Abstract: A dozer valve bracket includes a first member to secure to a rail. A second member receives a dozer valve. A pivot couples the first and second members with one another for pivotal movement with respect to one another. A stop in the second member contacts the rail to provide a second position to enable the second member to pivot away from the first member on another side of the rail to enable installation of an exhaust system.

Abstract: A fuel system includes a main pump assembly. The main pump assembly has a main fuel pump connected to an input line, a recirculation pump connected to the input line, and a fuel recirculation system. A recirculation control includes a first selector valve in fluid communication with an outlet line of the recirculation pump, with a recirculation return line connected to return fuel to the input line, and with an inter-valve line. The recirculation control includes a second selector valve in fluid communication with the inter-valve line, with a back-up line connecting the second selector valve to a main fuel control, and with a cooler recirculation line connected to supply the one or more coolers.

Abstract: The invention relates to a method for filtering an input signal (3b, 4b, 5b) relative to a physical variable of a turbine engine (9), the input signal being digitised, the method implementing frequency filtering of said signal in a computer (6) of a control system (7) of said turbine engine (9), said signal being provided at the input of the computer, a digital derivative of said signal being intended for being used by the control system (7), characterised in that it involves: —detecting an amplitude variation of said variable on said input signal, by a step of generating a second derivative signal (S) of the input signal and a step of comparing a value of the second derivative value of the input signal with at least one predetermined threshold (S1 . . .

Abstract: An inner structure is within an outer structure. A shield mount of a shield is attached to the outer structure. A sleeve of the shield extends from the shield mount through an aperture in the outer structure to a distal end of the shield. The sleeve is mated with the port at the distal end through a slip joint interface where a cylindrical sleeve surface of the sleeve contacts a cylindrical port surface of a port of the inner structure. The fluid transfer tube extends from an inner tube end through a bore of the shield and at least into the port to an outer tube end. An inner coupling is disposed at the inner tube end and mated with the inner structure through a cone seal interface. An outer coupling is disposed at the outer tube end and attached to the outer structure.

Abstract: A service tube assembly for an aircraft engine, comprising: a service tube having a threaded end portion, an opposed end portion and an annular tube surface proximate to the threaded end portion; a housing having an outer surface defining a tube socket extending in the outer surface, and a ramp extending toward the tube socket so as to define an engagement direction, the tube socket engaged with the threaded end portion of the service tube; a locking member having a bottom surface disposed against the ramp and an engagement surface facing toward the service tube, the locking member slidable along the ramp in the engagement direction between a first member position in which the engagement surface is spaced from the annular tube surface and a second member position in which the engagement surface contacts the annular tube surface; and a fastener releasably holding the locking member against the ramp.

Abstract: Heat-exchange and noise-reduction panel for a propulsion assembly, in particular for an aircraft, the panel comprising: a perforated plate comprising a plurality of through-openings; a cellular structure comprising longitudinally oriented structural walls covered by said perforated plate and comprising, between said walls, cavities that define Helmholtz resonators, said through-openings forming necks of said resonators; and means for the circulation of fluid, for example oil, at said perforated plate, wherein said fluid circulation means comprise channels that are formed at least in part in thickened ends of said walls on the same side as said perforated plate, and/or at least in part in regions of the perforated plate situated in the longitudinal extension of said thickened ends.

Abstract: A damper of shock and vibration. In one embodiment there is a hydraulic damper with a regressive damping characteristic in both compression and extension, such that damping forces decrease with increased stroking velocity within a predetermined range of stroking velocity. Outside of this range, damping forces are progressive, such that the damping force increases with increased stroking velocity. In another embodiment, there is a hydraulic damper with a second, slidable piston within one of the internal chambers defined by the main piston. This secondary piston is spring loaded and hydraulically latchable at either a first position or a second position based on the pressure differential across the main piston.

Abstract: In one featured embodiment, a sleeve for a valve includes a sleeve body surrounding a center axis and defined by an overall length extending from a first end to a second end. The sleeve body has a central bore extending from the first end to the second end. The central bore has a first surface portion comprising a piston contact surface that is defined by a first inner diameter, wherein the piston contact surface is configured to slide against a piston to be received within the central bore. In one example, a ratio of the overall length to the first inner diameter is between 3.51 and 3.63.

Abstract: A protocol for assembling a fuel shut off pin valve assembly for a gas turbine engine. The protocol outlines a specific sequence of events in order to ensure failsafe incorporation of a fuel shut off valve assembly within the low pressure turbine area and specifically within the engine casing of the gas turbine.

Abstract: Integrally formed, multi zone fuel manifolds for gas turbine engines and methods of construction are provided. The fuel manifold includes a plurality of annular channel members positioned adjacent each other, aligned and coupled together at the inner and outer peripheral sides thereof, with each pair of channel members defining a separate fluid conduit or passage within the manifold assembly. The fuel manifold can be constructed of any number of stacked and secured channel members to provide a compact multi zone fuel manifold having the desired number of fluid conduits or passages with a minimum number of sealed joints.

Abstract: Methods and apparatus are provided for detecting an anomaly in fuel demand data and fuel supply data generated by a fuel metering system for an engine, The method comprises collecting the fuel demand data and the fuel supply data during operation of the fuel metering system, generating expected fuel supply data based on the collected fuel demand data and a nominal response model describing the expected behavior of the fuel metering system, and detecting the anomaly if a difference between the expected fuel supply data and the collected fuel supply data exceeds a predetermined threshold.

Abstract: A compressed air energy storage system and method of capturing CO2 during compressed air energy storage the system and method including a gas inlet pipe, at least one air compressor stage attached to the gas inlet pipe and adapted for compression of a gas, a heat transfer system to cool the gas during or after compression, the heat being recycled throughout the system, at least one absorption bed for separating CO2 from the compressed gas attached to the heat transfer system, at least one compressed gas reservoir having an inlet and an outlet, the reservoir attached at its inlet to the absorption bed, at least one preheater stage attached to the outlet of the compressed gas reservoir for heating a compressed gas after storage in the compressed gas reservoir, and at least one gas expander attached to the preheater stage and adapted for the expansion of the compressed gas.

Abstract: A fuel control system for a gas turbine engine reheat system has a plurality of fuel metering devices for controlling fuel flow to respective ones of the reheat burners, and a plurality of throttle valves in series with the respective metering devices. One of the throttle valves regulates a pressure difference across its associated metering device and the remaining throttle valves maintain the pressure difference across their respective metering devices equal to that controlled by the aforesaid one throttle valve. The system may include a fuel supply valve which is responsive to a pressure signal controlled by two of the metering devices so that fuel supply from a pump is provided only when both of the two metering devices are open. The pump may include a delivery pressure regulating arrangement responsive to pump delivery pressure and to the highest of the pressures downstream of the metering devices, for regulating pump delivery pressure so as to maintain the metering pressure differences constant.

Abstract: A protocol for assembling a fuel shut off pin valve assembly for a turbo fan engine. The protocol outlines a specific sequence of events in order to ensure failsafe incorporation of a fuel shut off valve assembly within the low pressure turbine area and specifically within the engine casing of the turbo fan.

Abstract: A fluid flow control system includes a valve, in which a control element regulates flow through a metering orifice. A further control element regulates flow through an orifice downstream of the orifice and is responsive to the pressure downstream of the orifice and to an opposing control pressure on a line. The element is positioned in accordance with the pressure in a chamber controlled by an electrical valve. The pressure in line is set to provide a required pressure drop across the orifice.

Abstract: A combustion device, such as an afterburner 4 for a gas turbine engine, comprises primary and secondary fuel delivery means 12, 20. Pressure fluctuations in the afterburner 4 are damped by reducing the supply of fuel through the primary fuel delivery means 12 during pressure peaks. This is achieved by means of a spill valve 18, controlled by a controller 22 in response to pressure in the afterburner 4 as sensed by a transducer 24. The spill valve 18 diverts a proportion of the fuel to the secondary fuel delivery means 20. The secondary fuel delivery means 20 is positioned upstream of the primary fuel delivery means 12 by a distance X, such that the secondary fuel delivery means serves to supply additional fuel to the combustion zone 26 during pressure troughs.

Abstract: A fuel system for a gas turbine engine having at least one augmentor zone which fuel system includes a fuel pump (12) drawing fuel from a fuel tank (10) and pumping the fuel in a downstream direction, at least one fuel line (14) connecting the fuel pump (12) to the at least one augmentor zone, at least one augmentor metering valve (20) in the at least one augmentor fuel line (14) for metering fuel to the at least one augmentor zone, and a fuel return path (32) returning fuel from a point in the fuel line (14) downstream of the fuel pump (12) to the fuel tank (10), wherein the point is downstream of the at least one augmentor metering valve (20). A selector valve (30) is provided to allow thermal recirculation of fuel using an augmentor metering valve. Also a method of controlling fuel recirculation in a gas turbine engine.

Abstract: A double flow turbo-jet engine includes a re-heating channel of the primary flow and an ejection nozzle, the secondary flow emerging at least partially in the primary flow upstream of the re-heating channel, the re-heating channel including a burner ring, including a flame holder gutter in the form of a ring portion whereof the upstream section is situated in the secondary flow, receiving a fuel manifold and a protective tubular screen of the manifold. The gutter includes an upstream recess linked with the secondary flow, and the screen includes, on its upstream section, at least one ventilation orifice of the space situated between the screen and the manifold.

Abstract: A turbofan gas turbine engine augmenter includes a fuel/air swirler disposed between an axially extending bypass flowpath and an axially extending exhaust flowpath. A swirler inlet is axially open to and positioned substantially normal to the bypass flowpath and a swirler outlet is open to and positioned substantially parallel to the exhaust flowpath. A swirl chamber within the fuel/air swirler is between the swirler inlet and the swirler outlet. A swirl axis of the fuel/air swirler extends through the swirler outlet substantially normal to the exhaust flowpath. An air swirler may be centered about the swirl axis within the fuel/air swirler. The air swirler may be a louvered or have a plurality of swirling vanes. The swirler inlet may be radially offset with respect to the swirl axis. An air scoop may lead from the swirler inlet to a rounded swirler housing within which the air swirler is disposed.

Abstract: A missile includes a control system having divert and attitude control system thrusters with control valves. Each of the control valves has a nozzle plate having a plurality of small nozzles therein. The nozzle plate includes a pair of portions, one of which is rotatable relative to the other. Control of flow through the nozzle plate may be effected by relative positioning of the portions of the nozzle plate. An upstream convergent portion of the nozzle plate may be fixed relative to the missile, with a downstream throat and/or divergent portion of the nozzle plate moveable. Movement of the movable portion of the nozzle plate may be accomplished by use of an actuator that is external to the missile body. The control valve provides a simple, lightweight and compact way of controlling flow from a divert thruster.

Abstract: An apparatus for providing a backup fuel metering system for the gas generator section (24) of a gas turbine engine (10) is disclosed that includes a gas generator (24) and an augmentor (40). The apparatus includes a gas generator fuel metering system (52) providing fuel to the gas generator nozzles (32) and an augmentor fuel metering system (54) providing fuel to an augmentor (40). The augmentor fuel system (54) includes a diverter valve (88) which selectably directs fuel to the augmentor (40) during augmentation operation or to the gas generator nozzles (32) during a gas generator metering system failure or critical engine operation. The system allows the gas generator nozzles (32) to be supplied with fuel flow from the gas generator metering system (52), the augmentor metering (54) system or both. When the gas generator nozzles (32) are being supplied with flow from both metering systems the system is capable of improved fault accommodation.

Abstract: A method for fabricating an augmentor includes fabricating an outer casing having at least one channel defined therein, fabricating a centerbody having at least one channel defined therein, fabricating a plurality of turbine frame vanes, wherein each turbine frame vane includes a first sidewall having a first channel defined therein, a second sidewall having a second channel defined therein, and at least one cross-fire tube extending between the first sidewall and the second sidewall, and coupling the plurality of turbine frame vanes to the augmentor outer casing and to the centerbody such that the first sidewall first channel formed on a first turbine frame vane, the second sidewall second channel formed on a second turbine frame vane, the augmentor channel, and the centerbody channel define a substantially contiguous trapped vortex chamber.

Abstract: A fuel control system for an aircraft gas turbine engine that includes a thrust augmentation system. An augmentor fuel pump is arranged to provide pressurized fuel to an exhaust nozzle throat area actuation system to eliminate the need for a separate hydraulic pump to provide pressurized fluid for exhaust nozzle actuation. An augmentor fuel bypass arrangement is provided to enable the augmentor fuel pump to provide pressurized fuel to the main fuel pressurizing valve and to components operated by the main fuel system in the event of failure of the main fuel pump. The augmentor fuel pump pressure and output flow are controlled as a function of thrust augmentation demand and main fuel system operation. The system provides redundancy by enabling either the main fuel system or the augmentor fuel system to maintain engine operation if one of the fuel systems fails or provides inadequate fuel flow.

Abstract: A fuel control system for an aircraft gas turbine engine that includes a thrust augmentation system. An augmentor fuel pump is arranged to provide pressurized fuel to an exhaust nozzle throat area actuation system to eliminate the need for a separate hydraulic pump to provide pressurized fluid for exhaust nozzle actuation. An augmentor fuel bypass arrangement is provided to enable the augmentor fuel pump to provide pressurized fuel to the main fuel pressurizing valve and to components operated by the main fuel system in the event of failure of the main fuel pump. The augmentor fuel pump pressure and output flow are controlled as a function of thrust augmentation demand and main fuel system operation. The system provides redundancy by enabling either the main fuel system or the augmentor fuel system to maintain engine operation if one of the fuel systems fails or provides inadequate fuel flow.

Abstract: A frequency tracking extended Kalman filter (35), responsive to combustor pressure (30), produces in-phase (36) and quadrature (37) components of the estimated magnitude of the undesirable combustor pressure variations, for which compensation is to be achieved; a bidirectional minimum-seeking algorithm (41) is used to select the phase (42) of a process adjusting input variable (28), such as fuel that is in addition to the main fuel flow used for power control purposes.