GB1476237A - Support structure in gas turbine engines - Google Patents

Abstract

1476237 Gas turbine engines - arrangement of seals ROLLS-ROYCE (1971) Ltd 15 Aug 1975 [19 Sept 1974] 40829/74 Heading F1G and FIT The invention relates to a seal structure for a gas turbine engine in which the stationary part of the seal is supported from the turbine shaft by means of a stationary panel supported on the shaft by means of a bearing. The turbine assembly shown is the HP turbine of a gas turbine engine, the turbine comprising a rotor disc 24 carrying blades 7 and connected to a shaft 14 rotatably supported in bearings (15), (16) Fig. 1 (not shown). The assembly comprises also inlet guide vanes 6 carried by stator structure 43, 28. A bearing assembly 20 is mounted on the shaft 14 and carries a stationary panel 21 comprising a frusto-conical portion and a radial web 26 which carries at its periphery a piston ring type seal 27 which engages the stator structure 28, the frictional contact serving to prevent rotation of the panel 21. The radial web 26 of the panel 21 carries a flange member 22 which carries the stator portion 25 of a seal, the rotary portion 23 of the seal being carried by the turbine rotor disc 24. The radial web 26 is formed with openings 35, 40 through which cooling air supplied through passage 34 flows as indicated by the arrows. Some of the air flowing through openings 35 flows radially inwardly across the surface of the rotor disc 24, through openings 42, through the central opening of the rotor disc to the downstream side of the disc; a second portion of air from the openings 35 flows radially outwards through passages 36 in the rotary seal member 23 to the chamber 37 thence through passages 39 in the rotor blades 7. Cooling air flowing through the openings 40 enters the chamber beneath the blade platforms 30, the air passing from there through passages 41 in the rotor blades.