A turbine engine including a core engine cowl including a compartment, and a cooling system positioned within the compartment. The cooling system includes a cooling fan configured to exhaust heat from the compartment, a temperature sensor configured to monitor a temperature within the compartment, and a controller coupled in communication with the cooling fan and the temperature sensor. The controller is configured to actuate the cooling fan when the temperature is greater than a threshold.

Cooling a torque probe involves an elongated sleeve extending along a sleeve axis between a first sleeve end and a second sleeve end. The sleeve is mountable about the torque probe to define a flow passage between an inner surface of the sleeve and an outer surface of the torque probe. The flow passage is in fluid communication with a flow passage inlet of the sleeve and with a flow passage outlet of the sleeve spaced apart along the sleeve axis from the flow passage inlet. A cooling fluid is configured to flow into the flow passage via the flow passage inlet, through the flow passage along the outer surface of the torque probe to cool the torque probe, and out of the flow passage via the flow passage outlet.

This steam turbine blade is provided with: a blade body (61) extending in a radial direction and having an airfoil profile in a cross section perpendicular to the radial direction; and a heater (H) including a heating wire disposed so as to extend along a trailing edge (Er) of the airfoil profile in the blade body (61). This configuration makes it possible to further mitigate an efficiency drop due to moisture attached to the surface of the steam turbine blade (60).

A powerplant is provided that includes a pre-burner, a combustor, a power turbine, a mechanical load and a propellant system. The combustor is fluidly coupled with and downstream of the pre-burner. The power turbine is fluidly coupled with and downstream of the combustor. The mechanical load is rotatably driven by the power turbine. The propellant system is configured to direct fluid oxygen and fluid hydrogen to the pre-burner to provide an oxygen rich fuel mixture for combustion within the pre-burner. The propellant system is also configured to direct the fluid hydrogen to the combustor for combustion within the combustor with oxygen within combustion products received from the pre-burner.

A gas turbine engine comprises a fan drive turbine for driving a gear reduction. The gear reduction drives a fan rotor. A lubrication system supplies oil to the gear reduction. The lubrication system includes a lubricant pump supplying a mixed air and oil to a deaerator inlet. The deaerator includes a separator that for separating oil, and delivering separated air to an air outlet, and for delivering separated oil back into an oil tank. The separator includes a member having lubricant flow paths on both of two opposed sides. A method of designing a gas turbine engine is also disclosed.

A system for providing mobile electric power includes a first transport including an inlet plenum and a generator, a second transport including a gas turbine, and a turbine exhaust unit, and a third transport including a generator exhaust air handling system, a combustion air handling system, and a turbine enclosure air handling system. The first transport, the second transport, and the third transport are separate transports that are independently movable in a transportation mode. In an operation mode, the first transport and the second transport are connected to each other such that a first end side of the first transport faces and is connected to a first end side of the second transport, and the inlet plenum mounted on the first transport is connected to an intake of the gas turbine mounted on the second transport. In the operation mode, the third transport is positioned at a predetermined distance relative to the connected first and second transports such that a first longitudinal side of the third transport faces a first longitudinal side of the first transport and a first longitudinal side of the second transport.

The invention regards a turbine generator system that comprises a gas turbine engine and an electrical generator coupled to the gas turbine engine, wherein the gas turbine engine is located in a compartment having a compartment wall. A ventilation system is provided that comprises: at least one air inlet arranged in the compartment wall and configured to allow air to flow into the compartment; at least one air outlet arranged in the compartment wall and configured to allow air to flow out of the compartment; at least one electric cooling fan with an adjustable fan speed located in, upstream or downstream of the air inlet, the electric cooling fan adjusting by its fan speed the amount of air flowing into the compartment; and temperature sensing means sensing the temperature inside the compartment or at the air outlet. The ventilation system is configured such that the cooling fan adjusts its fan speed depending on the temperature sensed by the temperature sensing means.

A cooling system for a plurality of conductive cables in a gas turbine engine includes a cooling source and an electric motor disposed in a tail cone. The cooling source may comprise an electric fan or an oil pump. The cooling source may be configured for active cooling of the plurality of conductive cables. The electric fan may be in fluid communication with ambient air during operation of the gas turbine engine.

The invention relates to an aircraft turbine engine module (10), comprising a degassing tube (14) and an ejection cone (12). The tube and the cone comprise centring means engaging together. The invention also relates to a locating and adjusting tool for assembling said module.

A fuel delivery system for a gas turbine engine comprises a cryogenic fuel tank, a first fuel line for connection to the cryogenic fuel tank, a fuel pump connected to receive fuel via the first fuel line, a plurality of fuel lines connecting the fuel pump to a combustor of the gas turbine engine, a controller configured to operate the fuel delivery system, a purge gas tank connected to the first fuel line and configured to store a purge gas for purging the plurality of fuel lines and a fuel gas tank connected to the first fuel line and configured to store a fuel gas for flushing purge gas from the plurality of fuel lines.