A control ring for controlling discharge gates for an aircraft turbine engine extends around a casing of the turbine engine and includes a connector for connecting to the gates. The control ring includes metal sectors and composite material sectors. The metal sectors may be connected to one another by the composite material sectors and the connector may be carried by the metal sectors.

A steam turbine plant is provided with: a boiler; a fuel valve; a low-temperature steam generation source; a steam turbine; a main steam line that guides steam generated in the boiler to the steam turbine; a main steam adjustment valve that is provided to the main steam line; a low-temperature steam line that guides low-temperature steam from the low-temperature generation source to a position closer to the steam turbine-side than the main steam adjustment valve in the main steam line; a low-temperature steam valve provided to the low-temperature steam line; and a control device. During a stopping process of the steam turbine plant, the control device sends a command to close the fuel valve, and then sends a command to open the low-temperature steam valve.

A compressor bleed apparatus includes: a compressor comprising one or more rotors mounted for rotation about a central axis and enclosed in a compressor casing; a bleed slot passing through the compressor casing; an outer wall defining, in cooperation with the compressor casing, a plenum surrounding the compressor casing; at least one offtake pipe communicating with the plenum; and wherein at least one of the plenum and the bleed slot has a non-axisymmetric structure.

A turbocharger includes a turbine housing including an interior surface defining a turbine housing interior. The interior surface extends between a turbine housing inlet and a turbine housing outlet. The turbine housing also includes a wastegate duct disposed downstream of the turbine housing inlet and defining a wastegate channel. The turbocharger also includes a valve seat disposed about the wastegate channel, with the valve seat having a valve seat plane extending along the valve seat. The turbocharger further includes a wastegate assembly including a valve element engageable with the valve seat. The wastegate channel extends along a channel axis, and the channel axis is obliquely oriented with respect to the valve seat plane such that the wastegate channel and the valve element are configured to direct exhaust gas to a catalytic converter.

The present invention relates to an ultra-low emission stored exhaust gas-assisted internal combustion powerplant. The powerplant comprises a variable torque drive turbine connected to a piston compressor through a gearbox. The gearbox comprises a planetary or epicyclic gear to selectively direct power from the drive turbine to the compressor and at least one output shaft. The compressed air is mixed with fuel in a staged combustor, the hot exhaust gasses are used to drive the variable torque drive turbine or cooled and stored in a exhaust gasses storage system.

A non-return valve with twin plugs is connected to a fluid reservoir and equipment that can receive a small overflow quantity essentially in the gaseous state from the reservoir. This occurs when the primary valve is open. In the case of a larger overflow essentially in the liquid state, the openings are switched over to evacuate the overflow to another outlet branch of the non-return valve, without it being transferred to the equipment. The invention is useful in an oil lubrication circuit, in which a hypothetical fuel leak into the oil could cause the oil reservoir to overflow into the non-return valve and in which a significant flow of liquid to the equipment must be avoided; oil outlet through the other branch of the outlet can remain in a reservoir provided with a drain system.

Methods and systems are provided for a turbocharger. In one example, a method may include bypassing exhaust gases flowing to the turbocharger in response to a catalyst temperature being less than a threshold temperature. The bypassing includes opening a bypass valve and adjusting a position of one or more turbine nozzle vanes.

A method for forming a composite part of a gas turbine engine. The method includes assembling the composite part of a first composite material and a second composite material. The second composite material defines an outer surface of the composite part, and is selected to be curable at a cure temperature generated by heat from operation of the engine. The first composite material is selected to have an operating temperature limit less than the cure temperature. The method includes placing the composite part within the engine so that, in use, the second composite material is cured by exposure to the heat generated from operation of the engine. The second composite material thermally shields the first composite material from the heat generated from operation of the engine. The method includes operating the engine to cure the second composite material.

A turbine (3) includes: a turbine impeller chamber (43) having a tubular outflow portion (432), from which an exhaust gas flows out in an outflow direction (F) substantially parallel to an axis (C) of a turbine impeller (5); a bypass flow passage (491) bypassing the inside of the turbine impeller chamber; an outer duct (47) having an inner peripheral surface (475) that expands in diameter in the outflow direction from the outflow portion; and an inner duct (48) that extends in the outflow direction from the outflow portion. A diffuser flow passage (483) that expands in diameter in the outflow direction is disposed in the inner duct at least in a portion between the outflow portion and a distal end portion (481a). An outlet (492) of the bypass flow passage and a waste gate valve (493) that opens and closes the outlet are disposed on the inner peripheral surface.

A linear motion mechanism, including a drive portion, a screw shaft which is rotationally driven about an axis by the drive portion and in which a first spiral screw groove is formed on an outer peripheral surface, a nut in which a second spiral screw groove facing the first screw groove is formed on an inner peripheral surface and which moves forward or backward relative to the screw shaft in an axial direction, in which an axis of the screw shaft extends, according to a rotation of the screw shaft, a plurality of load balls which are disposed in a transfer path formed by the first screw groove and the second screw groove and advance while rolling on the transfer path, a plurality of retainer frames which are disposed between the plurality of load balls and advances on the transfer path along with the load balls.