| 摘要 |
1,108,705. Gas turbine combustion chambers. GENERAL ELECTRIC CO. May 25, 1966 [Oct. 1, 1965], No.23404/66. Heading F1L. The wall of a cooling structure, such as the wall of an annular flame tube in a gas turbine engine combustion chamber, is formed by axially overlapping rings 26, 28 having a corrugated spacer 32 welded there-between to define passages for the admission of cooling air. In order to produce a substantially uniform temperature profile around ring 28, crimps or weirs 42 are formed in the corrugations to reduce the crosssectional flow area of the cooling air passages. Ring 26 extends downstream of spacer 32 to form a region 44 where the velocity of the entering cooling air is reduced by diffusion. Additional cooling air is supplied through holes 48 aligned with the risers 40 of the corrugations. |
