷却空气用量下,小孔排间距的多孔排布方式与大孔排间距相比,具有近乎相同的红外辐射抑制效果和低的总压恢复系数下降幅度;气膜孔倾角从30°减小至15°,对塞锥后体表面温度的降低以及喷管总压恢复系数的改善效果微弱。

关键词: 排气喷管, 轴对称塞式喷管, 塞锥气膜冷却, 红外辐射, 气动性能

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.

Key words: exhaust nozzle, axisymmetric plug nozzle, plug film cooling, infrared radiation, aerodynamic performance

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