A gas turbine engine for an aircraft includes a compressor, a combustion chamber, and a turbine having at least one stator, and at least one rotor. Each stator and rotor is formed by a plurality of blades, a fluid channel is formed between two consecutive blades, and each blade has two opposing surfaces. The compressor is in fluid communication with a first group of stator channels, and the combustion chamber is in fluid communication with a second group of stator channels, such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls define a duct for the passage of the heated fluid through the rotor blades, and the outer wall is also arranged for directing the compressed air towards the combustion chamber.

In an adjusting device for an exhaust gas turbocharger with a first adjusting member and a second adjusting member for operating a valve element for varying the flow cross-section of a bypass duct of a flow-through exhaust gas guide portion of a turbine of an exhaust gas turbocharger, the first adjusting member and the second adjusting member are connected so as to be pivotable relative to one another by a pin-shaped connecting element with a locking element establishing a pivot joint of the first adjusting member and the second adjusting member with a predetermined axial engagement force.

A steam valve control device of this embodiment controls a steam valve. The steam valve has: an upper cover in whose through hole a bush is installed; and a valve rod which is installed so as to penetrate through the through hole of the upper cover via the bush. The valve rod has a contact surface which is formed so as to come into mechanical contact with the bush when the steam valve is opened to a maximum opening degree. The steam valve control device has a control part. When a governor free operation is performed, the control part controls the steam valve by setting a limited opening degree limited to be smaller than the maximum opening degree as an upper limit. When a load limiter operation is performed, the control part controls the steam valve by setting the maximum opening degree as the upper limit.

A steam valve control device of this embodiment controls a steam valve. The steam valve has: an upper cover in whose through hole a bush is installed; and a valve rod which is installed so as to penetrate through the through hole of the upper cover via the bush. The valve rod has a contact surface which is formed so as to come into mechanical contact with the bush when the steam valve is opened to a maximum opening degree. The steam valve control device has a control part. When a governor free operation is performed, the control part controls the steam valve by setting a limited opening degree limited to be smaller than the maximum opening degree as an upper limit. When a load limiter operation is performed, the control part controls the steam valve by setting the maximum opening degree as the upper limit.

An actuator includes a housing that defines a first inlet to receive a fluid, a second inlet to receive the fluid and a chamber. The actuator includes an actuator rod movably coupled to the housing. The actuator rod includes a head. A first face of the head is responsive to the fluid from the first inlet, and a second face of the head is responsive to the fluid from the second inlet to move the actuator rod. The head defines at least one cross-bore. The actuator includes at least one plug coupled to the cross-bore to inhibit a flow of the fluid through the cross-bore in a first state such that the plug fluidly isolates the fluid from the first inlet from the fluid from the second inlet. The plug is to enable the flow of the fluid through the at least one plug in a second state.

A bleed valve assembly includes a flow duct with an inlet and an outlet disposed downstream from the inlet. The outlet is smaller in cross-sectional area than a region of the flow duct disposed between the inlet and the outlet. A piston housing is disposed inside the flow duct between the inlet and the outlet so as to form an annular flow passage between the flow duct and the piston housing. The piston housing is axially aligned with a center axis of the flow duct. At least one rib extends between the flow duct and the piston housing. A sleeve piston is disposed inside the piston housing and is configured to extend downstream of the piston housing in a closed position. The sleeve piston comprises an outer wall that is at least the same in cross-sectional area as the outlet of the flow duct.

An actuator system mounted to a gas turbine engine that communicates mechanical power for positioning variable guide vanes within the gas turbine engine. The actuator system includes a torque box having components for communicating mechanical power to the variable guide vanes for positioning the vanes and an actuator mechanically coupled to provide mechanical power to the components of the torque box used to communicate the provided mechanical power to the inlet guide vanes. The actuator is mounted to the torque box via an elongate fastener extending in one direction and another elongate fastener extending in another direction.

A method and system for a turbofan gas turbine engine system is provided. The gas turbine engine system includes a variable pitch fan (VPF) assembly coupled to a first rotatable shaft and a low pressure compressor LPC coupled to a second rotatable shaft. The LPC including a plurality of variable pitch stator vanes interdigitated with rows of blades of a rotor of the LPC. The gas turbine engine system also includes a speed reduction device coupled to said first rotatable shaft and said second rotatable shaft. The gas turbine engine system further includes a modulating pressure relief valve positioned between an outlet of said LPC and a bypass duct and a controller configured to schedule a position of said plurality of variable pitch stator vanes and said modulating pressure relief valve in response to an operational state of said turbofan gas turbine engine system and a temperature associated with said LPC.

An actuator system including a harmonic drive operable to drive a variable vane system of a gas turbine engine.

A turbocharger assembly may include a turbine wheel. A turbine housing may surround at least part of the turbine wheel. A wastegate port may be defined by the turbine housing and may provide a bypass around the turbine wheel. A valve plate may be movable between a first position closing the wastegate port and a number of additional positions opening the wastegate port. The valve plate may have a face that faces the wastegate port. A shaft may be connected to the valve plate and may rotate about an axis at a pivot point. The pivot point may be located on an opposite side of a line from the valve plate, wherein the line may extend from the face and in a plane within which the face exists when the wastegate port is closed by the valve plate.