| 摘要: |
| 为了探究双气路内并联进气系统固定马赫数下模态转换过程中的分流板调节策略，利用数值计算与地面试验验证相结合的方法，研究了Ma3.5条件下双气路进气系统在典型分流板位置的流场干涉机制，获得了不同出口反压条件下双气路进气系统的总体性能和流场变化规律。研究结果表明：分流板高度调节影响高低速气路的总体性能，为避免高低速气路之间的流动干扰，引起流量剧烈变化，模态转换过程中提供推力气路的正激波应不被推出分流板前缘；数值预测的密度梯度与试验纹影预测的波系结构高度吻合，数值计算结果表明高低速气路出口反压比变化直接影响分流板附近高低速气路的波系结构，二元喉道段的流场具有明显的三维分布特征；采用抽吸孔和泄流缝的流场控制措施有效提高进气系统的起动性能，分流板相对高度0.702条件下进气系统抗出口反压比能力从28提升到32；采用双S弯扩压器设计，低速气路临界反压比条件下的出口平均马赫数和总压畸变度控制在0.3和0.09以下。 |
| 关键词: 组合发动机 双气路进气系统 模态转换 分流板 地面试验系统 |
| DOI：10.13675/j.cnki.tjjs.210115 |
| 分类号:V231.1 |
| 基金项目:高超声速冲压发动机技术重点实验室基金（STS/MY-ZY-2017-003）。 |
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| Numerical Study and Experimental Verification on Mode Transition Course of Inner over/under Inlet System with Double Flow Path |
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MU Zhong-qiang1, YANG Shun-hua2, WANG Tie-jun2, YOU Jin1, YUAN Hua-cheng3, REN Hu2, XIE Song-bai1, ZHANG Wan-zhou1
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1.Beijing Aerohydrodynamic Frontier Research Center，Beijing 100029，China;2.Science and Technology on Scramjet Laboratory，China Aerodynamics Research and Development Center， Mianyang 621000，China;3.College of Energy and Power，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China
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| Abstract: |
| To explore splitter adjustment tactic of double flow path inlet system during the mode transition course with fixed free stream Mach number， the method combined numerical simulation prediction with ground test verification has been used. The variation rules of total performance and flow field with different outlet back pressure and splitter height have been obtained， which is used to investigate flow field interference mechanism of double flow path when the free stream Mach number is 3.5. The results show that because the change of splitter height affects the total performance， to avoid flow field intervene between high and low speed flow path that results in mass flow rate changing drastically， the shock wave of flow path which is on working state should not be pushed out of the leading edge of splitter. The wave structure between density gradient magnitude from numerical prediction and schlieren photos from ground test is highly satisfied， which shows that the back pressure variation of double flow path affects the wave structure nearby splitter leading edge， and the flow field in the two-dimensional throat section has three dimensional distribution features significantly. The flow control method of bleed hole and leakage channel is effective to improve the inlet starting performance， which make the capacity of resistance to outlet back pressure ratio increased from 28 to 32 with the splitter relative height being 0.702. Through using the double S diffuser， outlet average Mach number and total pressure distortion coefficient of low speed flow path is less than 0.3 and 0.09， respectively， which is satisfied the inflow demand of combustor stable working. |
| Key words: Combined cycle engine Double flow path inlet system Mode transition Splitter Ground test system |
