A gas turbine engine includes a core engine section, including a compressor section, a primary combustor and a turbine section positioned within a core flow path of the gas turbine engine; a ramjet section, including a supplemental combustor disposed within a ram duct, the ram duct located radially outside the core engine section; and a core engine housing positioned radially outward of the core engine section and radially inward of the ramjet section.

A power generation apparatus and a power system are provided. The power generation apparatus includes a first transportation means, a gas turbine and a generator, the first transportation means has a first platform, a first housing is provided on the first platform, the gas turbine is arranged in the first housing and has a first input terminal and a first output terminal, the generator is arranged in the first housing and has a second input terminal and a second output terminal, the first output terminal is connected with the second input terminal.

A power generation apparatus and a power system are provided. The power generation apparatus includes a first transportation means, a gas turbine and a generator, the first transportation means has a first platform, a first housing is provided on the first platform, the gas turbine is arranged in the first housing and has a first input terminal and a first output terminal, the generator is arranged in the first housing and has a second input terminal and a second output terminal, the first output terminal is connected with the second input terminal.

A fully compounding rotorcraft includes a fuselage having first and second wings extending therefrom and configured to provide lift compounding responsive to forward airspeed. A twin boom includes first and second tail boom members that extend aftward from the first and second wings. An empennage is coupled between the aft ends of the tail boom members. An anti-torque system includes a tail rotor that is rotatably coupled to the empennage. An engine is disposed within the fuselage and is configured to provide torque to a main rotor assembly via an output shaft and a main rotor gearbox. An auxiliary propulsive system is coupled to the fuselage and is configured to generate a propulsive thrust to offload at least a portion of a thrust requirement from the main rotor during forward flight, thereby providing propulsion compounding to increase the forward airspeed of the rotorcraft.

A fully compounding rotorcraft includes a fuselage having first and second wings extending therefrom and configured to provide lift compounding responsive to forward airspeed. A twin boom includes first and second tail boom members that extend aftward from the first and second wings. An empennage is coupled between the aft ends of the tail boom members. An anti-torque system includes a tail rotor that is rotatably coupled to the empennage. An engine is disposed within the fuselage and is configured to provide torque to a main rotor assembly via an output shaft and a main rotor gearbox. An auxiliary propulsive system is coupled to the fuselage and is configured to generate a propulsive thrust to offload at least a portion of a thrust requirement from the main rotor during forward flight, thereby providing propulsion compounding to increase the forward airspeed of the rotorcraft.

A power generation transport includes a gas turbine, an inlet plenum coupled to an intake of the gas turbine, a generator driven by the gas turbine, and an air intake and exhaust module including an air inlet filter housing, an intake air duct coupled to the housing at a first end and to the inlet plenum at a second end, and an exhaust collector coupled to an exhaust of the gas turbine. The transport further includes at least one base frame. The frame mounts and aligns the gas turbine, the inlet plenum, the generator, and the air intake and exhaust module. The intake air duct is mounted on the base frame so as to be disposed underneath the gas turbine, and extend along the base frame from an exhaust end side of the gas turbine to an intake end side, in a longitudinal direction of the power generation transport.

A power generation transport includes a gas turbine, an inlet plenum coupled to an intake of the gas turbine, a generator driven by the gas turbine, and an air intake and exhaust module including an air inlet filter housing, an intake air duct coupled to the housing at a first end and to the inlet plenum at a second end, and an exhaust collector coupled to an exhaust of the gas turbine. The transport further includes at least one base frame. The frame mounts and aligns the gas turbine, the inlet plenum, the generator, and the air intake and exhaust module. The intake air duct is mounted on the base frame so as to be disposed underneath the gas turbine, and extend along the base frame from an exhaust end side of the gas turbine to an intake end side, in a longitudinal direction of the power generation transport.

An airplane is provided. The airplane includes a pressurized medium, a turbine, and a valve. The turbine includes at least one nozzle. The valve is located upstream of the turbine. The valve provides the pressurized medium to the at least one nozzle of the turbine according to an operational mode.

A system for controlling a turbine is disclosed. The system includes a turbine control fuel governor that has a plurality of VCPIDs operating in parallel with one another. Each VCPID is associated with a respective turbine parameter and one or more external parameters. Each VCPID incorporates feedback from the parallel operating VCPIDs to feed an integral term of a current VCPID in the following manner: a previous derivative gain and a previous proportional gain are summed and subtracted from a selected output for the turbine to yield a result, and the result is input to an integral gain portion of the current VCPID.

An aircraft hybrid propulsion system (5) comprising an inboard gas turbine engine (10a, 10c) and an outboard gas turbine engine (10b, 10d), each comprising a propulsor (12a, 12b) and a respective electric machine (32a, 32b) coupled to one or more engine shaft (24a, 24b). An electrical interconnection (34) is provided between the electric machine (32a) of the inboard gas turbine engine (10a) and the electric machine (32b) of the outboard gas turbine engine (10b). A controller (36) is configured to transfer electrical power between the inboard gas turbine engine electrical machine and the outboard gas turbine engine electrical machine when a thrust setting change is selected.