Volume 39 Issue 6
Jun.  2024
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QING Liming, ZHU Jianqin, CHENG Zeyuan. Investigation on turbine inter-vane combustion performance based on fuel cooled vane[J]. Journal of Aerospace Power, 2024, 39(6):20220388 doi: 10.13224/j.cnki.jasp.20220388
Citation: QING Liming, ZHU Jianqin, CHENG Zeyuan. Investigation on turbine inter-vane combustion performance based on fuel cooled vane[J]. Journal of Aerospace Power, 2024, 39(6):20220388 doi: 10.13224/j.cnki.jasp.20220388

Investigation on turbine inter-vane combustion performance based on fuel cooled vane

doi: 10.13224/j.cnki.jasp.20220388
  • Received Date: 2022-05-31
    Available Online: 2023-11-20
  • To expand the performance of aero-gas turbine engine, a structure of high-pressure turbine inter-vane combustion was proposed. The high-temperature fuel was injected into the inter-vane channel after cooling the vane. And the flame was stabilized by radial vane cavity (RVC). The C3X turbine guide vane was used as the inter-vane combustion model and the effects of radial vane cavity (depth length ratio 0.4−0.6), fuel-air ratio (0.007−0.0105) and fuel temperature (300−500 K) on inter-vane combustion performance were numerically studied. It was observed that the optimization combustion effect was obtained with depth length ratio 0.5. The thermal resistance loss caused by combustion was about 7%, which can realize the approximately isothermal combustion between the vanes. The inter-vane combustion performance decreased with the increase of fuel-air ratio, and the combustion efficiency reached 98.86% at 20 mm away from the blade outlet when the fuel-air ratio was 0.007. The combustion performance of high-temperature fuel in the inter-vane channel was better than that of low-temperature fuel, and the combustion efficiency at the outlet of the blade increased about 13%. The conclusions can provide a reference for the development of inter-vane burner technology.

     

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