基于油冷叶片的涡轮叶间燃烧性能研究

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− 0.010 5) 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.