Analysis Of Turbine Inter-vane Burner(TIB) With Different Combustion Ring Shapes

In order to improve propulsion efficiency of aero-engines, and reduce the amount of emissions, aTurbine Inter-vane Burner (TIB) based on the new Ultra-Compact Combustor (UCC) technology isbeing studied to reach all these goals. It is a new concept consisted of three cavity structures:Circumferential Ring, Axial Cavities for steady flame, and Radial Vane Cavity. The idea of radialflame stabilization, circumferential combustion, axial air flow can achieve pre-combustion in AxialCavities, primary combustion in Circumferential Ring, secondary combustion in Radial Vane Cavity,which can improve the mixing effects and increase the combustion residence time.In this study, the numerical simulation method for analysis and calculation was performed.Firstly, a base model was created to analyze its flow field, temperature field, the distribution of massfraction of the components, emissions, pressure loss, combustion efficiency. Secondly, analysis of thecombustion performance of the base model on different five loading conditions was made. Thirdly,analysis of the effects of different geometry structures on the combustion performance was done,mainly by changing the cavity structure, the secondary air injection angle and setting air injections inthe Axial Cavities. Find a geometry that has the best combustion performance by analyzing thecombustion chamber flow field, temperature field, the distribution of mass fraction of the components,emissions, pressure loss, combustion efficiency, The results show that high-mass high-pressure(HMHP)loading conditions, the Axial Cavity width of16mm, the secondary air injection angle of45°and55°is better suited to obtain enhanced combustion. But setting air injections in the cavity haslittle effect on improving the combustion performance. The numerical results are useable in the futuredesign of the experiment.