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