| 摘要 |
887,829. Generating combustion products under pressure. UNITED AIRCRAFT CORPORATION. Nov. 4, 1959 [March 31, 1959], No. 37442/59. Class 51 (1). A flame tube for a combustion system, for example of a gas-turbine engine, comprises an outer wall in the form of a sleeve, an annular end cap at the upstream end of the outer wall and a plurality of fuel nozzles disposed in the end cap concentric with the outer wall, the end cap having a central opening for admission of air into the flame tube and swirl-producing means disposed in the path of air admitted through the opening. The flame tube shown comprises an outer wall 2, an annular end cap 6 having a central opening and a ring of openings 10 in which are disposed fuel nozzles 8, and an inner sleeve 4 extending from the central opening. A ring of swirl vanes 24 is disposed at the downstream end of the sleeve 4, the vanes being disposed between an outer ring 26 and an inner dome-shaped fairing member 28. A central air inlet passage 14 is provided within the sleeve 4 and an annular combustion space 12 is provided between the outer wall 2 and the inner sleeve 4. The wall 2 and the sleeve 4 are formed of short frusto-conical rings which overlap one another and have air inlet openings 22 therein. The transition piece 16 is of cylindrical form at its upstream end 18 where it engages the outer wall 2, and is of segmental form at its downstream end 20 from which the combustion gases discharge to the turbine nozzle. |
