Patent GB-999663-A (GB)
Title: Gas turbine engine and aircraft provided therewith
Inventor: WILDE GEOFFREY LIGHT
IPC: F23R3/18
Filed: 1963-03-29
Abstract: 999,663. Gas turbine jet engines; combustion equipment. ROLLS-ROYCE Ltd. March 23, 1964 [March 29, 1963], No. 12675/63. Headings F1J and F1L. [Also in Division B7] A gas turbine jet propulsion engine comprises in flow series compressor equipment, combustion equipment, turbine equipment and a jet pipe through which combustion gases are discharged to atmosphere, the engine having also an outlet duct adapted to be supplied with compressed air direct from the compressor equipment of the engine to provide thrust, the outlet duct having disposed therein combustion equipment including combustion stabilizing means which is movable between an operative position in which it presents a relatively large impedance to air flow, and an inoperative position in which it presents a relatively small impedance to air flow. The aircraft shown in Fig. 1 is provided with two gas turbine jet engines each comprising low pressure and high pressure compressors 13, 14, combustion equipment 15, high and low pressure turbines 16, a jet pipe 17 and discharge nozzle 18. Each engine comprises also an outlet duct 20 which is adapted to receive through an annular chamber 19 part of the air delivered by the low pressure compressor 13, the outlet duct terminating in a jet nozzle 21 which may be moved so as to direct the air discharging therefrom either downwardly, rearwardly or forwardly. The two engines are disposed one on either side of the longitudinal axis of the aircraft and the jet pipes 17 of the two engines cross over each other so that the outlet nozzles 18 and 21 of one engine are disposed on opposite sides of the longitudinal axis of the aircraft. Disposed within each outlet duct 20 is combustion equipment comprising combustion stabilizing means in the form of two sets 24, 25 of semi-circular flame-holding gutters of substantially V-section 24a to f and 25a to f, the gutters being mounted on frame members 26, 27 which are pivotally mounted about the common diameter 28 of the semicircular gutters, the gutters being movable between an open operative position when fuel is being burned in the outlet duct and shown in full lines in Fig. 3 and a closed, inoperative position when air only is being discharged through the outlet duct as indicated by broken lines. An ignition device is provided to ignite fuel which is supplied into the outlet duct through the supply pipe 30 to the flame holding gutters. The ignition device which is described in more detail in Specification 999,664 comprises a combustion chamber 32 disposed on the axis of the outlet duct 20 and arranged to be supplied with air from the high pressure compressor 14 through annular duct 33 and swirlers 36 and with fuel through an injector disposed within aperture 35. Combustion gases discharge from the chamber 32 through four outlets 37 and ignite the fuel and air mixture formed downstream of the flame-holding gutters. An air casing 34 is disposed around the combustion chamber 32 and cooling air ducts 38 are disposed round the four outlets 37. Reheat combustion equipment may be provided in the jet pipes 17.