Volume 35 Issue 5
May  2020
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Article Navigation >  Journal of Aerospace Power  > 2020  >  35(5): 1042-1050
ZHANG Cheng, WANG Yun, WANG Ke. Compression performance of double-sided composite impeller with micro gas turbine[J]. Journal of Aerospace Power, 2020, 35(5): 1042-1050. doi: 10.13224/j.cnki.jasp.2020.05.016
Citation: ZHANG Cheng, WANG Yun, WANG Ke. Compression performance of double-sided composite impeller with micro gas turbine[J]. Journal of Aerospace Power, 2020, 35(5): 1042-1050. doi: 10.13224/j.cnki.jasp.2020.05.016
shu

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

doi: 10.13224/j.cnki.jasp.2020.05.016
  • 1.

    School of Aircraft Engineering,Nanchang Hangkong University,Nanchang 330063,China

  • 2.

    Key Laboratory of Jiangxi Micro Aeroengine,Nanchang 330063,China

  • Received Date: 2019-11-05
  • Publish Date: 2020-05-28
    Abstract
  • 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 4.4 K 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.

     

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