面向飞/发一体化设计的高温尾喷口流场分析

doi:10.7527/S1000-6893.2015.0333

Abstract

Abstract:

Combined with the aircraft-engine integration concept,transverse jet mixing technology is introduced to conduct the nozzle design in order to improve infrared stealth performance.The temperature field of circular and rectangular nozzle exhaust flow is analyzed by computational fluid dynamics(CFD) numerical simulation method,and we extract the central face of the rectangular nozzle to observe the cooling effect of transverse jet walls along with different angles.The results show that compared with the inlet temperature,the cooling ratio of rectangular nozzle reaches 30%approximately,the exhaust plume flows to both sides,and the volume of the core high temperature flow decreases obviously;circular nozzle cooling rate is about 10%,the exhaust plume keeps cylindrical along the central line,and the core jet volume attenuation is slow.Consequently,the rectangular nozzle cooling efficiency is significantly higher than that of the circular nozzle and is more advantageous to realize aircraft-engine integrated thermal management as well as infrared stealth.Additionally,active cooling effect also has close relationship with the deflection angle magnitude of the mid wall with transverse jet.

Key words: aircraft-engine integrated design, infrared stealth, transverse mixing, active cooling, CFD

CLC Number:

V221

LI Shu, WANG Li, WU Shuo, SHEN Dong, HUANG Rui, WANG Qiang. Analysis of high temperature nozzle exhaust flow towards aircraft-engine integrated design[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(1): 364-370.

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Analysis of high temperature nozzle exhaust flow towards aircraft-engine integrated design

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