Central cavity stable fire tangential combustion chamber

Abstract

The invention discloses a central cavity stable fire tangential combustion chamber, which consists of a shunting type diffuser, a combustion chamber external cartridge receiver, a central cavity rear step pre-combustion stage, an outer ring blunt body flame stabilizer main combustion stage, an inner ring blunt body flame stabilizer main combustion stage, a fuel supply system, an inner flame tube,an outer flame tube and an outlet supporting plate. An air flow with a deflection angle is diffused into the combustion chamber by the shunting type diffuser; the central cavity pre-combustion stage consists of a rear step, a top plate, a nozzle, a tangential slot inner ring and a tangential slot outer ring, and in the pre-combustion stage, the flame is stabilized by a low-speed recirculation zone generated by the rear step; the inner ring and the outer ring blunt body flame stabilizer main combustion stages consist of the inner ring, the outer ring and blunt body stabilizers with deflection angles, the high temperature and high pressure fuel jetted out of the inner ring and outer ring blunt body flame stabilizers is mixed with air, is ignited by the pre-combustion stage, and is burnt stably in a low-speed zone after a blunt body; and the outlet supporting plate is arranged between the inner flame tube and the outer flame tube and has an included angle with the axial line of the combustion chamber, and the outlet gas of the combustion chamber has an deflection angle. The central cavity stable fire tangential combustion chamber realizes tangential flow and tangential combustion while ensuring stable combustion for providing power; besides, the structure is simplified, and the weight of the combustion chamber is reduced.

Description

Technical field [0001] The invention is a gas turbine combustor with tangential intake, combustion and exhaust. While ensuring tangential flow and combustion, the combustor and the entire gas turbine are shortened in length, compact in structure and reduced in weight. Background technique [0002] The basic performance and structural distribution of modern gas turbine combustion chambers have reached a very high level. However, for modern gas turbine combustion chambers, there are still some problems and challenges. The development and application of new materials, new processes, new structures, and new concepts are Guarantee its source of continuous progress. [0003] The combustion organization of the conventional gas turbine combustor is based on the airflow mainly flowing in the axial direction, using the local low-speed recirculation zone of the main combustion zone to form a continuous ignition source for stable combustion, and adopting an appropriate fuel supply method to at...

AI Technical Summary

Problems solved by technology

[0006] In addition, due to the pressure of reducing the size and weight of aviation gas turbines, the length of the conventional combustion chamber is also greatly shortened, and the atomization, evaporation, mixing and combustion of fuel are all carried out in the axial direction, and the too short length of the combustion chamber It is bound to affect the combustion efficiency and outlet temperature distribution

Moreover, the axial combustion organization form in the conventional combustor makes the tangential momentum of the compressor outlet flow not well utilized, which needs to be considered in the future advanced combustor technology

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