GB830030A - Improvements in turbo-jet engines as regards í«reheatí» - Google Patents

Abstract

830,030. Jet-propulsion plant. ARMSTRONG SIDDELEY MOTORS Ltd. May 4, 1955 [May 20, 1954], No. 14797/54. Class 110 (3). [Also in Group XII] A reheat device for a turbo-jet engine comprises a fuel manifold 12 to be supplied with fuel through an altitude-responsive control 13, a flame stabilizer downstream of the manifold, and means for supplying a predetermined additional rate of flow of fuel and oxygen to the interior of the stabilizer at and above a predetermined altitude (say 40,000 ft.), the fixed rate of flow being sufficient for operation of the reheat device at a predetermined maximum operating altitude (say 100,000 ft.) of the engine, the altitude-responsive control 13 being operative to reduce to zero the flow of fuel to the fuel manifold at the predetermined maximum operating altitude. In Fig. 1 the flame stabilizer comprises an annular casing 15 supported by struts 16 of aerofoil cross-section. The casing 15 is flared at its open down-stream end, and fuel and oxygen are supplied to its interior at its closed upstream end by nozzles 18, 19 fed through passages within the struts 16. The axial spacing of the fuel manifold 12 is such that fuel from the manifold is at least partly vaporized by the time it reaches the stable flame zone at the downstream end of the stabilizer casing. The oxygen supply to the nozzle 19 may be in the form of liquid or gaseous oxygen or in the form of hydrogen peroxide. The fuel supply to manifold 12 is controlled by the altituderesponsiye control 13 to decrease progressively with increase in altitude until at maximum altitude all the reheating is effected by the fuel and oxygen supplied to the stabilizer 15; at low altitudes, below 40,000 ft, it is unnecessary to supply fuel and oxygen to the stabilizer 15.