高速火箭增强冲压发动机内转进气道气动设计与风洞试验

杨一言; 傅岸祥; 王昱辉; 田照阳; 石磊

doi:10.7527/S1000-6893.2025.32202

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DOI: https://doi.org/10.7527/S1000-6893.2025.32202

高速火箭增强冲压发动机内转进气道气动设计与风洞试验

杨一言 ,
傅岸祥 ,
王昱辉 ,
田照阳 ,
石磊

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西北工业大学

收稿日期: 2025-05-07

修回日期: 2025-07-02

网络出版日期: 2025-07-03

基金资助

国家自然科学基金;陕西省重点研发计划项目资助

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Aerodynamic design and wind tunnel test on the inward-turning inlet of high-speed rocket-augmented ramjet engine

YANG Yi-Yan ,
FU An-Xiang ,
WANG Yu-Hui ,
TIAN Zhao-Yang ,
SHI Lei

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Received date: 2025-05-07

Revised date: 2025-07-02

Online published: 2025-07-03

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摘要

将压缩效率高、内流品质好、流量系数高、溢流阻力小的内转进气道应用于火箭增强冲压发动机，实现内转进气道与内置火箭中心支板的一体化融合，将有效提高组合发动机进气道在典型飞行区间内的工作性能，大幅强化火箭增强型冲压动力的应用潜力。基于典型的中心支板式火箭增强冲压发动机构型，如果只采用简单的结构集成方式，一方面中心支板的物理介入会严重破坏内转进气道的压缩性能；另一方面，其楔形前缘会分割进气道隔离段下游的高速气流并引发斜激波和膨胀波干扰，导致额外压缩作用及内收缩比增加，引起总压恢复系数显著下降。为解决这些问题，本文提出了一种基于流线追踪技术的内转进气道与中心支板结构的一体化设计方法，通过融合中心支板与进气道压缩曲面，不仅可消除附加压缩效应，还可以充分发挥其特型前体的来流压缩能力。数值仿真与风洞试验结果表明，该设计方法可使一体化内转进气道在引入中心支板结构的同时充分发挥出内转基准流场的压缩性能。在与传统的楔形中心支板方案的对比中，其长度最大可缩短60%，内收缩比可降低25%，从而保证良好的起动能力；在来流速度马赫6、喉部压升比34.8的高收缩比、大压缩量条件下，总压恢复系数可提升17%。

关键词： 火箭增强冲压发动机; 内转进气道; 流线追踪技术; 中心支板; 风洞试验

本文引用格式

杨一言 , 傅岸祥 , 王昱辉 , 田照阳 , 石磊 . 高速火箭增强冲压发动机内转进气道气动设计与风洞试验[J]. 航空学报, 0 : 1 -0 . DOI: 10.7527/S1000-6893.2025.32202

Abstract

Integrating inward-turning inlet with high compression efficiency, good internal flow quality, high flow coefficient, and low overflow resistance with a rocket-augmented ramjet engine can effectively improve the performance of rocket-combined ramjet inlet within the typical flight range and greatly enhance the application potential of rocket-augmented ramjet engine. Based on the typical central strut configuration of a rocket-augmented ramjet engine, if only a simple structural integration method is adopted, the physical intervention of the central strut would seriously damage the compression performance of the inward-turning inlet while its wedge-shaped leading edge would divide the high-speed airflow downstream of the inlet isolator and cause oblique shock and expansion wave interference, resulting in additional compression and an increase in internal contraction ratio, causing a significant decrease in the total pressure recovery coefficient. To address these issues, this paper proposes a structural integration design method between an inward-turning inlet and central strut based on streamline tracing technique. By integrating the central strut with the inlet compression surfaces, not only can additional compression effects be eliminated, but the inflow compression capability of its special precursor can also be fully utilized. The numerical simulation and wind tunnel test verification results indicate that this design method can enable the integrated inward-turning inlet to fully exert the compres-sion performance of the basic flow field while introducing the central strut. Compared with the traditional wedge-shaped central strut, its length can be reduced by 60% at most, and the internal contraction ratio can be reduced by 25%, thus ensuring better start capability. Under the conditions of high contraction ratio and strong compression with the incoming flow of Mach 6 and the throat pressure rise ratio of 34.8, the total pressure recovery coefficient is improved by 17%.

Key words： rocket-augmented ramjet; inward-turning inlet; streamline tracing technique; central strut; wind tunnel test

参考文献

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