Abstract: A multi-engine aircraft that includes two or more powerplants, each including an electric motor, and an electric power system controlling electrical distribution and operatively connected to the electric motors. The electric power system includes primary battery packs operatively connected to the electric motor of a respective one of the two or more powerplants, a reserve battery pack, and a switch interconnecting the reserve battery pack and the electric motors. The reserve battery pack is shared by the electric motors by the switch and configured such that the reserve battery pack provides electric power to a selected one of the electric motors.

Abstract: A gas turbine engine comprising a fan, an intermediate pressure compressor, a high pressure compressor, a high pressure turbine, a low pressure turbine and a gearbox. The low pressure turbine is arranged to drive the intermediate pressure compressor via a shaft and an intermediate pressure compressor drive shaft and the fan via the shaft, a gearbox input shaft, the gearbox and a gearbox output shaft. The intermediate pressure compressor drive shaft has a V-shaped cross-section comprising a base, a first limb and a second limb extending from the base. An end of the first limb of the intermediate pressure compressor drive shaft is removably connected to the intermediate pressure compressor. An end of the second limb of the intermediate pressure compressor drive shaft is removably connected to the gearbox input shaft and the base of the intermediate pressure compressor drive shaft is removably connected to the shaft.

Abstract: A geared architecture for a gas turbine engine includes a lubricant manifold for directing lubricant flow to the geared architecture. The manifold including annular channel and a bowl member received within the annular channel for defining a passage for directing lubricant.

Abstract: The present invention relates to a jet engine nacelle (1) comprising an aft section (5) having an internal structure (9) intended to surround an aft portion of an engine compartment and to define, with an exhaust nozzle (6), a calibrated outlet section for the ventilation of the engine compartment by way of spacing means arranged in the outlet section, characterized in that the spacing means are divided into rigid spacing means (11) designed to provide a constant spacing and into compensating means (13) designed so as to be able to adapt to the relative movements of the jet engine with respect to the nacelle.

Abstract: An apparatus and system disclosed herein provides detonation wave arrestor including a detonation wave deflector and a burst element. The detonation wave arrestor disclosed herein attenuates and defects the propagation of a detonation wave characterized by a supersonic flame front propagation. The detonation wave arrestor provides deflection of detonation wave towards the burst element. The rupture of the burst element provides venting of hot gases remaining from the detonation, thus providing separation and attenuation of combusted gas residuals. The detonation wave arrestor disclosed herein may be used in a combustible fuel delivery system.

Abstract: A rotor blade for a compressor includes a pressure sidewall; a suction sidewall coupled to the pressure sidewall at a leading edge and a trailing edge; and a through hole extending between the pressure sidewall and the suction sidewall.

Abstract: In one featured embodiment, a closure sleeve for a valve comprises a sleeve body surrounding a center axis and defined by an overall length extending from an upstream end to a downstream end. The sleeve body has an internal cavity that is enclosed at the downstream end and is open at the upstream end. The internal cavity is defined in part by a piston contact surface that is defined by an inner diameter. The piston contact surface is configured to slide against a piston to be received within the internal cavity, and a ratio of the inner diameter to the overall length is between 1.0 and 1.5.

Abstract: A method is described for controlling load variations in a gas turbine. The method comprises reducing the flow of gaseous fuel entering the combustor to a predefined minimum value, if an increase is observed in the rotation regime of said turbine above a predefined maximum value and a total reduction in the load, activating a selective feeding sequence of the burners if the turbine is operating in normal functioning or premixed flame mode, modifying the angulation of the adjustable stator vanes, in order to reduce the speed rate of the compressor, and opening one or more anti-surge valves and one or more overboard bleeds, in order to reduce the air flow at the inlet of the combustor.

Abstract: A pressure relief apparatus for an engine compartment having a wall and an opening in the wall is provided. The pressure relief apparatus includes a door panel arranged in blocking relationship to the opening in the wall of the engine compartment, a plurality of hinges coupling the door panel to an inner surface of the wall of the engine compartment, a spring assembly coupled between each hinge and the inner surface of the wall, wherein the spring assembly includes a canister having an open end and a spring element housed within the canister, and a support fitting mounted to the engine compartment wall and having a portion extending toward the open end of the canister for applying a compressive force on the spring element.

Abstract: A control system is provided for a power generating system having a gas turbine, a flue gas exhaust stage and a blow-off valve assembly. The gas turbine includes a compression stage, a combustion stage and a driveshaft. The blow-off valve assembly is configured to selectively provide fluid communication between the combustion stage and the flue gas exhaust stage. The control system includes a controller configured to output a signal causing the blow-off valve assembly to provide the fluid communication in response to a sudden de-loading of the gas turbine.

Abstract: A method of controlling variable extraction flow in a combustion turbine engine, wherein extraction flow comprises a supply of compressed air extracted from the compressor and supplied to the turbine through extraction conduits, and wherein the extraction conduits includes a variable extraction orifice, the method comprising the steps of: measuring a plurality of turbine engine operating parameters; monitoring, by a control unit, the measured operating parameters of the combustion turbine engine; setting the variable extraction orifices to a setting that allows an approximate maximum level of extraction flow; calculating, by the control unit, at least one calculated operating parameter based upon model-based control and the measured operating parameters, including at least a current turbine inlet temperature and a maximum turbine inlet temperature; and manipulating the setting for the supply of fuel to the combustor such that an increased and/or maximum level of engine output is determined by comparing the va

Abstract: A method may mitigate a flashback condition in a gas turbine. The gas turbine may include a fuel nozzle. The method may include detecting the flashback condition in the fuel nozzle, and interrupting a flow of fuel to the fuel nozzle.

Abstract: A gas turbine engine includes an epicyclic gear train that drives a turbo fan. The epicyclic gear train employs a one-piece carrier in which the spaced side walls are interconnected with circumferentially spaced apart mounts to form a unitary structure. Baffles are secured to the carrier near the mounts and provide lubrication passages that spray oil onto the sun gear and/or intermediate gears arranged between the baffles. The baffles can be constructed from a different material than the carrier since the baffles are not structural components in the gear train.

Abstract: The present invention relates to a gas storage power plant (1) with a gas store (8), a turbogroup (2) and a gas supply line (9) which leads from the gas store (8) to the turbogroup (2). A gas supply control device (12) is arranged in the gas supply line (9). So that a gas flow cam be provided, even in an emergency, the gas supply control device (12) has a main line (14) and a bypass line (19). The main line (14) forms a section of the gas supply line (9). In the main line (14) is arranged a main valve arrangement (15) which shuts off the main line (14) in an emergency. The bypass line (19) bypasses the main valve arrangement (15). In the bypass line (19) is arranged a bypass valve arrangement (20) which opens the bypass line (19) in an emergency.

Abstract: A vehicle driving method and hybrid propulsion system are disclosed. In the vehicle driving method and hybrid propulsion system, a heat engine is intermittently operated to provide a first power output and hot exhaust. A heat recovery unit containing thermal storage means is utilized to recover and store waste of hot exhaust, thereby enabling continuous production of motive gases during non-operation period of the heat engine. An expansion turbine is coupled to the heat engine and expands the motive gases to produce a second power output in a continuous fashion. The vehicle is driven by the first and second power outputs. A control unit operates the heat engine in an on/off mode to intermittently supply the hot exhaust to heat recovery unit, thereby providing remarkable fuel economy with reduced pollutants.