Integrated diffusion oriented combustion chamber

Abstract

The invention relates to an integrated diffusion oriented combustion chamber which adopts a full ring combustion chamber structure. The integrated diffusion oriented combustion chamber mainly comprises a crankcase, a combustion liner and an oriented diffuser. The oriented diffuser realizes pneumatic and structural coupling, controls the tangential flow direction and carries out diffusion and speedreduction, and a local return low-speed zone is formed, thereby being good for flame linkage and tangential stable combustion; grading combustion is adopted, and a pre-combustion grade can be selected to work alone and work together with a main pre-combustion grade according to work conditions; the pre-combustion grade utilizes the trapped vortex combustion technology for stable work, goes into amain combustion zone to inflame a main combustion grade through a contraction outlet, and provides a stable ignition source for the main combustion grade; fuel of the main combustion grade is injected to a main combustion grade airflow in the oriented diffuser, atomization evaporation mixing with short distance is realized, and combustible mixture gas with uniform mixing is provided for the maincombustion zone. The invention allows tangential rotational flow of a gas compressor to directly go into the combustion chamber so as to realize tangential highly efficient and stable combustion; in addition, the discharge of pollutants is low, pre-rotation is provided for a turbine, the structure can be simplified, the weight is lightened, and the densification of a gas turbine is realized.

Description

technical field [0001] The invention relates to a full-ring combustor of a gas turbine adopting an integrated structure of a guider and a diffuser, which is suitable for tangential airflow conditions at the inlet and outlet of the combustion chamber, simplifies the structure of the combustion system of the gas turbine, and ensures stable and efficient combustion in a wide working range. Background technique [0002] Judging from the aerodynamic layout of conventional gas turbine combustors, it is mainly based on axial flow. However, whether it is an axial-flow compressor or a centrifugal compressor, the outlet air flow has a strong tangential swirl component. For a conventional combustion chamber, it must be equipped with an inlet de-rotation guide, and then use the expansion In order to successfully organize the combustion and ensure the performance of the combustion chamber, the compressor must be used to diffuse the pressure and reduce the speed. If the direction of the ...

AI Technical Summary

Problems solved by technology

From this point of view, from the outlet of the compressor to the inlet of the turbine, in order to meet the normal heating operation of the conventional combustion chamber and ensure the combustion performance, two-stage guides have to be added, which will inevitably increase the unnecessary length and weight of the engine and make the structure more complicated. , and the airflow friction and turning in the guide will cause a certain amount of aerodynamic loss, which also reduces the overall performance of the engine

[0003] 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 advanced combustor technology

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