跨音压气机边界层抽吸控制方法研究
发布时间：2019-01-04 20:38
【摘要】：提高航空发动机高推重比的重要途径是提高压气机的级载荷。然而压气机在强逆压梯度和复杂的内部流动条件下极易诱发流动分离,尤其是在轮毂端壁的角区和叶片吸力面,即使在设计工况下也常常伴随着复杂的局部分离结构和明显的尾迹现象。这将限制跨音压气机性能的提高,而边界层抽吸可以有效的控制边界层发展,减小分离区,扩展压气机的工作范围,稳定转子通道内的激波系。本文针对Rotor 67跨音转子,采用数值方法详细分析了角区和叶表的流动分离机理以及不同边界层抽吸方案对流动结构、叶片载荷分布、尾缘脱落涡以及通道激波特性的影响机制,以探究控制跨音转子边界层分离的有效途径,主要内容包括：1.深入分析了跨音转子Rotor 67在设计和非工况下的流场特性、内部流动分离机理和通道内激波系结构的发展变化规律。详细研究了跨音转子通道中两个分离区：角区和叶表吸力面分离的诱发机制。2.针对角区的典型流动特点,选取影响角区分离结构的关键位置,设计了多个轮毂端壁边界层抽吸方案,以优化转子角区的流动特性,改善跨音转子叶根的效率和做功能力。通过研究抽吸流量和抽吸缝布置方式的选择原则,以实现边界层抽吸高效控制跨音转子内流动结构的目的。3.对叶表吸力面边界层分离机理进行了研究,并针对激波导致的吸力面边界层分离进行了叶表抽吸方案的研究,以消除吸力面分离的发生,提高叶尖效率,增强做功能力。
[Abstract]:The important way to improve the high thrust-weight ratio of aeroengine is to increase the stage load of compressor. However, the compressor is easy to induce flow separation under the strong inverse pressure gradient and complex internal flow conditions, especially in the angle area of the hub end wall and the suction surface of the blade. Even under design conditions, complex local separation structures and obvious wake phenomena are often accompanied. This will limit the performance of the transonic compressor, and the boundary layer suction can effectively control the development of the boundary layer, reduce the separation area, expand the compressor's working range, and stabilize the shock wave system in the rotor channel. In this paper, the flow separation mechanism of angle region and blade surface and the influence of different boundary layer suction schemes on flow structure, blade load distribution, tail edge shedding vortex and channel shock characteristics are analyzed numerically for Rotor 67 transonic rotor. In order to explore the effective way to control the separation of boundary layer of transonic rotor, the main contents are as follows: 1. The characteristics of flow field, the mechanism of internal flow separation and the development and variation of shock system structure of transonic rotor Rotor 67 under design and off-condition conditions are analyzed in depth. In this paper, the inductive mechanism of two separation regions in transonic rotor channel, angular region and suction surface of blade surface, is studied in detail. 2. In view of the typical flow characteristics of the angular region, the key position affecting the separation structure of the angular region is selected, and the suction scheme of several hub endwall boundary layer is designed in order to optimize the flow characteristics of the rotor corner region and improve the efficiency and work ability of the transonic rotor blade root. By studying the selection principle of suction flow rate and suction joint arrangement, the purpose of efficiently controlling the flow structure of transonic rotor by boundary layer suction is achieved. In this paper, the separation mechanism of the suction boundary layer on the blade surface is studied, and the suction scheme for the suction surface boundary layer separation caused by shock wave is studied in order to eliminate the suction surface separation, improve the blade tip efficiency and enhance the work ability.
【学位授予单位】：中国科学院研究生院(工程热物理研究所)
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V232
本文编号：2400767
[Abstract]:The important way to improve the high thrust-weight ratio of aeroengine is to increase the stage load of compressor. However, the compressor is easy to induce flow separation under the strong inverse pressure gradient and complex internal flow conditions, especially in the angle area of the hub end wall and the suction surface of the blade. Even under design conditions, complex local separation structures and obvious wake phenomena are often accompanied. This will limit the performance of the transonic compressor, and the boundary layer suction can effectively control the development of the boundary layer, reduce the separation area, expand the compressor's working range, and stabilize the shock wave system in the rotor channel. In this paper, the flow separation mechanism of angle region and blade surface and the influence of different boundary layer suction schemes on flow structure, blade load distribution, tail edge shedding vortex and channel shock characteristics are analyzed numerically for Rotor 67 transonic rotor. In order to explore the effective way to control the separation of boundary layer of transonic rotor, the main contents are as follows: 1. The characteristics of flow field, the mechanism of internal flow separation and the development and variation of shock system structure of transonic rotor Rotor 67 under design and off-condition conditions are analyzed in depth. In this paper, the inductive mechanism of two separation regions in transonic rotor channel, angular region and suction surface of blade surface, is studied in detail. 2. In view of the typical flow characteristics of the angular region, the key position affecting the separation structure of the angular region is selected, and the suction scheme of several hub endwall boundary layer is designed in order to optimize the flow characteristics of the rotor corner region and improve the efficiency and work ability of the transonic rotor blade root. By studying the selection principle of suction flow rate and suction joint arrangement, the purpose of efficiently controlling the flow structure of transonic rotor by boundary layer suction is achieved. In this paper, the separation mechanism of the suction boundary layer on the blade surface is studied, and the suction scheme for the suction surface boundary layer separation caused by shock wave is studied in order to eliminate the suction surface separation, improve the blade tip efficiency and enhance the work ability.
【学位授予单位】：中国科学院研究生院(工程热物理研究所)
【学位级别】：硕士
【学位授予年份】：2015
【分类号】：V232
【参考文献】
相关期刊论文 前1条
1 于贤君;刘宝杰;张志博;赵斌;;近失速状态下压气机静子通道内的三维流动[J];工程热物理学报;2009年01期
相关博士学位论文 前1条
1 兰发祥;吸附式压气机设计技术研究[D];南京航空航天大学;2009年
，本文编号：2400767
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