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带有中心钝体的固体燃料冲压发动机工作性能分析
引用本文:张宁,史金光,王中原,马晔璇.带有中心钝体的固体燃料冲压发动机工作性能分析[J].推进技术,2022,43(8):40-47.
作者姓名:张宁  史金光  王中原  马晔璇
作者单位:南京理工大学,南京理工大学,南京理工大学,北京动力机械研究所
摘    要:为提高固体燃料冲压发动机的燃烧特性和工作性能,提出了带有中心钝体的固体燃料冲压发动机方案,基于雷诺转捩和涡概念耗散方程建立了其湍流燃烧模型,并数值计算分析了其内流场、燃面退移速率、推力与总压损失。结果表明:带有中心钝体的冲压发动机内部流动过程较为复杂,钝体后部有四个漩涡,增强了发动机内来流空气与燃气的掺混;钝体孔隙中的高速气流与两侧的小尺度漩涡保证了钝体尾涡的稳定性;与普通固体燃料冲压发动机相比,在燃烧室中增加中心钝体能增大燃烧室内高温区面积,提高补燃室内温度,可使推进剂平均燃面退移速率提高26.11%,发动机推力提高22.12%,燃烧效率提高8.9%。

关 键 词:固体燃料冲压发动机  涡旋燃烧  燃面退移速率  推力  燃烧效率
收稿时间:2021/3/16 0:00:00
修稿时间:2022/6/7 0:00:00

Performance Analysis of Solid Fuel Ramjet with Central Bluff Body
ZHANG Ning,SHI Jin-guang,WANG Zhong-yuan,MA Ye-xuan.Performance Analysis of Solid Fuel Ramjet with Central Bluff Body[J].Journal of Propulsion Technology,2022,43(8):40-47.
Authors:ZHANG Ning  SHI Jin-guang  WANG Zhong-yuan  MA Ye-xuan
Institution:Nanjing University of Science and Technology,Nanjing University of Science and Technology,,
Abstract:In order to improve the combustion characteristics and working performance of the solid fuel ramjet, a solid fuel ramjet with a central bluff body is proposed. Based on the Renault transition and Eddy-Dissipation equations, the turbulent combustion model is established, and the internal flow field of the ramjet, as well as the regression rate, thrust and total pressure loss, were numerically analyzed. The results show that: the internal flow process of the ramjet with a central bluff body is more complex. There are four vortices at the rear of the bluff body, which enhances the mixing of air and gas in the engine. The small-scale vortices on both sides of the holes maintain the stability of the vortices behind the bluff body. Compared with the ordinary ramjet, adding a central bluff body in the combustion chamber can increase the combustion chamber and the inner high temperature zone. The results show that the average burning surface regression rate of propellant increases by 26.11%, the engine thrust increases by 22.12%, and the combustion efficiency increases by8.9%.
Keywords:Solid fuel ramjet  Vortex combustion  Regression rate  Thrust  Combustion efficiency
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