涡扇发动机二元喷管模型吹风对比试验

推进技术 ›› 2007, Vol. 28 ›› Issue (3): 261-263.

涡扇发动机二元喷管模型吹风对比试验

李小彪,徐凌志,李俊萍,李锋

南京航空航天大学能源与动力学院;航天科工集团31所;航天科工集团31所;航天科工集团31所;北京航空航天大学能源与动力学院

发布日期:2021-08-15

Model comparative test for infra-red stealth nozzle of gas turbine engine

Coll.of Energy and Power,Nanjing Univ.of Aeronautics and Astronautics,Nanjing 210016,China;The 31st Research Inst.of CASIC,Beijing 100074,China;The 31st Research Inst.of CASIC,Beijing 100074,China;The 31st Research Inst.of CASIC,Beijing 100074,China;Coll.of Energy and Power,Beijing Univ.of Aeronautics and Astronautics,Beijing 100083,China

Published:2021-08-15

摘要/Abstract

摘要： 在多功能热喷流实验台,进行了某型涡扇发动机二元喷管模型试验件与常规轴对称喷管模型试验件吹风对比试验。试验结果表明:与常规轴对称喷管相比,采用二元喷管后,其尾喷流的流场速度快速衰减,其温度比常规轴对称喷管衰减得快得多,射流的高温区沿轴向大幅减少(大约为原来的1/5),这对红外辐射的抑制十分有利。

关键词: 涡轮风扇发动机;喷管;试验

Abstract: The comparative test between conventional nozzle and infra-red stealth nozzle was conducted in multi-function heat-cascade test bed.Test results show that for infra-red stealth nozzle both velocity and temperature recede quickly compared with conventional axial symmetry nozzle.High temperature zone becomes smaller in axial direction(approximately 1/5 compared with conventional nozzle).

Key words: Turbofan engine;Nozzle;Test

李小彪,徐凌志,李俊萍,李锋. 涡扇发动机二元喷管模型吹风对比试验[J]. 推进技术, 2007, 28(3): 261-263.