GB733362A - Improvements in or relating to gas turbine engines - Google Patents

Abstract

733,362. Gas turbine plant. BRISTOL AEROPLANE CO., Ltd. July 7, 1953 [July 7, 1952], No. 17071/52. Class 110 (3). [Also in Group XII] In a gas turbine plant comprising a compressor and a turbine 1, 2 mounted on a shaft 4 and having combustion equipment comprising a plurality of flame tubes 20 circumferentially disposed in an annular air casing 16, 31, the turbine end of the shaft is journalled in a bearing 6 which is supported by a disclike structure 9 arranged transversely of the air casing. The disc structure 9 is supported between successive sections 16, 18 of the inner wall of the air casing and is also secured to the outer wall 31 of the air casing, the disc 9 having for each flame tube 20 a hole receiving the downstream end thereof and also supporting the upstream end of a nozzle duct 48 for the flame tube. The engine shown is a jet propulsion engine and the turbine motor comprises discs 1, 2 secured together by a sleeve 3 and secured to the hollow shaft 4. Cooling air flows through the hollow shaft and between the motor discs as shown by the arrows e, and escapes into the gas stream. Cooling air also passes through the annular space 70 between the shaft 4 and the tubular partition 71, through the bearing 6, to which oil is supplied by a nozzle 73, into the tubular member 72 at the centre of the turbine rotor and then across the downstream face of the rotor as shown by the arrows f. Some cooling air also flows through the holes 76 to the-space 75 and so across the upstream face of the turbine rotor as shown by the arrows g. Cooling air from the space 50 adjacent the air casing wall 31 passes through openings in the disc 9 to the space between the stator part 32 and the flame tube nozzle ducts 48 through openings 52 into the space between the stress-carrying member 38 and the stator casing 32, 33, 34. From here the air flows through openings 53 in the duct wall 39, through the hollow struts 41 and int to the fairing bullet 40 and thence into the jet stream. Cooling air adjacent the inner air casing wall 16 flows through openings 60 in the disc 9, between the section 18 of the inner air casing and partition 61 and then over the roots of the guide blades 19 and into the gas stream adjacent the roots of the first row of rotor blades 63.