航空发动机燃烧室的冷却结构及航空发动机燃烧室

韩品连; 张坤; 魏存驹; 张亮

韩品连

南方科技大学

南方科技大学

518055 广东省深圳市南山区西丽学苑大道1088号

深圳意动航空科技有限公司

518000 广东省深圳市南山区桃源街道学苑大道1088号南方科技大学慧园5栋303室 (广东,深圳,南山区)

深圳意动航空科技有限公司

518000 广东省深圳市南山区桃源街道学苑大道1088号南方科技大学慧园5栋303室 (广东,深圳,南山区)

CN201810005871.0

2018-01-03

CN108317542B

2020-02-07

2020-02-07

未缴年费 ; 权利转移

2024-01-12

授权发明

第一

本发明公开了一种航空发动机燃烧室的冷却结构及航空发动机燃烧室。航空发动机燃烧室的冷却结构包括筒壁，筒壁开设有多个气膜冷却孔和多个参混孔，气膜冷却孔与参混孔间隔设置，沿筒壁的周向上，筒壁的内壁面的截面和筒壁的外壁面的截面均呈波浪形，气膜冷却孔与参混孔均贯穿所述内壁面及所述外壁面。本发明实施方式的航空发动机燃烧室的冷却结构及航空发动机燃烧室中，筒壁的内壁面和筒壁的外壁面均呈波浪形可以增加筒壁的刚度，使得筒壁可以满足相关需求，避免采用昂贵的材料，降低了航空发动机燃烧室的造价。

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.

F23R3/42

F23R3/42

（TRANSFER OF PATENT RIGHT）[2021-05-25][CN]

1

1

黄德海

北京清亦华知识产权代理事务所(普通合伙)

PatSnap

韩品连,张坤,魏存驹,等. 航空发动机燃烧室的冷却结构及航空发动机燃烧室[P]. 2020-02-07.