Research On Ultra-Compact Combustor For Turbine Inter-Blade Burner

As a novel concept on Aero-engine combustor, Ultra-Compact Combustor for Turbine inter-Blade Burner has been applied to turbine engine with the feature of compact structure, high efficiency and low losses. Based on the relevant achievement, this thesis designed an experimental model(Turbine inter-Blade Burner with 3 Cavities, for short TIB-3C) and experimental system with it. The purpose of the experiment was to verify the results of numerical simulation. The numerical simulation of experimental model was to study the influence of flow rate and operating pressure with the CFD software FLUENT. Besides, this thesis simulated Main Combustor(MC for short)—Turbine inter-Blade Burner(TIB for short) intergration Combustor(MC-TIB for short) with different constructions to study the influence of combustion characteristic in MC-TIB with different length-width ratios and air injection angles.Firstly, the thesis researched the effect of Turbine Ultra-Compact Combustor for Turbine inter-Blade Burner(TIB-3C) on different working conditions. It showed:(1) on the condition of constant total flow, through the methods of appropriately increasing the flow rate of air injection, it could increase the velocity, improve the distribution of temperature,increase the efficiency and decrease the emission of pollutants like NOx,CO and UHC at outlet. Besides, on the condition of high air injection flow rate, the outlet of the combustor got fairly ideal distribution of temperature;(2) the way of properly increasing the operating pressure was beneficial to reduce the pressure losses, improve the efficiency, increase the temperature outlet and decrease the emission of pollutants.Secondly, the thesis designed an experiment on Ultra-Compact Combustor for Turbine inter-Blade Burner(TIB-3C) and experimented with the goal of verifiability. It achieved :(1) the structure of experimental sample was consisting of 45 ° &55 ° of air injection angle,0.6 of length-width ratios, crooked with groove on the back of Turbine inter-blade and prewhirl vane;(2) the experimental working system of air and fuel;(3) keeping the total flow constant, increasing the flow rate of air injection led to more total pressure losses and the relative error was approximately 10% comparing with the same condition on numerical simulation;(4) compared with simulation, the temperature relative error was about 18% on the surface of the vane.Finally, the thesis studied the influence of combustion characteristic with different structures of Main Combustor — Turbine inter-Blade Burner intergration Combuster. It resulted:(1) the length-width ratios of combustion ring restricted the size of the space for reaction in Turbine inter-Blade Burner(TIB for shot), resulting in the effect of combustion performance; by the way of increasing the ratio, it would increase the outlet velocity and temperature, improve distribution of velocity and reduce the pressure losses at outlet; through the method of decrease the ratio, it would strengthen the mixing of main flow and air injections, improve the distribution of temperature and reduce emission of pollutants;(2) the air injection angles of combustion ring had influence on the flow field in combustion ring; appropriately increasing the air injection angles was benefit to increase the velocity outlet, improve its distribution and reduce the pollutants of UHC; decreasing the angles could increase the temperature outlet, improve its distribution and reduce the pollutants of NOx; the change of angles had less influence on pressure losses outlet.