Patent GB-978462-A (GB)
Title: Gas turbine by-pass engine
Inventor: SHAW WILLIAM
IPC: F02K1/74
Filed: 1963-10-28
Abstract: 978,462. Deflecting propulsive gases. ROLLSROYCE Ltd. Oct. 28, 1963, No. 42502/63. Heading B7G. [Also in Division F1] A gas turbine by-pass type jet engine comprises an annular flow duct in which are disposed in series flow compressor means, combustion equipment and turbine means, an annular bypass duct surrounding the flow duct through which a portion of air from the compressor flows by-passing the combustion equipment and the turbine means, and an annular fan duct which surrounds the by-pass duct and in which is mounted a fan driven by the engine. The engine comprises also an exhaust duct which communicates at its upstream end with the downstream ends of the flow duct, the by-pass duct and the fan duct, the downstream end of the common exhaust duct having a propulsion nozzle. The downstream end of an engine in accordance with the invention is shown in Fig. 2, the engine comprising an annular flow duct 14 in which are disposed a low pressure compressor, a high pressure compressor, combustion equipment (none of these being shown), a high pressure turbine 18 which drives the high pressure compressor through shaft 21 and a low pressure turbine 19 which drives the low pressure turbine through shaft 22, the turbine exhaust gases discharging into duct 31. A by-pass duct 25 surrounds the engine easing 13 and a portion of air from the low pressure compressor passes through the duct 25 into the exhaust duct 31. A fan duct 27 formed between walls 24, 26 is disposed around the by-pass duct 25 at the downstream end thereof and fan blades 30 are disposed therein, the fan blades being connected to and driven by the low pressure turbine 19, the air delivered by the fan discharging into the common duct 31 at the downstream end of which is a nozzle 32. Associated with the exhaust duct 31 is a thrust reverser device comprising a pair of eyelid-type members 34 which are pivotally mounted at 33 and are movable between an inoperative position shown in full lines in which they close off lateral outlets 35, and an operative position shown in chain-dotted lines in which they close off the nozzle 32 and divert the exhaust stream through the outlets 35. Deflector vanes 36 are provided in the outlets 35 to assist in directing the gases in a forward direction. The members 34 are actuated by a pair of rams 40. In the embodiment shown in Fig. 3, a pair of closure doors 41 is provided so as to close the outer portions of the openings 35a when the thrust reverser members are in the inoperative positions. The doors 41 are pivotally mounted at 42 and are movable by rams 47 between the closed position shown in full lines and the open position shown in dotted lines. Each ram 47 acts on a lever 45 pivotally mounted at 46, the lever carrying a roller 44 which engages in a slot 43 formed in the closure door. In a similar embodiment the same rams are utilized to actuate both the thrust reverser members 34 and the closure doors 41, a bell-crank lever being used in place of the simple lever shown in Fig. 2, the second arm of the bell-crank lever being connected to the closure door. In Fig. 5 the ram 64 is connected to a lever 54, one arm of the lever being connected to a thrust reverser member 34c and the other arm of the lever being connected by a link 55 to one arm 56 of a bell-crank lever, the second arm 57 of which is connected to the closure door 41c. The rearward end of the door is connected to a link 62 which is mounted for pivotal movement at 63. In a further similar embodiment the closure door is so mounted that in moving from its closed position to its open position it swings first radially outwardly and rearwardly and then radially inwardly and rearwardly. In Fig. 7, the closure door 41e is of cylindrical form and is movable axially between closed and open positions.