GB1268301A - Improvements in or relating to gas turbine engines - Google Patents

Abstract

1,268,301. Gas turbine engines; cooling. ROLLS-ROYCE Ltd. Jan. 13, 1970, No.1564/70. Heading F1G. A gas turbine engine comprises stator structure and a bladed rotor, sealing means being disposed therebetween, the stator structure defining at least two flow paths for the passage of cooling fluid, one of the flow paths being arranged to supply cooling fluid to the bladed rotor. The engine shown comprises inlet guide vanes 10 supported at their inner ends by support ring 12 having flanges 16, 18 and at their outer ends by support ring 14, the inner support ring 12 being connected to a structural member 30. The guide vanes provide two flow paths 36, 38 for flow of cooling air, air flowing through the path 36 discharging through openings formed at the leading edges of the guide vanes. The engine comprises also a rotor 48 having blades 50 which carry shrouding 52. The rotor is formed with a seal element 54 which co-operates with a seal element 22 on the flange 18 of the support ring 12. The rotor also carries seal elements 56, 58 which co-operate with seal elements 32, 24 carried by the structural member 30 and the support ring 12 respectively. Openings 28 are formed in the support ring 12 and are provided with swirl vanes 26. Hollow spokes 34 are disposed between the openings 28. Cooling air is supplied through the openings 28 and swirl vanes 26 into the chamber 60 on to the rotor 48, this constituting one flow path, the air passing through the seal 24, 58 into a chamber 62, also through the seal 54, 22, through openings 64 into the second flow path. Cooling air is also supplied through the seal 32, 56 into the chamber 62, the air then flowing through the hollow spokes 34 and through the passages 38 in the guide vanes 10 into the chamber 42. The air then flows through openings 44 to chamber 46, through swirl vanes 40 on to the shroud elements 52. This constitutes the second flow path.