A non-metallic tailcone in a tip turbine engine includes a tapered wall structure disposed about a central axis. The non-metallic tailcone is fastened to a structural frame in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.

A non-metallic tailcone in a tip turbine engine includes a tapered wall structure disposed about a central axis. The non-metallic tailcone is fastened to a structural frame in the aft portion of the tip turbine engine. The tip turbine engine produces a first temperature gas stream from a first output source and a second temperature gas stream from a second output source. The second temperature gas stream is a lower temperature than the first temperature gas stream. The second temperature gas stream is discharged at an inner diameter of the tip turbine engine over an outer surface of the tailcone. Discharging the cooler second temperature gas stream at the inner diameter allows a non-metallic to be used to form the tailcone.

A ventilation flow path, a cooling air flow path, a mixing space, and a mixed air flow path are formed in a gas turbine rotor. The ventilation flow path guides compressed air farther on an axially upstream side than an air discharge port of a compressor to an interior of a compressor rotor as compressor extracted air. The cooling air flow path guides cooling air to a part farther on an axially downstream side than the air discharge port. The compressor extracted air and the cooling air are mixed in the mixing space. The mixed air flow path guides mixed air containing the compressor extracted air and the cooling air into a turbine rotor.

A ventilation flow path, a cooling air flow path, a mixing space, and a mixed air flow path are formed in a gas turbine rotor. The ventilation flow path guides compressed air farther on an axially upstream side than an air discharge port of a compressor to an interior of a compressor rotor as compressor extracted air. The cooling air flow path guides cooling air to a part farther on an axially downstream side than the air discharge port. The compressor extracted air and the cooling air are mixed in the mixing space. The mixed air flow path guides mixed air containing the compressor extracted air and the cooling air into a turbine rotor.

A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger includes an first inlet connected to a high pressure compressor bleed, a first outlet connected to a high pressure turbine inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) coolant circuit and a second outlet connected to the sCO2 work recovery cycle. The sCO2 work recovery cycle is a recuperated Brayton cycle

A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger includes an first inlet connected to a high pressure compressor bleed, a first outlet connected to a high pressure turbine inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) coolant circuit and a second outlet connected to the sCO2 work recovery cycle. The sCO2 work recovery cycle is a recuperated Brayton cycle

A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger includes an first inlet connected to a high pressure compressor bleed, a first outlet connected to a high pressure turbine inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) work recovery cycle and a second outlet connected to the sCO2 work recovery cycle. The sCO2 work recovery cycle is an overexpanded, recuperated work recovery cycle.

A gas turbine engine includes a primary flowpath fluidly connecting a compressor section, a combustor section, and a turbine section. A heat exchanger includes an first inlet connected to a high pressure compressor bleed, a first outlet connected to a high pressure turbine inlet. The heat exchanger further includes a second inlet fluidly connected to a supercharged CO2 (sCO2) work recovery cycle and a second outlet connected to the sCO2 work recovery cycle. The sCO2 work recovery cycle is an overexpanded, recuperated work recovery cycle.

A gas turbine engine for an aircraft includes an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades, wherein a fan tip radius of the fan is measured between a centreline of the engine and an outermost tip of each fan blade at its leading edge; and a nacelle surrounding the fan and the engine core and defining a bypass exhaust nozzle, the bypass exhaust nozzle having an inner radius. An inner bypass to fan ratio of:

[00001]$\frac{\mathrm{the}.Math..Math.\mathrm{inner}.Math..Math.\mathrm{radius}.Math..Math.\mathrm{of}.Math..Math.\mathrm{the}.Math..Math.\mathrm{bypass}.Math..Math.\mathrm{exhaust}.Math..Math.\mathrm{nozzle}}{\mathrm{the}.Math..Math.\mathrm{fan}.Math..Math.\mathrm{tip}.Math..Math.\mathrm{radius}}$

is in the range from 0.4 to 0.65

A gas turbine engine for an aircraft includes an engine core having a turbine, a compressor, and a core shaft connecting the turbine to the compressor; a fan located upstream of the engine core, the fan having a plurality of fan blades, wherein a fan tip radius of the fan is measured between a centreline of the engine and an outermost tip of each fan blade at its leading edge; and a nacelle surrounding the fan and the engine core and defining a bypass exhaust nozzle, the bypass exhaust nozzle having an inner radius. An inner bypass to fan ratio of:

[00001]$\frac{\mathrm{the}.Math..Math.\mathrm{inner}.Math..Math.\mathrm{radius}.Math..Math.\mathrm{of}.Math..Math.\mathrm{the}.Math..Math.\mathrm{bypass}.Math..Math.\mathrm{exhaust}.Math..Math.\mathrm{nozzle}}{\mathrm{the}.Math..Math.\mathrm{fan}.Math..Math.\mathrm{tip}.Math..Math.\mathrm{radius}}$

is in the range from 0.4 to 0.65