| 一种双流路变几何涡轮基组合循环进气道的设计与仿真 |
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| 引用本文： | 王德鹏,庄逸,谭慧俊,张鸿,杜沫辰,李光胜.一种双流路变几何涡轮基组合循环进气道的设计与仿真[J].航空动力学报,2015,30(11):2695-2704. |
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| 作者姓名： | 王德鹏 庄逸 谭慧俊 张鸿 杜沫辰 李光胜 |
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| 作者单位： | 南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016,南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016,南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016;先进航空发动机协同创新中心, 北京 100191,中国民航大学 中欧航空工程师学院, 天津 300300,南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016,南京航空航天大学 能源与动力学院 江苏省航空动力系统重点实验室, 南京 210016 |
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| 基金项目： | 国防基础科研; 国家自然科学基金(91216112, 11172133,1172136); 教育部新世纪优秀人才支持计划(NCTE-11-0831) |
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| 摘 要： | 针对涡轮基组合循环(TBCC)发动机宽速域的工作需求,提出了一种外并联双流路的变几何进气道方案.通过转动涡轮和亚燃通道的唇罩前缘,可对进气道的捕获高度进行调节,并可实现模态切换;通过亚燃通道下壁面的多连杆机构,可对进气道的内收缩比进行调节,以实现进气道在宽马赫数范围的高效工作.通过对该进气道进行CFD数值模拟,获得了其流动和工作特性,并与定几何进气道方案进行了对比分析.研究结果表明:该变几何进气道具较宽的工作马赫数范围,且具有良好气动性能.与定几何方案相比,该变几何进气道在来流马赫数Ma为2.5,3.0,4.0时的总压恢复系数分别高出了12.5%,30.2%,133.3%.
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| 关 键 词： | 涡轮基组合循环 变几何进气道 外并联 双流路 亚燃通道 |
| 收稿时间： | 2014/4/12 0:00:00 |
Design and simulation of a dual-channel variable geometryturbine based combined cycle inlet |
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| WANG De-peng,ZHUANG Yi,TAN Hui-jun,ZHANG Hong,DU Mo-chen and LI Guang-sheng.Design and simulation of a dual-channel variable geometryturbine based combined cycle inlet[J].Journal of Aerospace Power,2015,30(11):2695-2704. |
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| Authors: | WANG De-peng ZHUANG Yi TAN Hui-jun ZHANG Hong DU Mo-chen and LI Guang-sheng |
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| Institution: | Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China,Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China,Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China;Collaborative Innovation Center for Advanced Aero-Engine, Beijing 100191, China,Sino-European Institute of Aviation Engineering, Civil Aviation University of China, Tianjin 300300, China,Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China and Jiangsu Province Key Laboratory of Aerospace Power Systems, College of Energy and Power Engineering, Nanjing University of Aeronautics and Astronautics, Nanjing 210016, China |
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| Abstract: | To meet the demand of turbine based combined cycle (TBCC) engine, a design concept of external parallel dual-channel variable inlet was proposed. By rotating cowls of turbine channel and ramjet channel, the inlet can regulate mass flow capture height and realize mode transition. Besides, the inlet can obtain good performance in a wide Mach range by adjusting internal contraction ratio with the Multi-linkages mechanism under the lower wall of ramjet channel. Numerical simulation method was applied to investigate the flow characteristics and the performance of the inlet. The results reveal that the variable inlet can work in a wide Mach range with good performance in the work envelope. Compared with fixed geometry inlet, the variable geometry inlet can increase total pressure recovery coefficient up to 12.5%, 30.2% and 133.3% at Mach number is 2.5,3.0 and 4.0, respectively. |
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| Keywords: | turbine based combined cycle(TBCC) variable inlet external parallel dual-channel ramjet channel |
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