Patent ID: 9388741
Filing Date: 2016-07-12
CPC Classification: F02C,F05D,F28D,Y02T

Claim Text:
1. A gas turbine engine having a compressor section, a combustor section and a turbine section with a gas exhaust duct downstream of the turbine section, the gas turbine engine further comprising a recuperator disposed in the gas exhaust duct, the recuperator including a casing of circular cross-section surrounding at least a core having channels including pre-combustion stage air channels and exhaust gas channels for directing hot gases from the turbine section into heat exchange relationship with pre-combustion stage air passing through respective channels, and inlet and outlet openings defined in the casing for the passage of said hot gases through the exhaust gas channels in the core, feeder members extending radially across the outlet opening for passing the pre-combustion stage air through the air channels of the core, and header members extending radially across the inlet opening of the casing for receiving and redirecting air from the pre-combustion stage air channels in the core towards the combustor section, the feeder and header members each having a tapered configuration from the casing to the axial center of the casing so as to maintain a relatively constant pressure over the radial extent of the respective feeders and headers, wherein an outer casing surrounds the casing surrouding the core and defines air ducts in fluid communication with the compressor section and the feeder members for conducting the pre-combustin stage air to the feeder members and separate air ducts for conducting the hot air from the header memebers to the combustor section.