A hollow turbine airfoil or a hollow turbine casting including a cooling passage partition. The cooling passage partition is formed from a single crystal grain structure nickel based super alloy, a cobalt based super alloy, a nickel-aluminum based alloy, or a coated refractory metal.

A hollow turbine airfoil or a hollow turbine casting including a cooling passage partition. The cooling passage partition is formed from a single crystal grain structure nickel based super alloy, a cobalt based super alloy, a nickel-aluminum based alloy, or a coated refractory metal.

A rotor disk assembly for a gas turbine maintains a sealing capability even though adjacent labyrinth arms are dislocated from each other due to torsion or similar relative movement by thermal expansion or by rotation of the rotor disks of the gas turbine. The rotor disk assembly includes a plurality of rotor disks axially assembled to each other, the plurality of rotor disks including adjacent rotor disks coupled to each other by Hirth parts. Each rotor disk includes two labyrinth arms that extend axially and bilaterally and are located on the rotor disk more radially outward than the Hirth parts, and a first labyrinth arm of the two labyrinth arms having an end surface in which a receiving groove for receiving a seal ring is formed.

A system includes a controller configured to monitor a fuel system supplying fuel to a gas turbine engine. The system also includes an electric propulsion system controlled by the controller. The electric propulsion system is configured as a variable load, which is supplied rotational energy by the engine. The controller is configured to dynamically control a magnitude of the variable load to adjust rotational speed of the gas turbine engine during a fixed level of fuel supply to the gas turbine engine. The electric propulsion system may include an electric generator and a plurality of propulsor motor(s) rotating a propulsor to provide thrust and/or lift to a vehicle such as an aircraft. The electric generator may be rotationally driven with the gas turbine engine to output electric power. The electric power is supplied to the propulsor motor(s) to rotate the propulsor to provide thrust and/or lift of the vehicle.

A nozzle segment for a gas turbine engine comprises an outer band having a cooling air inlet, an inner band having a first cooling air outlet, and a nozzle airfoil comprising a cooling flow passage arranged to receive the cooling air as a cooling air stream. A first channel and a second channel are arranged within the cooling flow passage. A deflector is arranged to divide the cooling air stream into a first cooling air stream in the first channel and a second cooling air stream in the second channel, respectively. The deflector deflects the first cooling air stream obliquely to a suction sidewall in the first channel, wherein the first channel is configured to transport the first cooling air stream along the first channel in a swirly flow.

A tool for performing inspection and/or maintenance operations on an engine defines a longitudinal direction and a tangential direction. The tool includes a base extending along the longitudinal direction and including a body, a first extension member extending from the body in the tangential direction at a first location, and a second extension member extending from the body in the tangential direction at a second location. The second location is spaced from the first location along the longitudinal direction. The tool also includes a pivot member rotatably coupled to the base and moveable between an insertion position in which the pivot member is oriented generally along the longitudinal direction and a deployed position in which the pivot member is oriented away from the longitudinal direction.

The invention relates to a compressed-air energy storage and production method comprising the following steps: compression of the air by staged compressors, during which cooling of the air after at least one compression step is performed through exchange with a heat transfer fluid, storage of the compressed air and of the hot heat transfer fluid after exchange during compression, staged expansions of the air by power generation turbines, during which heating of the air is performed after at least one step of expansion by said hot heat transfer fluid from said storage. According to the invention, after heating the expanded air and prior to being recycled to the compression step, the heat transfer fluid is cooled by an additional energy recovery loop comprising a pump, an exchanger and a turbine, as well as an additional transfer fluid.

An air seal for a jet turbine engine with an upper stator, lower stator and finned turbine disk. The thermal expansion of the stators may be regulated by a control ring, which has a lower rate of thermal expansion that the stators, to prevent rubbing between the stator and fins.

A gas turbine engine includes a turbine blade rotating about an axis of rotation defining an axial direction. A blade outer air seal is positioned radially outward of a radially outer tip of the turbine blade. The blade outer air seal has a forward support and an aft support. The forward support is supported on a forward hook from a blade outer air seal support. The aft support is supported on an aft hook from the blade outer air seal support. The blade outer air seal has a central web extending between the forward support and the aft support and radially outwardly of the turbine blade radially outer tip. A radially outer chamber is defined radially outwardly of the central web, and axially intermediate the forward support and the aft support. The radially outer chamber is divided into at least two separate subchambers maintained at two different pressures. A forward subchamber is at a higher pressure than an aft subchamber. A seal separator separates the forward and aft subchambers.

A turbine blade includes: an airfoil body; a cooling passage extending along a blade height direction inside the airfoil body; and a plurality of turbulators disposed on an inner wall surface of the cooling passage and arranged along the cooling passage. The airfoil body has a first end portion and a second end portion which are opposite end portions in the blade height direction. A passage width of the cooling passage in a suction-pressure direction of the airfoil body at the second end portion is greater than a passage width of the cooling passage at the first end portion. A height of the plurality of turbulators increases from a first end portion side to a second end portion side in the blade height direction.