Abstract: A system for moving an auxiliary component of a gas turbine engine is disclosed. The system may have a mobile support platform configured to support the auxiliary component during operation of the gas turbine engine. The system may further have at least one guide assembly operably connected to the mobile support platform and configured to guide movement of the mobile support platform. The system may also have a drive assembly operably connected to the mobile support platform and configured to impart movement of the mobile support platform between an elevated position and a lowered position.

Abstract: A control system of a hydraulic type for a thrust reversal device with which a jet engine nacelle is equipped, and associated with a nozzle variation device, is provided by the present disclosure. The control system includes at least one additional control unit hydraulically connecting actuators together, wherein hydraulic supply lines from the control unit in a nozzle mode and from the control unit in a reverser mode are then able to communicate hydraulically with each other. A plurality of control valves are laid out so that when the unit for driving the actuators in a nozzle mode is active, a corresponding hydraulic signal controls the valves of the control unit in a position such that the hydraulic supply lines of the actuators from the driving unit according to a reverser mode are cut off.

Abstract: A device for injecting a mixture of air and fuel into a turbomachine combustion chamber includes a centering ring for centering an injector and a primary swirler situated downstream from the ring, the ring including axial air-passing orifices and the swirler including curved air-passing channels, a number of orifices in the ring being no greater than a number of channels in the swirler, and downstream outlets of the orifices in the ring being situated between the channels in the swirler.

Abstract: The present invention provides a gas turbine capable of reducing energy consumption while suppressing a so-called cat back phenomenon. The gas turbine includes a combustor-accommodating chamber casing for accommodating therein a combustor which burns fuel and air compressed by a compressor to generate combustion gas and which injects the combustion gas to a turbine. The gas turbine also includes a first air supply passage and a second air supply passage on an upper portion of the combustor-accommodating chamber casing in the vertical direction. The first air supply passage discharges air toward the compressor in the combustor-accommodating chamber casing. The second air supply passage discharges air in a direction different from that of the first air supply passage.

Abstract: A fluid delivery system in a gas turbine engine includes an electric motor, a first fluid pump system and a second fluid pump system. The electric motor operates at a variable speed. The first pump system includes a first pump driven by the motor to deliver a first fluid to the gas turbine engine. The second pump system includes a second pump driven by the motor to deliver a second fluid to the gas turbine engine, the second pump having a variable displacement.

Abstract: An apparatus for attenuating acoustic oscillations of a gas flow contained in part by a combustor wall of a gas turbine engine combustor, wherein the combustor includes at least one air/fuel mixer, includes at least one resonating tube with a closed end and an open end and a single cavity between the ends. The tube is located on the combustor wall downstream of the air/fuel mixer.

Abstract: A rotating device for producing pressure by expansion of a-pressurized process substance is provided. The rotating device includes a U-channel structure arranged to be rotatable around an axis of a shaft. The U-channel structure includes an expansion point arranged at a periphery of the rotating device, a sinking channel for delivery of the pressurized process substance to the expansion point, a rising channel for delivery of the expanded process substance from the expansion point to a regulating valve for a delivery of the expanded process substance under a higher pressure than that of the pressurized process substance through an outlet channel to an energy recovery device. The rotating device is connected to driving devices in order to rotate the U-channel structure around the axis of the shaft.

Abstract: A method and apparatus for a pump control system. One or more embodiments of the invention include a pump controller that can perform a self-calibration procedure, can provide precise motor speed control, can provide a limp mode before shutting down the motor when system parameters are exceeded and/or fault conditions occur, can detect fault conditions, and can store fault conditions for later retrieval.

Abstract: A combined cycle power plant system and methods of operation so as to minimize consumption of cooling water utilizes exhaust from a combustion turbine to generate steam for power generation in a steam turbine topping cycle. The exhaust steam from the steam turbine topping cycle is utilized to vaporize an organic working fluid in an organic working fluid bottoming cycle, where vaporized organic working fluid expanded across a turbine generates additional power. Exhaust gas from the organic working fluid bottoming cycle is condensed utilizing an air-cooled heat exchanger. Heat exchange bundles of the air-cooled heat exchanger are preferably arranged horizontally relative to the ground to maximize efficiency. Turbine inlet cooling is employed at the combustion turbine to recapture energy lost in the system. A thermal energy storage tank may be utilized in conjunction with the turbine inlet cooling to supply chilling water to the system.

Abstract: A method of assembling a gas turbine engine is provided. The method includes providing at least one heat exchanger assembly including a heat exchanger and a mixer extending downstream from the heat exchanger. The mixer includes a plurality of windows formed therein. The method also includes coupling the at least one heat exchanger assembly within a bypass duct of the engine such that the at least one heat exchanger assembly is coupled to at least one of an outer engine casing and an inner engine casing of the turbine engine.

Abstract: An accessory system for a gas turbine engine includes a main case which defines an accessory gearbox axis. A cover is removably mountable to the main case and a first gear set at least partially within the cover along a first accessory axis transverse to the accessory gearbox axis.

Abstract: A compressor shroud has a continuous slot defined in a gaspath side surface thereof for communicating through the body of the shroud. Spaced-apart structural bridges span a rear portion of the slot in the shroud to maintain structural rigidity of the shroud. The method of forming the continuous slot is also described.

Abstract: An accessory system for a gas turbine engine includes an accessory gearbox which defines an accessory gearbox axis. A crossover gear set generally along the accessory gearbox axis interconnects a first gear set and a second gear set.

Abstract: A system and method for pumping fluid using a pump cassette. The system includes a control assembly for operating the pump cassette. A force assembly having a movable member is capable of applying force to the pump cassette to press the pump cassette against the control assembly. The movable member may be an expandable member, such as a bladder.

Abstract: A method of managing transient events regularly seen during gas turbine operation that may cause undesirable operation and hardware damage. During certain transient operations, a lag may be seen between reference exhaust temperature and actual turbine exhaust temperature. This lag can result in an under-fired condition within the combustion system of variable magnitude and duration. Either fuel split schedules or a control algorithm can be positioned during these transients to prevent combustion dynamics or loss of flame. Combustion dynamics are known to cause damage that may require hardware replacement. Once the transient has completed, normal control operation is resumed.

Abstract: A turbofan engine includes a fan variable area nozzle axially movable relative to the fan nacelle to vary a fan nozzle exit area and adjust a pressure ratio of the fan bypass airflow during engine operation.

Abstract: A fuel injection system for an annular combustion chamber of a turbomachine including a support device for supporting and centering a fuel injector head; and a bowl arranged downstream from the support device and including at its downstream end an annular collar that extends radially outwards and that is cooled by air impacting against its upstream radial surface is disclosed. The upstream radial surface includes a device which disturbs the flow of cooling air and increases the heat exchange area between the air and the collar.

Abstract: An aircraft nacelle in which a power plant is arranged delimits a duct for a flow which assists the thrust. The nacelle includes a device for reducing, canceling, or reversing the thrust that includes at least one flap that can have an active position in which it deflects—in the direction of a radial opening—at least a portion of the flow and an at-rest position in which the flap does not interfere with the flow, whereby the wall of the nacelle delimiting the duct includes at least one moving part that can occupy a first position in which it is interposed between the flow to be deflected and the flap and another position in which it releases the flap so as to allow the flap to change position and to move from the at-rest position to the active position.

Abstract: A method for controlling a turbomachine exhaust gas recirculation (EGR) system is provided. The EGR system may allow for the removal and sequestration of at least one constituent within the exhaust before the recirculation occurs.

Abstract: A support assembly for a turbine system is disclosed. The support assembly includes a transition duct extending between a fuel nozzle and a turbine section. The transition duct has an inlet, an outlet, and a passage extending between the inlet and the outlet and defining a longitudinal axis, a radial axis, and a tangential axis. The outlet of the transition duct is offset from the inlet along the longitudinal axis. The support assembly further includes a plurality of protrusions extending from the transition duct. The plurality of protrusions are configured to allow movement of the transition duct about at least one axis.