Patent GB-1102571-A (GB)
Title: Improvements in jet propulsion power plants
Inventor: LANE RAYMOND JOHN
IPC: F02K1/52
Filed: 1963-12-12
Abstract: 1,102,571. Jet propulsion plant; gas turbine jet engines. BRISTOL SIDDELEY ENGINES Ltd. Dec. 11, 1964 [Dec. 12, 1963], No.49167/63. Headings F1G and F1J. An aircraft jet propulsion power plant comprises at least two jet propulsion engines suitable for operation respectively at progressively higher ranges of supersonic flight speeds, there being a separate nozzle for the exhaust of each engine, and a trough structure into one end of which the nozzles discharge, that end of the trough being otherwise closed and the other end open. The nozzle of the lowest flight speed engine is disposed adjacent the base of the trough, the other nozzles being displaced therefrom towards the open side of the trough in the order of their increasing corresponding flight speeds, there being means for preventing reverse flow through a lower speed engine when a higher speed engine is operating and it is not. In a first embodiment the power plant comprises a gas turbine jet engine 11 and a ram jet engine 12 disposed in a common pod. The gas turbine engine jet nozzle 13 changes from circular to rectangular section, a portion 15 of the lower wall being pivotally mounted at 16 whereby the hinged portion may be moved to the position 15a indicated by broken lines so as to close off the nozzle passage. The ram jet engine 12 comprises three sets of combustion equipment 21, see Fig. 2, and the upper wall of the jet nozzle comprises a portion 23 pivotally mounted at 24 whereby it may be moved to the position 23a indicated in broken lines when the ram jet engine is not in operation. The gas turbine jet nozzle and the ram jet nozzle both discharge into a trough-shaped member 17 which has a closed upper side 19 and an open lower side 18. The gas turbine jet engine is suitable for propelling the aircraft up to a lower supersonic flight speed say Mach 2À5 and the ram jet engine up to a high supersonic flight speed say Mach 4. In a transition phase both engines would be in operation. In a second embodiment the power plant is mounted partly in the wing 30 of an aircraft and partly in a nacelle 34 projecting below the wing, the nacelle being divided by horizontal partitions 36 and 37 and by vertical partitions 35 into three horizontal rows of rectangular section passages. Each passage 38 of the top row houses a gas turbine jet engine 31 each engine being supported on trunnions 39 and having a jet nozzle 61 which changes from circular to rectangular crosssection, the upper and lower walls of the nozzle being constituted by pivoted flap members 62 which may be moved to the positions indicated by broken lines in which they abut a vane 63 so as to close off the nozzle passage. The air intake of each gas turbine jet engine may be closed by means of a pair of shutters 59 which are pivotally mounted at 60. A diaphragm 40 is provided to close the space between the engine 31 and the wall of the passage 38. Boundary layer air tapped off at 55 is discharged into the passage 38 downstream of the diaphragm 40. Each passage 41 of the second row houses a composite ram jet engine 32 for the intermediate speed range, the term "composite" indicating that it has a common air intake system with the gas turbine jet engines. Each ram jet engine 32 is provided with a variable throat area convergent-divergent nozzle constituted by flaps 69, the flaps being movable to the positions indicated by broken lines when the ram jet engine is not in operation. Each passage 42 of the lowermost row of passages houses a high speed ram jet engine 33 for the highest speed range. The jet nozzle of each engine 33 is constituted by a fixed lower wall 75 and an upper wall 37 having adjustable flaps 73 which may be moved to the position indicated in broken lines when the engine is not in operation. The jet nozzles of the gas turbine jet engines, the composite ram jet engines and the high speed ram jet engines discharge into a trough member 64 having a closed upper wall 66 and an open lower wall 65. The gas turbine jet engines and the composite ram jet engines are supplied with air from a common intake diffuser passage 45 which is defined by a lower fixed wall 37 and an upper wall comprising two members 46, 47 which are in telescopic engagement at 48. The member 46 is pivotally mounted to fixed structure at 49 while the forward member 47 is pivotally connected at 50 to the rearward end of an intake compression ramp which comprises two members 51, 52 pivotally connected together at 53, the forward member 51 being pivotally connected to fixed structure at 54. The ramp system is adjustable by means of jacks 56, 57 from the take-off position shown in full lines to the high speed position shown in chain dotted lines in which the diffuser passage 45 is closed off and air then passes only to the subsonic diffuser passage 58 to the high speed ram jet engines. In a third embodiment, Fig. 13 a gas turbine by-pass type jet engine 80 and a ram jet engine 84 have jet nozzles which discharge into a common trough-shaped member 17 open at its lower side. The by-pass engine has a jet nozzle 88 having an adjustable flap member 89 which may be moved to the position indicated at 89a so as to close off the jet nozzle. The ram jet nozzle is constituted in part by the adjustable flap member 89 and in part by a pair of adjustable ramp members 91, 92. Means are provided at 82 for supplying fuel into the by-pass passage 83 and means 86 and 87 are provided for supplying fuel to the ram jet engine.