Compression performance of double-sided composite impeller with micro gas turbine

被引：0
|
作者：
Zhang C. [1 ,2 ]
Wang Y. [1 ,2 ]
Wang K. [1 ,2 ]
Wang J. [1 ,2 ]
He S. [1 ,2 ]
机构：
[1] School of Aircraft Engineering, Nanchang Hangkong University, Nanchang
[2] Key Laboratory of Jiangxi Micro Aeroengine, Nanchang
来源：
Hangkong Dongli Xuebao/Journal of Aerospace Power | 2020年 / 35卷 / 05期
关键词：
Aerodynamic performance; Conventional impeller; Double-sided composite impeller; Micro gas turbine; Rear intake pipe;
D O I：
10.13224/j.cnki.jasp.2020.05.016
中图分类号：
学科分类号：
摘要：
In order to achieve the core engine with high performance parameters and high-tech equipment, based on the ideas of structural fusion and thermal process fusion, the core engine of traditional micro-turbine was integrated through innovation. Based on the 3D printing design and manufacturing technology foundation, a double-sided composite impeller structure was designed, with a radial connection of a double-sided conventional impeller and an axial-flow turbine, making it possible to become a type of high-efficiency impeller with great potential in the future. Specifically, the principle, structural scheme and expected performance of the micro gas turbine were analyzed. Numerical investigation of aerodynamic compression performance of a double-sided composite impeller and backward pipe heat transfer characteristics was primarily studied. Results show that compared with the conventional impeller, the aerodynamic compression performance of the double-sided composite impeller can meet the expectation perfectly. The total pressure ratio, flow rate and isentropic efficiency have been greatly improved; the recovery of 4.4K exhaust gas temperature in the rear intake pipe can improve the thermal efficiency. It has laid the foundation for the development of gas turbines with high aerodynamic performance and high cycle parameters. © 2020, Editorial Department of Journal of Aerospace Power. All right reserved.
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页码：1042 / 1050
页数：8
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