Abstract: A device for fastening a fluid duct such as a fuel duct in an orifice of a turbojet casing, the device comprising a ring screwed into the orifice of the casing and having an annular rim coming to bear against a washer at the end of the duct, and a nut screwed onto the end of the duct so as to clamp the annular rim of the ring against the washer of the duct in order to fasten the duct to the casing.

Abstract: A turbojet thrust reverser includes two doors each displaceable between an open position and a closed position of the reverser by at least one respective control actuator. Two electric motors drive the control actuators for the doors; each motor being controlled by an electronic control unit connected to a full authority digital engine control. Two servo-control devices control the displacement of the doors as a function of determined position references. The servo-control devices enable the doors to be displaced synchronously as a function of any variation in the forces exerted on the reverser and as a function of any force difference between the two doors.

Abstract: An adjustment method and system for an auxiliary power unit (APU) allows the APU speed to vary based on the inlet air temperature to the APU compressor. The APU is controlled by a control law that allows the APU speed to float within a selected range based on speed and electric power generators phase matching criteria that provides smooth power transfer between the APU and a main engine generator. The specific APU mechanical speed for a given temperature may be determined from a compressor map that identifies the optimum combination of pressure ratio, flow rate and efficiency for a given inlet temperature, and avoids running the APU near mechanical resonant vibration conditions.

Abstract: A gas turbine system comprises a compressor for compressing air, a combustor for burning the air compressed by the compressor and fuel, a turbine driven by combustion gases produced from the combustor, and a spraying apparatus for adding water to working air at least upstream or in an intermediate stage of the compressor. A rotationally symmetric groove or projection is formed in an inner wall surface defining a channel through which the working air added with the water flows, or in a channel-defining surface of a rotor or a casing of the gas turbine. A larger amount of water can be supplied to the compressor while improving the reliability of the gas turbine.

Abstract: A method of operating a gas turbine power plant and gas turbine power plant are disclosed wherein hydrogen for the combusting process is produced by feeding natural gas mixed with steam through a membrane/partial oxidation reactor and converting the natural gas at least to H2 and CO. Thereby oxygen is transferred from the compressed air through the membrane of the membrane/partial oxidation reactor and the oxygen is used for the partial oxidation process of the natural gas. The process is followed by converting the syngas in a CO shift reactor and a CO shift reactor to a CO2 removal equipment to mainly hydrogen.

Abstract: A premixing nozzle includes swirler blades for agitating combustion air inside a nozzle body. Each one end of the swirler blades is fitted to the nozzle body, and the other end is connected to a hub, respectively. The tip portion of a fuel nozzle shaft is conical, and a part of the tip portion is arranged inside the hub. A combustion gas flows into the hub from a space between the tip portion of the fuel nozzle shaft and the upstream end of the hub, passes through between the tip portion and the inner peripheral surface of the hub, and flows toward the downstream of the hub.

Abstract: The fuel injector has a first means defining a number of flowpaths each having an inlet for receiving air and an outlet for discharging a fuel/air mixture. One or more arrays of vanes are each positioned to impart swirl to an associated one or more of the flowpaths. Second means are provided for introducing the fuel to the air.

Abstract: Methods and systems for processing uncalcined coke are provided. The methods and systems provide for combusting effluent gas from a refinery unit and a stream of uncalcined coke. The refinery unit effluent gas may be the offgas from a rotary kiln calciner. The refinery unit effluent gas and the uncalcined coke stream are combusted in an integrated gas/solids incinerator. Heat released during the combustion of these streams may be used to generate steam or electricity. The methods and systems disclosed provide low cost energy production at calciner effluent gas incinerator locations where uncalcined coke is available.

Abstract: A combustion chamber/supersonic nozzle assembly is cooled by an array of coolant channels in the wall of the assembly with coolant being fed to the assembly at the throat plane between the subsonic (convergent) and supersonic (divergent) sections. A minor portion of the coolant entering at the throat plane is directed to coolant channels in the supersonic section wall, while the remainder is directed to a complex arrangement of channels in the subsonic section wall. The latter arrangement includes an outer layer of wide axially oriented channels for delivery of coolant to, and removal from, an inner layer of smaller, circumferentially oriented channels that are adjacent to the hot gas and carry the bulk of the coolant load. The path of coolant travel through each inner channel is relatively short, lessening the pressure drop through those channels relative to coolant channel arrangements of the prior art.

Abstract: An apparatus is provided that includes a body having a first wall and a second wall, at least one appending structure extending from an end of the body and at least one actuator positioned between the first and second walls. The actuator includes first end coupled to a portion of the body and a second end coupled to a portion of the appending structure. At least one shape memory alloy (SMA) wire is connected to and extends between the first and second ends of the actuator. The SMA wire is adapted to controllably constrict when activated by heat, whereby the constriction causes the appending structure to move from a first position to a second position.

Abstract: The turbomachine of the invention extends longitudinally along an axis, and includes a rotor attached to drive shaft, arranged to rotate around an axis, supported by at least a first bearing, mounted on the fixed structure of the turbomachine by a bearing support element. The turbomachine is characterised by the fact that it includes a stop ring, mounted on the fixed structure of the turbomachine, to cooperate with the support element of the first bearing and, in the event of displacement of the rotor in relation to the fixed structure, to perform a function of axial retention of the rotor in an even manner, with no angle effect between the axis of the turbomachine and the axis of the drive shaft.

Abstract: Conventional auxiliary power units (APUs) may experience over-temperature shutdowns when attempting to start them at high altitudes. Further, such conventional APUs may also experience overspeed conditions when a generator load is removed during on-speed operations. A fuel control logic that controls the fuel flow cutback below the minimum blowout fuel schedule is provided. A temperature trim loop measures engine temperature to determine the onset of a possible over-temperature condition. The fuel flow may then be trimmed accordingly to correct this over-temperature onset. Further, when the onset of an overspeed condition is detected, such as when a generator load is removed, the fuel flow may be trimmed accordingly to correct this overspeed onset. The fuel control logic allows the control to find the individual minimum fuel flow for each fuel control without risking blowout of the APU itself.

Abstract: A fuel injector for a gas turbine combustor is disclosed which includes a feed arm having a flange for mounting the injector within the combustor and a fuel nozzle depending from the feed arm for injecting fuel into the combustor for combustion. An optical sensor array is located within the fuel nozzle for observing combustion conditions within the combustor.

Abstract: A method for assembling a gas turbine engine includes providing a first fan assembly including a plurality of rotor blades that are configured to rotate in a first rotational direction at a first rotational speed, rotatably coupling a second fan assembly axially aft of the first fan assembly, wherein the second fan assembly includes a plurality of rotor blades that are configured to rotate in a second rotational direction, and coupling a gearbox to the second fan assembly that is configured to rotate the second fan assembly at a second rotational speed that is different than the first rotational speed.

Abstract: A fuel system for a propulsion system includes a fuel deoxygenating device and a catalytic module containing catalytic materials. The fuel deoxygenating device removes dissolved oxygen from the fuel to prevent formation of insoluble materials that can potentially foul the catalyst and block desirable catalytic reactions that increase the usable cooling capacity of an endothermic fuel.

Abstract: A system for providing an oxidizer and a fuel to a rocket engine is provided. The system includes a fuel supply system. The fuel supply system includes a fuel pump that pumps fuel to the rocket engine. The system includes a coolant supply system that supplies a coolant to the rocket engine, and a power plant that powers at least one of the fuel supply system and the coolant supply system. The power plant is powered by energy received from the coolant system.

Abstract: A gas turbine engine combustor swirler has vanes with a spanwise chord length distribution providing a desired swirl distribution.

Abstract: An aircraft structure includes a duct having an inlet for fluid flow into the duct and a first outlet for fluid flow out of the duct. The duct is configured to guide fluid flow out of the duct through the first outlet in an at least partially reversed direction relative to fluid flow into the duct to thereby reverse thrust.

Abstract: As shown schematically in FIG. 1, hot gases, containing molecular oxygen, from generator elements, (14) and (19), pass through a bed of coal chunks in an ODD reactor chamber (2). The molecular oxygen content of these hot gases is less than stoichiometric, relative to the coal volatile matter content, so that partial oxidation of only the volatile matter occurs within the ODD reactor chamber, (2), during devolatilization therein. Two products are thusly created, a partially oxidized, and hence cleaner burning, volatile matter fuel gas, and a solid devolatilized coke. The hot coke is transferred, by overfeed, into a coke reaction chamber, (7), where counterflowing primary air, via air meter, (12), gasifies the coke into carbon monoxide with some carbon dioxide. Finally, the carbon monoxide and the partially oxidized volatile matter, are admixed with overfire air, and burned fully to carbon dioxide in overfire burner chambers, (23), (26).

Abstract: A combustion chamber according to the invention, in particular for a gas turbine, includes at least one combustion chamber wall through which cooling fluid flows and at least one resonator device. The combustion chamber according to the invention is distinguished in that the resonator device is integrated into the combustion chamber wall in such a way that it has the cooling fluid flow passing there through.