Abstract: A displacement machine for compressible media includes at least two shafts. Each of the shafts has a rotor which is configured as a profiled body with the profiles of the rotors engaging one another in the manner of gearwheels during rotation and running without contact relative to one another. Each of the shafts is driven by an electric motor. The angular positions of each shaft is determined by an associated synchro resolver. Each of the synchro resolvers has a rotor and emits an electronic signal to the electric motor of the shaft such that the motors are electronically synchronized. Each of the shafts further has a gearwheel, with the gearwheels engaging one another and having an angular clearance which is smaller than that of the profiled bodies. At least one of the gearwheels is directly connected to the rotor of the synchro resolver associated with its shaft and both gearwheels together are releasably connected as a unit to the shaft.

Abstract: A steam-cooled second-stage nozzle segment has an outer band and an outer cover defining a plenum therebetween for receiving cooling steam for flow through the nozzles to the inner band and cover therefor and return flow through the nozzles. To measure the temperature of the buckets of the stage forwardly of the nozzle stage, a pyrometer boss is electron beam-welded in an opening through the outer band and TIG-welded to the outer cover plate. By machining a hole through the boss and seating a linearly extending tube in the boss, a line of sight between a pyrometer mounted on the turbine frame and the buckets is provided whereby the temperature of the buckets can be ascertained. The welding of the boss to the outer band and outer cover enables steam flow through the plenum without leakage, while providing a line of sight through the outer cover and outer band to measure bucket temperature.

Abstract: A gas turbine plant comprises an air compressor, a gas turbine combustor and a gas turbine, which are operatively connected in series. In the gas turbine plant, an air compressor shaft is accommodated in the air compressor and composed of discs piled up along an axial direction of the air compressor shaft, a gas turbine shaft is accommodated in the gas turbine and composed of discs piled up along an axial direction of the gas turbine shaft, and an intermediate shaft is interposed between the air compressor shaft and the gas turbine shaft. At least one of the discs of the air compressor shaft and the discs of the gas turbine shaft are provided with bulged portions each having approximately a hanging bell shape or trapezoidal shape.

Abstract: An injector for injecting a first liquid propellant and a second liquid propellant into a combustion chamber of a rocket engine. The injector includes a first injection element for injecting a first portion of the first liquid propellant into the combustion chamber such that the first portion of the first liquid propellant enters the combustion chamber in a first sheet or stream. A second injection element is spaced radially outward from the first injection element and injects a second portion of the first liquid propellant into the combustion chamber such that the second portion of the first liquid propellant enters the combustion chamber in a second stream. The first and second streams collide, causing the first and second portions of the first liquid propellant to at least partially atomize.

Abstract: In a process and apparatus for two-stage supercharging of process air for a fuel cell, in one of the two charging stages, supercharging taking place by means of a displacement machine. In the other charging stage, supercharging is performed by means of a combined expansion and compression machine. Energy is recovered from the exhaust gas of a fuel cell by means of the combined expansion and compression machine.

Abstract: The invention relates to the field of automatic equipment and, in particular, to devices for chemical ignition of liquid rocket engine propellant components. The ampoule comprises a body, diaphragm units mounted at the body inlet and outlet, each of which is made as a piston made as a single part with a diaphragm. The peripheral part of the diaphragm is fixed in an air-tight manner to the body under a guide element in which the body is mounted. The piston has a stem extending into a guide bush. Furthermore, a device for filling the ampoule with fuel is located in a partition of the body inside the ampoule. A guaranteed cutting of the diaphragm along the entire perimeter and reproduction of hydraulic characteristics for the flow part of the ampoule are achieved in this ampoule design.

Abstract: A heat exchanger having a cold side flow path adjacent to and thermally coupled with a hot side flow path or other heat source, such that heat is transferred to the cold side flow path; and means for introducing evaporative fluid into the cold side flow path.

Abstract: An apparatus for reducing noise reduction produced by a super sonic jet, comprises a cavity tone generator provided near an exit of a supersonic jet nozzle. The cavity tone generator is a cavity formed in an inner wall of the nozzle exit, and the cavity having a lateral cross-sectional shape similar to a lateral cross-sectional shape of the inner wall of the nozzle exit. More preferably, the cavity and the nozzle exit are formed to have a rectangular lateral cross-sectional shape.

Abstract: A turbine and gas turbine comprise an annular stator and a turbine rotor rotatably disposed in the stator. The stator includes a tangential inlet to introduce a jet stream of motive gases in a tangential direction, an outlet to exhaust expanded gases, and a plurality of circumferentially spaced and radially extending flow deflectors. The turbine rotor includes an annular jet stream path communicating with the inlet and the outlet, and a plurality of turbine blades circumferentially spaced in close proximity with the annular jet stream path, which accommodates the flow detectors to deflect the jet stream toward the turbine blades.

Abstract: An integrated exhaust nozzle and thrust reverser for a turbojet engine is provided. The exhaust nozzle comprises an exhaust duct situated within a fairing (9), a set of hot flaps (14) at a downstream end of the duct, a set of cold flaps (16) at a downsteam end of the fairing (9), and a thrust reverser (30). The thrust reverser comprises two eyelids (31, 32) which are movable between a thrust reversal position wherein they project into the duct and a forward-thrust position. In a takeoff mode, the eyelids (32, 33) are moved away from each other by one or more actuators (50) acting on arms (33, 34) pivotably connected to the eyelids (31, 32). Movement of the eyelids (31, 32) from the reverse-thrust position to the forward-thrust position, or vice-versa, is implemented by control actuators (35, 36).

Abstract: A hand pump includes an automatic inflation device and a manual inflation device. The automatic inflation device includes a gas container containing pressurized gas for providing automatic and rapid inflation. When the automatic inflation device malfunctions or the gas container runs out of gas, the manual inflation device can be manually operated for inflation.

Abstract: A deswirler system for a centrifugal compressor of a gas turbine engine that improves overall engine performance as a result of exhibiting significantly reduced friction losses. The deswirler system generally entails an annular-shaped manifold having an inlet configured to receive radially-outward flowing gas from a diffuser of the compressor, an outlet configured to discharge the gas in an axial downstream direction, and an arcuate passage therebetween. The deswirler system further includes a plurality of deswirler vanes directly within the arcuate passage and closely coupled to the diffuser.

Abstract: The present invention relates to a diaphragm pump comprising an entirely pneumatic control mechanism, which has a double acting jack (18), to which is connected a diaphragm (19), delivery being obtained by the pressurizing of several chambers (15, 16, 17), admission being obtained by the preparation of a first chamber (15), the other chambers (16, 17) being under atmospheric pressure.

Abstract: A combustor liner for use in a gas turbine engine includes a first annular panel section having a first cooling nugget formed at one end thereof and a second annular panel section having a second cooling nugget formed at one end thereof. A first row of cooling holes is formed in the first cooling nugget, and a second row of cooling holes is formed in the second cooling nugget. The second row of cooling holes is arranged in a preferential cooling pattern including a plurality of arrays, each array has a first set of cooling holes having a first diameter and a second set of cooling holes having a second diameter that is smaller than the first diameter. The cooling hole arrays are preferably arranged to minimize tooling set-ups and thereby reduce cost. At least one igniter tower is formed in the first annular panel section and is circumferentially aligned with one of the second sets of cooling holes.

Abstract: A turbofan aircraft engine has a core engine, which is arranged in a gondola, and a fan which delivers a cold air current through a bypass flow duct to a mixer within which a low-pressure turbine cone is provided and on which the hot-gas current emerging from the low-pressure turbine of the core engine is mixed with the cold-air current. A portion of the cold-air current is branched off by an ejector effect and, as a cooling air current for the low pressure turbine housing, arrives in a ring gap between the housing and a covering surrounding this housing. A portion of this cooling air current is guided by hollow outlet guide blades of a follower guide wheel of the low-pressure turbine for sealing off the rearmost ring gap between the rotor and the stator of the low-pressure turbine, while the largest portion of the cooling air current reaches the ejector.

Abstract: A scroll-type variable-capacity compressor is disclosed in which a single spool is moved to open or close bypass ports and thereby change the capacity of compression chambers. Especially, the capacity can be controlled in satisfactory manner by opening the bypass ports to a specific position. Specifically, a first bypass port is arranged in the neighborhood of the contact point between the inner surface of the spiral wall of a fixed scroll and the outer surface of the spiral wall of a movable scroll making up one of the compression chambers with the capacity thereof reduced to a predetermined level. A second bypass port is arranged at a position on the side beyond a discharge port from the first bypass port but where the discharge port is not located on the line connecting the particular position and the first bypass port.

Abstract: A gas turbine combined plant, a method of operating the same, and a steam-cooling system for a gas turbine hot section are provided, whereby the generation of thermal stress can be utmost reduced. A gas turbine hot section steam cooling system (30) is designed to cool a hot section (8) of a gas turbine unit (1) by the steam of an exhaust heat recovery boiler (2) and to supply the steam after cooling into a steam turbine (23). The system (30) comprises: a temperature detectors (15, 16) for detecting the outlet temperature of the steam of the gas turbine hot section and the outlet temperature of the steam of the exhaust heat recovery boiler, respectively, at the start-up time of the gas turbine; and a shielding valve (20) disposed to a pipe (12a) supplying the steam after cooling the gas turbine hot section to the steam turbine for shielding the steam after cooling in the case where there is a substantial difference between the both temperature levels.

Abstract: A dual pump for independently pumping two fluids includes a pump body having a first concave depression on a first side of the body. A first inlet port and a first outlet port are contained within the body, in fluid communication with the first depression. A second concave depression is on a second side of the body opposite the first depression. A second inlet port and a second outlet port are contained within the body in fluid communication with the second depression. A first diaphragm is coupled to the first side of the body and encloses the first depression to form a first inner chamber. A second diaphragm is coupled to the second side of the body and encloses the second depression to form a second inner chamber. A shell encloses the body on its first and second sides. The shell defines a first outer chamber with the first diaphragm in pressure communication with the first inner chamber.

Abstract: A turbojet-engine thrust-reverser comprising pivoting hollow doors (3) which in the forward-thrust mode are integrated into the external cowling of the turbojet-engine and which in the thrust-reversal mode constitute scoop-type flow-deflecting baffles. A displaceable external cowling panel (20) covers both the fore frame (8) of the stationary structure and the cross-section of the flow exhaust of the door (3) when in the forward-thrust mode. The external cowling panel (20) is pivotable on a panel pivot (24) situated downstream of the pivot (9) of the door (3) and its upstream edge moves radially outward to simultaneously clear a space above the fore frame (8) and the exhaust cross-section for the deflected flow.