变结构RBCC发动机亚燃模态全流道数值模拟研究  

Ramjet Mode of Variable Geometry RBCC via Full Flow Path Numerical Simulations

作　　者：叶进颖 潘宏亮[1] 秦飞[1] 王亚军[1] 朱韶华 YE Jin-ying;PAN Hong-liang;QIN Fei;WANG Ya-jun;ZHU Shao-hua(Science and Technology on Combustion,Internal Flow and Thermo-Structure Laboratory,Northwestern Polytechnical University,Xi’an 710072,China)

机构地区：[1]西北工业大学燃烧、热结构与内流场重点实验室,陕西西安710072

出　　处：《推进技术》2021年第9期1948-1955,共8页Journal of Propulsion Technology

基　　金：陕西省重点研发计划(2019ZDLGY19-09)。

摘　　要：变结构燃烧室是提高宽范围工作火箭基组合循环(Rocket-based combined-cycle,RBCC)发动机性能的有效途径之一。通过全流道三维数值模拟的方法,研究变结构RBCC发动机在低来流马赫数条件下燃烧室与进排气匹配状况,以及采用变结构燃烧室进行亚燃模态可靠燃烧组织的可行性。针对Ma=3来流,研究了火箭冲压和纯冲压燃烧模式下的发动机性能,并实现了燃烧室工作模式的转变。通过研究得到以下结论:(1)在火箭冲压工作模式下,一次火箭小流量工作能够提高二次燃料的燃烧效率,冲压燃烧室比冲性能较优,燃烧室与进排气能够匹配工作。(2)燃烧室工作在火箭冲压模式时,采用燃料支板集中喷注燃料的性能优于隔离段和燃料支板分散喷注时性能;发动机工作在纯冲压模式时,燃烧效率将会下降,并且发动机冲压比冲比火箭冲压工作模式下降10.2%,全流道比冲则上升14.5%。The use of a structurally variable combustor is one of the most effective methods to improve the performance of a rocket-based combined-cycle(RBCC)engine over a wide operating range.Aims to study the matching between the combustor and the inlet/exhaust of a variable geometry RBCC engine at low inflow Mach numbers via full flow path of three-dimensional numerical simulations.Furthermore,focus on the feasibility of using a variable geometry combustor to carry out a steady secondary fuel combustion organization in ramjet mode.Under the inflow condition of Ma=3,the engine performances were studied based on the rocket-ramjet and pure ramjet combustion mode,and the transition of the engine from the rocket-ramjet mode to the pure ramjet mode was obtained in the variable geometry ram combustor.Concluding remarks are summarized as:(1)In the rocket ramjet mode,the primary rocket has obvious positive effects on improving the secondary fuel combustion efficiency and results in a higher ramjet specific impulse.Matching of the combustor and inlet/exhaust has been realized under the rocket-ramjet mode.(2)In the rocket ramjet mode,improvement of the engine performances prefers a concentrated fuel injection rather than a dispersed injection through isolator section and pylons.In the pure ramjet mode,the specific impulse of the full flow path increases by 14.5%,compared with in the rocket-ramjet mode,despite the decrease of ram specific impulse by 10.2% due to a worsen combustion efficiency.

关 键 词：火箭基组合循环 变结构 燃烧室 亚燃模态 数值模拟 燃烧性能 

分 类 号：V236[航空宇航科学与技术—航空宇航推进理论与工程]