| 摘要 |
1,180,706. Gas turbine combustion chambers. ROLLS-ROYCE Ltd. Aug. 2, 1968, No.37091/68. Heading F1L. A flame tube 22 for a gas turbine engine has a wall of double-skinned construction over at least a greater part of its length comprising an internal skin 30 spaced within an external skin 32 to define a passage 31 and apertures 34 in the skin 32 to direct jets of cooling air on to the skin 30 at a substantial angle thereto, the passage 31 being open at its downstream end 42 to direct a film of cooling air over the internal surface of the flame tube wall 44 downstream thereof. As shown, the double-skinned construction is applied to only the radially inner wall 28 of an annular flame tube, but the tube may be entirely double-skinned or the construction applied to can type flame tubes. The downstream end of skin 32 carries a flange 46 which is slidingly located on a mounting and sealing shoulder 48 on a part 50 of the surrounding air casing. |
