A steam turbine includes an inner casing which has an inner casing body in which a first main flow path to which steam is to be supplied from an inner introduction port is defined, an outer casing which has an outer casing body which defines a second main flow path between the inner casing body and the outer casing body and an upper discharge port and a lower discharge port which are in the outer casing body and through which exhaust steam is to be discharged, an upper valve and a lower valve configured to adjust a flow rate of the exhaust steam which has been discharged, and a control unit which can independently control the upper valve and the lower valve.

A system and method for measuring average temperature of gas in an axial cross-section of a gas turbine engine gas path, involving diverting gas samples from different positions in the axial cross-section to a gas mixing chamber and measuring a temperature of the resulting mixed gas.

A system may comprise a sensor configured to measure a characteristic of an engine component. A valve assembly may have an airflow outlet in fluid communication with the engine component. The valve assembly may include a first valve. A first valve control device may be coupled to the first valve and configured to control the first valve based on a measurement by the sensor. A second valve may be in fluidic series with the first valve. A second valve control device may be coupled to the second valve and configured to control the second valve based on the measurement by the sensor.

A lever assembly forming part of a vane actuating mechanism and serving to connect a stator vane of a turbomachine to an actuating ring of an actuator is provided. The lever assembly is adapted such that an actuating lever of the lever assembly is moved in a first mounting direction transversely to a vane stem of the stator vane extending radially relative to a longitudinal machine axis of the turbomachine and is thereby positioned laterally against the vane stem, and that the actuating lever is radially form-fittingly locked to the vane stem by a locking piece in a second mounting direction. An assembly method and a turbomachine is also provided.

A lever assembly forming part of a vane actuating mechanism and serving to connect a stator vane of a turbomachine to an actuating ring of an actuator is provided. The lever assembly is adapted such that an actuating lever of the lever assembly is moved in a first mounting direction transversely to a vane stem of the stator vane extending radially relative to a longitudinal machine axis of the turbomachine and is thereby positioned laterally against the vane stem, and that the actuating lever is radially form-fittingly locked to the vane stem by a locking piece in a second mounting direction. An assembly method and a turbomachine is also provided.

A guide system for repairing turbomachinery includes a housing; a guide tube have a hollow interior for accepting a working tool module; an axial motor for moving the guide tube axially with respect to the housing; a rotational motor for rotating the guide tube with respect to the housing; and an attachment for securing the housing with respect to a turbomachinery casing. A repair kit and method are also provided.

A clearance measurement device is for measuring a clearance between an inner peripheral surface of a cylindrical casing and an outer peripheral surface of a rotating member configured to rotate in the casing. The clearance measurement device includes a marker provided to the outer peripheral surface; an optical sensor attached to the casing, and configured to emit light toward the outer peripheral surface, receive light reflected from the rotating member, and detect the marker based on a change in amount of the received reflected light; and a measurement controller configured to perform signal processing on signals from the sensor. The sensor includes light reception fibers disposed such that optical axes intersect and having a measurement region on the outer peripheral surface, and planar light sources provided in a row along a rotating direction and each configured to emit light in a manner overlapping with the measurement region.

An auxiliary power unit for an aircraft, having a compressor, an intercooler including first conduit(s) having an inlet in fluid communication with the compressor outlet and second conduit(s) configured for circulation of a coolant therethrough, an engine core having an inlet in fluid communication with an outlet of the first conduit(s), and a bleed conduit in fluid communication with the outlet of the first conduit(s) through a bleed air valve. The auxiliary power unit may include a generator in driving engagement with the shaft of the engine core to provide electrical power for the aircraft. A method of providing compressed air and electrical power to an aircraft is also discussed.

Methods and systems for controlling a pneumatic starter air valve of a gas turbine engine are described herein. The starter air valve is controlled in a first mode of operation by actuating a first solenoid of the starter air valve with a steady-state input signal. Passage of the steady-state input signal to a second solenoid of the starter air valve is allowed, to actuate the second solenoid and enable pressure regulation of the starter air valve. The starter air valve is controlled in a second mode of operation by actuating the first solenoid with a pulse-width modulation input signal. Passage of the pulse-width modulation input signal to the second solenoid is prevented, to disable the pressure regulation in the second mode of operation.

A compressor case for a gas turbine engine includes an annular body that extends circumferentially around a center axis and extends axially along the center axis. A first bleed manifold is formed on an outer surface of the annular body and encloses a first plenum. A second bleed manifold is formed on the outer surface of the annular body and is axially aft of the first bleed manifold. The second bleed manifold encloses a second plenum. A bleed inlet extends through the annular body and into the first bleed manifold. Cooling passages are formed in the annular body, and each of the cooling passages extends from the first plenum to the second plenum and fluidically connects the first plenum to the second plenum.