Cooling structure of aero-engine combustor and aero-engine combustor

Abstract

The invention discloses a cooling structure for an aero-engine combustion chamber and the aero-engine combustion chamber. The cooling structure for the aero-engine combustion chamber comprises a cylinder wall, multiple air film cooling holes and multiple mixing holes are formed in the cylinder wall, the air film cooling holes and the mixing holes are arranged at intervals, the cross section of theinner wall surface of the cylinder wall and the section of the outer wall surface of the cylinder wall are both wavy in the circumferential direction of the cylinder wall, and the air film cooling holes and the reference holes penetrate through the inner wall surface and the outer wall surface. According to the cooling structure for the aero-engine combustion chamber and the aero-engine combustion chamber, the inner wall surface of the barrel wall and the outer wall surface of the barrel wall are both wavy so that the rigidity of the barrel wall can be increased to enable the cylinder wall tomeet relevant requirements, expensive materials are avoided, and manufacturing cost of the aero-engine combustion chamber is reduced.

Description

technical field [0001] The invention relates to the field of design and manufacture of an aero-engine combustor, in particular to a cooling structure of an aero-engine combustor and the aero-engine combustor. Background technique [0002] The working conditions of the aero-engine combustor are complex, such as high temperature, high air pressure, and complex flow field. Therefore, high-strength and high-rigidity materials are often required to manufacture the aero-engine combustor, which makes the aero-engine combustor expensive. Contents of the invention [0003] The invention provides a cooling structure of an aero-engine combustion chamber and the aero-engine combustion chamber. [0004] The cooling structure of the combustion chamber of the aero-engine according to the embodiment of the present invention includes a cylinder wall, and the cylinder wall is provided with a plurality of film cooling holes and a plurality of mixing holes, and the film cooling holes are arra...

AI Technical Summary

Problems solved by technology

[0002] The working conditions of the aero-engine combustor are complex, such as high temperature, high air pressure, and complex flow field. Therefore, high-strength and high-rigidity materials are often required to manufacture the aero-engine combustor, which makes the cost of the aero-engine combustor expensive

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