低反动度高负荷超声速轴流压气机气动设计方法

王松涛; 胡应交; 王仲奇

低反动度高负荷超声速轴流压气机气动设计方法

哈尔滨工业大学能源科学与工程学院发动机气体动力研究中心, 哈尔滨 150001

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出版历程
- 收稿日期: 2012-05-31
- 刊出日期: 2013-06-28

Aerodynamic design method of high loaded supersonic axial-compressor with low reaction

Engine Aerodynamic Research Center, School of Energy Science and Engineering, Harbin Institute of Technology, Harbin 150001, China

摘要

摘要: 对超声速轴流压气机的发展历程进行了总结,分析了两类传统超声速压气机内部流动特点及其所存在的流动问题,并对未来超声速压气机的发展提出了展望.针对超声速压气机内部流动特点,提出了一种新的低反动度高负荷超声速轴流压气机气动设计原理.该原理可有效避免在动叶中进行流动控制,同时降低动叶出口绝对马赫数,并结合附面层抽吸控制静叶栅内部流动,最终实现级的高负荷气动设计.利用该原理进行设计验证,三维黏性数值模拟结果表明:在叶尖切线速度为360m/s的前提下,实现了2.3的级压比,级效率为86.5%.
- 超声速轴流压气机 /
- 低反动度 /
- 附面层抽吸 /
- 气动设计 /
- 数值模拟
Abstract: For supersonic axial flow compressors, a brief summary was given for its historical development. The internal flow characteristics and problems of the two kinds of traditional supersonic compressors were analyzed. Some prospects were proposed for its future technology trends and research orientation. According to the flow characteristics in supersonic compressors, a new aerodynamic design method of high loaded supersonic axial-compressor with low reaction was put forward. Using this method, active flow control means are not necessary in the efficient rotor, and the exit absolute Mach number of the rotor is decreased. For the downstream stator, boundary layer suction is used to solve its internal flow problems to fulfill an efficient and high loaded stage design.A preliminary design verification of the principle has been conducted.The 3-D viscous numerical simulation results show that at the tip tangential speed of 360m/s,the stage pressure ratio of 2.3 and the isentropic efficiency of 86.5% are achieved in the use of this concept.
- supersonic axial-compressor /
- low reaction /
- boundary-layer suction /
- aerodynamic design /
- numerical simulation

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参考文献(20)

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