Patent ID: 9103281
Filing Date: 2015-08-11
Classification: D01H,F01D,F02C,F04D

Abstract:
1. A gas turbine engine comprising: a compressor section with rotational compressor components rotatable with respect to static compressor components; a compressed air bleed arrangement that cools one or more other components of the gas turbine engine and that takes a flow of compressed air from the compressor section along an off-take passage, wherein the off-take passage opens in the compressor section in a stepped arrangement at an off-take port and comprises a radially outer surface that is rotatable, in use, with the rotational compressor components, wherein the off-take passage includes one or more vanes shaped to increase a tangential velocity of a flow of compressed air in the off-take passage in comparison to a flow of compressed air at the off-take port, and wherein the compressed air bleed arrangement is operable to provide the flow of compressed air along the off-take passage with higher static pressure than the flow of compressed air at the off-take port, and wherein the one or more other components of the gas turbine engine includes at least one rotating component of a turbine section of the gas turbine engine and the compressed air bleed arrangement delivers the flow of compressed air from the compressor section to the at least one rotating component with a tangential velocity that is substantially matched to a tangential velocity of the at least one rotating component.