向心涡轮内部流动数值模拟分析

基金项目: 国防基础科研基金资助(K1204060722);国防科技重点实验室基金资助(51459060104HK3802)

Numerical Simulation of the Flow Inside Radial Inflow Turbine

1.
National Key Laboratory on Aero-Engines, School of Jet Propulsion, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
2.
Aeroengine Numerical Simulation Research Center, Beijing University of Aeronautics and Astronautics, Beijing 100083, China
3.
Chinese Aviation Powerplant Research Institute, Zhuzhou 412002, China

摘要: 利用三维数值模拟方法对向心涡轮内部流动进行数值模拟,分析了岛型导叶的气动特点、通道中的二次流动和各个涡系的发展以及不同叶尖间隙对流动的影响。结果表明:在一定范围内岛型导叶对气流角变化不敏感;在靠近动叶进口处二次流动比较明显,流动比较复杂,而通道中各个涡系的演化发展都集中在靠近动叶吸力面一侧;随着的罩壳半径的减小,动叶叶尖处间隙流动逐渐增强;适量的间隙流动有利于改善通道顶部区域流动。
- 航空、航天推进系统 /
- 向心涡轮 /
- 数值模拟 /
- 二次流动 /
- 间隙流动
Abstract: Three-dimensional numerical simulation of the flow inside a radial inflow turbine was presented.Preliminary analysis of the aerodynamic characteristics of the island shaped blade,secondary flow and development of vortex and impact of tip clearance were conducted.Results show that island shaped blade has little sensitivity to flow direction in certain range;secondary flow is evident near the inlet of the impeller and close to the suction surface of the passage;along with the reduction of shroud radius,tip clearance flow of the rotor becomes strong.Appropriate tip clearance flow can improve the flow in the tip region.
- aerospace propulsion system /
- radial inflow turbine /
- numerical simulation /
- secondary flow /
- tip clearance flow

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