Axial swirler structure with oil spraying structure blades

Abstract

The invention provides an axial swirler structure with oil spraying structure blades. The blades of which the interiors are provided with fuel oil channels are adopted in an axial swirler, fuel oil issprayed to air passing through the axial swirler through oil spraying holes formed in the blades, and meanwhile the back portions of the side faces of the blades are provided with supporting plates.The axial swirler structure with the oil spraying structure blades has the advantages that oil spraying mixing is conducted when the air passes through the axial swirler, the oil-air mixing effect isimproved to a certain extent, the fuel oil collides with the inner sides of the supporting plates, and the fuel oil atomization evaporation effect is effectively improved; meanwhile, the supporting plates can decrease the air flow speed and stabilize air flow; and through the combined action of the aspects, the combustion efficiency and the combustion stability in a combustion chamber can be effectively improved, combustion is fuller, smoke and nitric oxide emission is reduced, and the effects that flame is stable, the high-altitude ignition property is good, and the stealth performance is improved are achieved.

Description

technical field [0001] The invention belongs to the field of gas turbine engines, and in particular relates to an axial swirler structure with blades of an oil injection structure. Background technique [0002] Modern aero-engine combustors are built on the basis of high performance, high reliability, and a wide and stable operating range. As the development of the engine continues to pursue a high thrust-to-weight ratio, it must work at a higher pressure ratio and combustion chamber inlet and outlet temperatures. For military engine combustors, high combustion efficiency, stable flame, good high-altitude ignition and low nitrogen oxide emissions are key indicators. [0003] The head structure of the traditional main combustion chamber is mainly a single center nozzle for fuel injection. The oil and gas mixing effect is not ideal, resulting in incomplete combustion, carbon deposits in the nozzle, obvious smoke exhaust, and high nitrogen oxide content in the outlet. The vis...

AI Technical Summary

Problems solved by technology

[0003] The head structure of the traditional main combustion chamber is mainly a single center nozzle for fuel injection, and the oil-gas mixing effect is not ideal, resulting in incomplete combustion, carbon deposits in the nozzle, obvious smoke exhaust and high nitrogen oxide content in the outlet, and exhaust leakage. The visibility of smoke and nitrogen dioxide greatly affects the stealth performance of military aircraft and greatly damages the environment

In addition, the intake flow rate greatly affects the quality of high-altitude ignition, and the high intake flow rate greatly increases the difficulty of high-altitude ignition.

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