A gas turbine engine of an aircraft includes: an engine core having a turbine including a lowest pressure rotor stage, a turbine diameter, a fan including a plurality of fan blades extending from a hub, an annular fan face at a leading edge of the fan; wherein a downstream blockage ratio is:

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and a quasi-non-dimensional mass flow rate Q defined as:

[00002]

A dryer includes a hollow casing, a fan disposed inside the casing so as to cause air to be introduced into the casing and to be discharged therefrom, a heater disposed inside the casing to heat the air introduced into the casing by the fan, and a discharge tube including an inlet into which the air is introduced, and an outlet from which the air is discharged. The fan includes a first fan and a second fan, which rotate in opposite directions about an imaginary axis shared by the first and second fans. A discharge amount or a discharge rate can be controlled in a stepwise manner. The discharge tube is disposed inside the casing so as to be rotated in at least one direction, thereby diffusely discharging drying air to a region desired to be dried.

A gas turbine engine of an aircraft includes: an engine core having a turbine including a lowest pressure rotor stage, a turbine diameter, a fan including a plurality of fan blades extending from a hub, an annular fan face at a leading edge of the fan; wherein a downstream blockage ratio is:

An aeroderivative gas turbine provided with a casing, a compressor including a rotor mounted on a generator shaft supported for rotation in the casing, a high pressure turbine arranged in the casing and with a rotor mounted on the generator shaft for co-rotation with the compressor rotor, a combustor, a power turbine arranged in the casing and including a rotor mounted on a turbine shaft to drive a load, wherein a thermal insulation coating is present to reduce heat dispersion through the casing.

A fluid cooler for installation in a bypass duct of a turbofan gas turbine engine and associated methods are provided. The fluid cooler includes an inlet duct, a heat exchanger and an outlet duct. The inlet duct includes an inlet protruding into the bypass duct to receive a portion of the bypass air into the inlet duct. The heat exchanger is in fluid communication with the inlet duct. The heat exchanger facilitates heat transfer between a fluid and the portion of bypass air received into the inlet duct. The heat exchanger defines a general flow direction for the portion of bypass air that is different from the main flow direction of bypass air inside the bypass duct. The outlet duct conveys the portion of bypass air from the heat exchanger back to the bypass duct.

A turbofan includes a circular end plate, a ring-shaped shroud facing the end plate, and a plurality of blade members disposed between the end plate and the shroud. An annular portion of a space between the end plate and the shroud where the blade members are disposed is a pressure-increase flow path. The turbofan causes air to flow from an inner peripheral side to an outer peripheral side of the pressure-increase flow path. A cross-sectional area of the pressure-increase flow path increases gradually from an upstream end toward a downstream end of the pressure-increase flow path.

An aeroderivative gas turbine provided with a casing, a compressor including a rotor mounted on a generator shaft supported for rotation in the casing, a high pressure turbine arranged in the casing and with a rotor mounted on the generator shaft for co-rotation with the compressor rotor, a combustor, a power turbine arranged in the casing and including a rotor mounted on a turbine shaft to drive a load, wherein a thermal insulation coating is present to reduce heat dispersion through the casing.

An airflow deflector is provided that includes at least one liner attachment flange, a deflector panel, and at least one deflector leg. The at least one liner attachment flange has a liner side surface and an opposing outer surface. The at least one deflector leg extends between and is attached to the at least one liner attachment flange. The at least one deflector leg extends a distance between the deflector panel and the liner attachment flange to maintain the deflector panel a separation distance from the liner attachment flange. The airflow deflector is configured for insertion of the at least one deflector leg and the deflector panel within a liner aperture.

An aeroderivative gas turbine provided with a casing, a compressor including a rotor mounted on a generator shaft supported for rotation in the casing, a high pressure turbine arranged in the casing and with a rotor mounted on the generator shaft for co-rotation with the compressor rotor, a combustor, a power turbine arranged in the casing and including a rotor mounted on a turbine shaft to drive a load, wherein a thermal insulation coating is present to reduce heat dispersion through the casing.

An integrated fuel cell and engine combustor assembly includes an engine combustor having a combustion chamber fluidly coupled with a compressor and a turbine. The assembly also includes a fuel cell stack circumferentially extending around the combustion chamber of the combustor. The fuel cell stack includes fuel cells configured to generate electric current. The fuel cell stack is positioned to receive discharged air from the compressor and fuel from a fuel manifold. The fuel cells in the fuel cell stack generate electric current using the discharged air and at least some of the fuel. The fuel cell stack is positioned to radially direct partially oxidized fuel from the fuel cells into the combustion chamber of the combustor. The combustor combusts the partially oxidized fuel into one or more gaseous combustion products that are directed into and drive the downstream turbine.