The turbine inter-vane burning technology was applied to achieve the purpose of high thrust-weight ratio

low specific fuel consumption

low pollution and expanded stable working range of aero-engine. For this purpose

the burner placed between the turbine vanes was reheated to increase the gas temperature in the turbine

and then improve the overall performance of aero-engine. This works elaborated the potential advantage of the turbine inter-vane burning technology of enhancing the aero-engine overall performance based on overall thermodynamic cycle performance analysis

helping to research key technology

parameters and mechanism problem about combustion in this technology. And it is observed that: (1) for the jet-swirl scheme

radial vane cavity plays a decisive role in temperature distribution at the exit of combustor

and combustion efficiency can be improved by reducing the equivalence ratio in combustion ring cavity while leading to lower pollutant emissions quantity of CO

UHC (unburned hydrocarbon)

NOx; (2) the jet-vortex scheme has better combustion performance when the secondary jet-flow angle is 60 degrees.