GB888320A - Gas turbine engine - Google Patents

Abstract

888,320. Gas-turbine plant. ROLLSROYCE Ltd. Nov. 18, 1960 [Nov. 26, 1959], No. 40279/59. Class 110 (3). A gas-turbine engine has a front air intake portion which comprises an outer casing and an internal housing mounted within the casing by means of a plurality of struts, at least one of which is hollow, the casing and housing driving therebetween a passage through which air flows to the engine, the casing being readily releasable from the remainder of the engine, the casing having mounted externally thereon at least one engine auxiliary device which forms an operative part of the engine, drive transmission means for driving the engine auxiliary device or devices extending through a hollow strut, the drive transmission means being freely disengageable from a shaft disposed within the engine. The aircraft gas turbine jet-propulsion engine shown comprises a front casing portion 13 which is bolted to the casing portion 14 and so may be readily detached therefrom. Mounted on the front casing portion is a number of engine auxiliary devices including a centrifugal fuel pump 20, a filter and oil cooler 21, a fuel control unit 22, a backing pump 23, an emergency governor 24 and a pair of hydraulic pumps 25. Quillshafts 29 are utilized for transmitting drive from the compressor 17 to the auxiliary devices and they extend through certain of the hollow struts 28 which extend across the annular airintake passage 27 formed between the front casing portion and the bullet-shaped front bearing housing 26, the latter being supported from the casing portion by the struts. The quillshafts have bevel gears 30 at their inner ends, the bevel gears engaging with a bevel gear 31 on a shaft driven by the compressor. The engine auxiliary devices are disposed within a rectangular section housing 12 within which the engine is disposed, the housing being mounted either on the aircraft wing or fuselage. In Fig. 4, the engine auxiliary devices 36, 37, 38 are supported from the front casing portion of the engine by means of struts 40, 41 which extend through holes 42, 43, 44 in the wing or fuselage 39 within which the auxiliary devices are disposed. The quill-shaft 46 driving the device 37 extends through a hollow strut 28, but the quill-shafts 45, 47 are connected by bevel gears to quill-shafts 48, 49, these latter shafts extending through hollow struts 28.