Abstract: A seal arrangement for sealing a gap between two housing parts, the gap being situated between opposite end faces of the housing parts. In the first housing part, there is a first receiving groove on the first end face, in which first receiving groove a sealing strip is arranged which protrudes out of the receiving groove and lies against a first outer flank. The sealing strip engages in an opposite second receiving groove of the second housing part and lies against a second outer flank. For position securing purposes and to achieve a sealing effect, even if there is no differential pressure, a spiral strip is provided, which spiral strip is situated in the first receiving groove and exerts an elastic force on the sealing strip.

Abstract: This steam turbine is provided with: a steam turbine rotor which extends in an axial direction; a pair of bearings which support the steam turbine rotor in such a way as to be capable of rotating about the axial direction; a steam turbine casing which encloses the steam turbine rotor between the pair of bearings; a casing support unit which supports the steam turbine casing from below; and a first heating unit which is provided on the casing support unit and which is capable of heating the casing support unit.

Abstract: A structure is provided for a gas turbine engine. This gas turbine engine structure includes an engine case, an engine pylon and an engine line. The engine case includes a base, a mounting boss and a first support element. The base extends axially along and circumferentially about an axial centerline of the engine case. The mounting boss projects radially out from the base. The first support element projects radially out from the base and laterally out from the mounting boss. The first support element is configured as or otherwise includes a peripheral boss. The engine pylon is mounted to the mounting boss. The engine line is coupled to the peripheral boss.

Abstract: A method and system for aligning a component within a turbine casing, and a related turbine casing. In a top-on position, a location of an optical target and another, vertically spaced optical target on the joint flange are measured. After removing at least the upper casing, the optical targets' locations are measured again, and the locations of a pair of reference points on an upper surface of the horizontal joint flange are measured. A prediction offset value is calculated for the component support position in the top-on position based on the locations. The prediction offset value may include a vertical adjustment based, in part, on a translation of a triangular spatial relationship of a number of the reference points and/or a tilt angle, a horizontal adjustment, and a horizontal joint flange surface distortion adjustment. Support position is adjusted by the prediction offset value to improve alignment.

Abstract: Disclosed is a compressor of a dual-flow aircraft turboshaft engine extending longitudinally along an axis X, the compressor comprising a low-pressure compressor, a high-pressure compressor and an intermediate casing axially connecting the low-pressure compressor and the high-pressure compressor, the high-pressure compressor comprising an inlet guide stator comprising a retaining ring, an outer high-pressure compressor casing and a plurality of vanes, the compressor comprising an immobilising device comprising at least one first member secured to the intermediate casing and at least one second member secured to the retaining ring and configured to cooperate with the first member in order to prevent tangential movement while allowing axial movement and radial movement of the retaining ring relative to the intermediate casing according to the axis X.

Abstract: The present disclosure is directed to a composite component defining a component aperture extending between a first surface and a second surface. The composite component includes an insert having an insert annular wall positioned in the component aperture. The insert annular wall defines an insert aperture therethrough. An insert flange extends radially outwardly from the insert annular wall and contacts the first surface of the composite component. The insert flange includes a diameter about 1.5 times to about 5 times greater than a smallest diameter of the component aperture defined by the composite component.

Abstract: A turbine blade tip, turbine blade and method where improved cooling is made possible by an improved cooling structure with cooling air holes inside a depression in a blade tip and a special arrangement of multiple cooling air holes which are supplied by a single cooling air channel inside a wall.

Abstract: Airfoils and methods of cooling an airfoil are provided. The airfoil may comprise a spar; a coversheet on the spar; and a dual feed circuit between the spar and the coversheet. The dual feed circuit may include a first dam, a second dam spaced apart from the first dam along the chord axis of the spar, a first inlet disposed adjacent to the first dam, a second inlet disposed adjacent to the second dam, a circuit outlet disposed between the first inlet and the second inlet, and a plurality of diamond and/or hexagonal pedestals disposed on an outer surface of the spar. The diamond and/or hexagonal pedestals may form a plurality of cooling channels between the first inlet, the second inlet, and the circuit outlet. There may be no other circuit inlets are located between the first inlet and the second inlet.

Abstract: A turbine system component includes a body having an exterior surface, and a cooling passage defined in the body. The cooling passage has a first cross-sectional area in the body. The component also includes a hollow member defining a first exit opening at the exterior surface of the body and coupled in the cooling passage. The hollow member, at the first exit opening, has a second cross-sectional area that is less than the first cross-sectional area, creating an exit opening with a smaller dimension than the original cooling passage. The hollow member is made of a material having a melt temperature higher than an operating temperature of the turbine system. The hollow member(s) reduces the cooling capabilities of the cooling passage. A cooling profile of the component can be generated to identify those cooling passages having excess cooling so they can have their exit openings reduced in cross-sectional area.

Abstract: A moving blade for a wheel of an aircraft turbine engine, including an aerodynamic aerofoil and an outer heel defining the aerofoil. The heel includes a platform and a first lip that projects from the platform. The first lip is inclined upstream and peripherally along an axis of elongation. The heel includes a row of ribs that are arranged at a distance from each other. The row of ribs extends along the axis of elongation and from the platform up to the first lip. The ribs are arranged upstream of the first lip in such a way as to generate turbulence upstream of first lip.

Abstract: A rotor arrangement for a rotor of a gas turbine includes at least one rotor disk with attachment slots for carrying rotor blades and an annular groove having an annular opening towards the outward direction; and rotor blades having an airfoil and a blade root and assembled in an attachment slot. Each of the assembled blade roots have a root extension with a root groove. The root groove faces the annular groove when the rotor blade is assembled in the attachment slot. For each assembled rotor blade a locking element is provided, the locking element engaging the annular groove of the rotor disk and the root groove of the respective rotor blade. Preferably all locking elements are embodied as a locking sheet metal strip, which has two bended tongues embracing the respective root extension.

Abstract: There is provided apparatuses and methods for a gas turbine engine. The embodiments include a core section with a flow path. The flow path includes a stator vane array having outlet vanes. Each outlet vane has a trailing edge. A strut has a leading edge that is upstream of the trailing edges. Alternatively, the flow path includes a stator vane array having inlet vanes. Each inlet vane has a leading edge. The strut has a trailing edge that is downstream of the leading edges. There also is increased spacing between adjacent vanes and rotor blades.

Abstract: A gas turbine engine defining a centerline and a circumferential direction, the gas turbine engine including: a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the turbomachine defining a working gas flowpath and a fan duct flowpath; a primary fan driven by the turbomachine defining a primary fan tip radius R1 and a primary fan hub radius R2; a secondary fan located downstream of the primary fan and driven by the turbomachine, at least a portion of an airflow from the primary fan configured to bypass the secondary fan, the secondary fan defining a secondary fan tip radius R3 and a secondary fan hub radius R4, wherein the secondary fan is configured to provide a fan duct airflow through the fan duct flowpath during operation to generate a fan duct thrust, wherein the fan duct thrust is equal to % Fn3S of a total engine thrust during operation of the gas turbine engine at a rated speed during standard day operating conditions; wherein a ra

Abstract: The present disclosure relates to cogeneration of power and one or more chemical entities through operation of a power production cycle and treatment of a stream comprising carbon monoxide and hydrogen. A cogeneration process can include carrying out a power production cycle, providing a heated stream comprising carbon monoxide and hydrogen, cooling the heated stream comprising carbon monoxide and hydrogen against at least one stream in the power production cycle so as to provide heating to the power production cycle, and carrying out at least one purification step so as to provide a purified stream comprising predominately hydrogen.

Abstract: An energy storage system converts variable renewable electricity (VRE) to continuous heat at over 1000° C. Intermittent electrical energy heats a solid medium. Heat from the solid medium is delivered continuously on demand. An array of bricks incorporating internal radiation cavities is directly heated by thermal radiation. The cavities facilitate rapid, uniform heating via reradiation. Heat delivery via flowing gas establishes a thermocline which maintains high outlet temperature throughout discharge. Gas flows through structured pathways within the array, delivering heat which may be used for processes including calcination, hydrogen electrolysis, steam generation, and thermal power generation and cogeneration. Groups of thermal storage arrays may be controlled and operated at high temperatures without thermal runaway via deep-discharge sequencing. Forecast-based control enables continuous, year-round heat supply using current and advance information of weather and VRE availability.

Abstract: An engine brake rocker arm assembly for a valvetrain and operable in an engine drive mode and an engine braking mode. The assembly is configured to selectively open one of first and second exhaust valves in the engine braking mode and includes a brake rocker arm configured to rotate about a rocker shaft, and an engine brake capsule assembly movable between (i) a locked position configured to perform an engine braking operation, and (ii) an unlocked position that does not perform the engine braking operation. A lash setting tool is configured to removably engage the engine brake capsule assembly and move the engine brake capsule to the locked position to enable mechanical lash adjustment while the brake rocker arm is assembled in a valvetrain and the engine brake capsule is assembled in the brake rocker arm.

Abstract: An electronic phaser system configured for use in an engine system is provided. The electronic phaser system comprises an intake camshaft, an electronic phaser and an engine control module (ECM). The intake camshaft has a plurality of camshaft lobes. The electronic phaser couples a gearbox to the intake camshaft. The electronic phaser is configured to rotationally advance the intake camshaft an amount of crank degrees to a desired rotational position. The ECM targets a desired cranking compression ratio based on one of an engine stop request and an engine start request. The ECM converts the desired cranking compression ratio into a camshaft lobe centerline position and commands the electronic phaser to rotate the intake camshaft to the desired rotational position that satisfies the camshaft lobe centerline position to achieve the desired cranking compression ratio. The desired cranking compression ratio is between 5:1 and 6:1.

Abstract: A measuring rod for measuring a fill level of a lubricant in a reservoir of an internal combustion engine includes a rod element, at one end of which is arranged a measuring tongue which can be submerged into the lubricant and by which the fill level can be measured and can be detected visually. At least one sealing element is arranged on the measuring tongue, by way of which the measuring rod can be sealed in relation to a guide tube for guiding the measuring rod.

Abstract: A lubrication system for internal combustion engines, in particular for vehicles with a rideable saddle, said system comprising a crank chamber in which at least one connecting rod is accommodated, and a basin or pan for collecting a lubricating liquid, wherein said crank chamber and said collection basin or pan are put in mutual communication by means of a first opening obtained in said crank chamber, wherein the flow of said lubricating liquid through said first opening from said crank chamber into said basin is adjusted by means of a first adjusting element adapted to be switched to an open position so as to allow the discharge of said lubricating liquid from said crank chamber into said collection basin or pan at a predetermined switching gas pressure value inside said crank chamber.

Abstract: A muffler includes a housing defining a first chamber, a second chamber and a third chamber. The muffler includes at least a pair of nested protrusions in communication with an inlet. The pair of nested protrusions is coupled to a respective surface of a pair of plates disposed in the housing such that one of the pair of nested protrusions is spaced apart from and opposite another of the pair of nested protrusions to define a tortuous path that terminates at an outlet defined along an outer circumference. The first chamber is downstream from the pair of plates. The muffler includes a first tube fluidly coupled to the first chamber to direct the exhaust gases from the first chamber to the second chamber. The muffler includes a second tube fluidly coupled to the second chamber to direct the exhaust gases from the second chamber to the third chamber.

Abstract: A method for automatically changing the engine exhaust sound in conjunction with the traveling mode implemented by the exhaust system applied to the vehicle may vary the valve opening of an electronic variable valve provided in a first tail pipe of first and second tail pipes of muffler discharging the exhaust gas coming from an engine by a mode recognition logic connected to an engine ECU to the atmosphere, and control the variation of the valve opening with the engine torque and the engine RPM based on a change in an accelerator pedal stroke in any one of a SMART DRIVE MODE-ECO state, a SMART DRIVE MODE-COMFORT state, and a SMART DRIVE MODE-SPORT state, implementing a quiet engine exhaust sound and a sporty engine exhaust sound depending on various vehicle traveling states provided by the SMART DRIVE MODE and increasing vehicle/engine outputs.

Abstract: A turbocharger manifold is disclosed. In one embodiment, the manifold has a first exhaust conduit, a second exhaust conduit, and a valve. The first exhaust conduit has a first exhaust inlet and a first turbocharger outlet. The second exhaust conduit has a second exhaust inlet and a second turbocharger outlet. The second exhaust inlet is connected to the first exhaust conduit. The valve has an open position and a closed position and controls exhaust gas access from the first exhaust conduit to the second exhaust conduit.

Abstract: Subject of the invention is an exhaust gas purification system for a gasoline engine, comprising in consecutive order the following devices: a first three-way-catalyst (TWC1), a gasoline particulate filter (GPF) and a second three-way-catalyst (TWC2), wherein the platinum-group metal concentration (PGM) of the GPF is at least 40% greater than the PGM of the TWC2, wherein the PGM is determined in g/ft3 of the volume of the device, The invention also relates to methods in which the system is used and uses of the system.

Abstract: A method to control an internal combustion engine having an exhaust duct and an exhaust gas after-treatment system comprising at least one catalytic converter arranged along the exhaust duct; an oxygen sensor housed along the exhaust duct and arranged upstream of said at least one catalytic converter; and a burner suited to introduce the exhaust gases into the exhaust duct upstream of the oxygen sensor the method provides the steps of calculating the thermal power required to reach the nominal operating temperature of said at least one catalytic converter obtained with an objective value of the air/fuel ratio value; and determining both the objective fuel flow rate and the objective air flow rate to be fed to the burner to obtain the thermal power required to reach the nominal operating temperature of said at least one catalytic converter.

Abstract: The present disclosure relates to an exhaust gas aftertreatment system and method for controlling same. The exhaust gas aftertreatment system comprises: a reductant dosing device; a selective catalytic reduction device arranged downstream of the reductant dosing device; an ammonia slip catalyst arranged downstream of the SCR device; a feedback NOx sensor arranged downstream of the SCR device and upstream of the ammonia slip catalyst; a tailpipe NOx sensor arranged downstream of the ammonia slip catalyst; and a control device configured for: providing an initial dosing of reductant from the reductant dosing device; obtaining a feedback signal from the feedback NOx sensor and a tailpipe NOx signal from the tailpipe NOx sensor; and adjusting the dosing of reductant until the feedback signal exceeds the tailpipe NOx signal by a value within a predetermined positive interval.

Abstract: An exhaust purification device includes a casing which accommodates a purifier that purifies exhaust gas of an engine mounted on a vehicle and in which a flow direction of the exhaust gas corresponds to a longitudinal direction of the casing, an inlet opening at a first longitudinal end of the casing, an outlet opening provided at a second longitudinal end of the casing, a first pipe connected to the inlet opening, and a second pipe connected to the outlet opening. A cross section of at least one of a connecting end of the first pipe for the casing and a connecting end of the second pipe for the casing is in a flattened shape as a dimension of the cross section in the longitudinal direction of the casing is shorter than a dimension of the cross section in a lateral direction of the casing.

Abstract: An equalizing tank for a cooling circuit of a motor of a motor vehicle has a tank top piece, on which an inlet line for a coolant is arranged, and a tank bottom piece, on which an outlet line for the coolant is arranged. The inlet line for the coolant is configured as a separate structural unit from the tank top piece, having an outlet opening situated in the region of the tank bottom piece.

Abstract: An auxiliary generator drive for a belt driven generator being powered by an internal engine, the auxiliary generator drive including a hydraulic motor, wherein the hydraulic motor is arranged and adapted to drive the generator and to be driven via a hydraulic pump powered by the internal engine.

Abstract: In vibratory plates (vibratory plate compactor machine), the reciprocating movement of an engine piston is converted into rotation of the crankshaft, and the latter is converted into rotation of an eccentric rotary shaft of vibrator unit, which create a periodic force that leads to reciprocating movement of the plate. Such a vibratory plate is complicated. It is proposed to use a free-piston engine with one piston as the engine for a vibratory plate. In this free piston engine, the piston moves reciprocally, and the cylinder performs reciprocating movements opposite to the movements of the piston. The cylinder is mounted vertically and fixed to the plate. In each engine cycle the gas pressure acts on the piston and cylinder. After combustion, the piston moves up and the cylinder moves down. Since the cylinder is fixed to the plate, it also moves downward and compacts soil, gravel, etc.

Abstract: A gas turbine engine system includes a gas turbine engine including a compressor, combustor including a plurality of late lean fuel injectors supplied with secondary fuel; gas turbine, and wash system configured to be attached and in fluid communication with the late lean fuel injectors. The wash system includes a water source including water; first fluid source including a first fluid providing vanadium ash and vanadium deposit mitigation and removal from internal gas turbine components; a mixing chamber in communication with the water source and first fluid source; a water pump to pump the water to the mixing chamber; a first fluid pump the first fluid to the mixing chamber; a fluid line in fluid communication with the mixing chamber and late lean fuel injectors so fluid from the mixing chamber is injected into the combustor at the late lean fuel injectors while the gas turbine engine is on-line.

Abstract: An airflow profiled structure having a profiled leading edge. The profiled leading edge having, along a leading edge line, a serrated profile line with a succession of teeth and depressions. The airflow profiled structure also includes a porous acoustically absorbent region located towards the bottom of the depressions.

Abstract: An assembly is provided for a turbine engine with a flowpath. This assembly includes a fuel source and an engine component. The engine component forms a peripheral boundary of the flowpath. The engine component includes a component internal passage. The engine component is configured to receive fuel from the fuel source. The engine component is configured to crack at least some of the fuel within the component internal passage thereby cooling the engine component and providing at least partially cracked fuel. The assembly is configured to direct the at least partially cracked fuel into the flowpath for combustion.

Abstract: A multi-engine aircraft includes first and second gas turbine engines for providing motive power to the aircraft, each of the first and second engines comprising an air system, an air pressure line extending between and fluidly connecting the air systems of the first and second engines, and a pressure wave damper communicating with the air pressure line extending between the first and second engines.

Abstract: A gas turbine engine comprises at least a power output turbine unit (POT), which is rotatably arranged inside an outer housing unit, and a compressor-turbine unit (CTU), which is rotatably arranged inside the POT, and the CTU, POT and outer housing unit are arranged about a common axis of rotation (CL). The POT and the CTU are arranged in such close proximity (d) that a dynamic friction coupling is generated between the POT and the CTU.

Abstract: A turbine engine includes a first compression section includes a last blade trailing edge radial tip length that is greater than about 67% of the radial tip length of a leading edge of a first stage of the first compression section. A second compression section includes a last blade trailing edge radial tip length that is greater than about 57% of a radial tip length of a leading edge of a first stage of the first compression section.

Abstract: An aircraft propulsion system and computing system are provided. The propulsion system includes a low pressure (LP) spool and a core engine having a high pressure (HP) spool. A frame is positioned in serial flow arrangement between an HP turbine and an LP turbine. The frame includes an inter-turbine burner including a strut forming an outlet opening into a core flowpath of the propulsion system. A first fuel system is configured to flow a liquid fuel to a combustion section for generating first combustion gases. A second fuel system is configured to flow a gaseous fuel to the core flowpath via the inter-turbine burner for generating second combustion gases. The propulsion system forms a rated power output ratio of the core engine and the inter-turbine burner with the LP spool between 1.5 and 5.7.

Abstract: A system including a turbine engine configured to generate rotor power and produce an engine air flow. The system is configured to provide rotor power to one of more shaft-driven lift fans to generate a first thrust on an aircraft body and provide a gas flow to one or more gas-driven lift fans to generate a second thrust on the aircraft body. The gas flow may be at least a portion of the engine air flow produced by the turbine engine. The turbine engine may be configured to exhaust another portion of the engine air flow through a jet nozzle to generate an engine thrust. In examples, the system includes at least a second turbine engine. The one of more shaft-driven lift fans and/or one of more gas-driven lift fans be powered by the turbine engine, the second turbine engine, or both the turbine engine and the second turbine engine.

Abstract: A diffuser pipe has a tubular body defining a pipe center axis extending therethrough. The tubular body includes a first portion extending in a generally radial direction from an inlet of the tubular body, a second portion extending in a generally axial direction and terminating at a pipe outlet, and a bend portion fluidly linking the first portion and the second portion. The tubular body has a length defined between the inlet and the pipe outlet. The tubular body has cross-sectional profiles defined in a plane normal to the pipe center axis. An area of the cross-sectional profile at the pipe outlet is at least 20% greater than an area of the cross-sectional profile at a point upstream from the pipe outlet a distance corresponding to 10% of the length of the tubular body.

Abstract: In a closed system that recirculates exhaust gas from a gas turbine engine, recirculated exhaust gas should be mixed into inlet gas in a manner that produces a uniform distribution within the mixed gas, while preventing an excessive pressure drop at the point of mixing, and without needing excessive duct length. Otherwise, the performance of the gas turbine engine may be detrimentally affected. Accordingly, a mixer box is disclosed that injects recirculated exhaust gas into a flow path of inlet gas in a uniform manner. The mixer box may comprise mixer(s) that extend the flow path of the recirculated exhaust gas into the flow path of the inlet gas along two axes. Each mixer may comprise surface apertures and/or interior channels designed to promote uniform ejection of the recirculated exhaust gas from the mixers into the flow path of inlet gas.

Abstract: An assembly for an aircraft includes a variable area inlet for an aircraft propulsion system. The variable area inlet extends along a longitudinal centerline. The variable area inlet includes an inlet structure, an inlet door, an inner inlet passage, and an outer inlet passage. The inlet door is configured to axially translate from a closed position to an open position along the longitudinal centerline. The inlet door is configured to close the outer inlet passage when the inlet door is in the closed position. The inlet door is configured to open the outer inlet passage when the inlet door is in the open position. The inner inlet passage extends into the variable area inlet from a leading edge of the inlet structure. The outer inlet passage extends through the inlet structure to the inner inlet passage.

Abstract: A gearbox for a gas turbine engine. The gearbox including a rotor and a gutter. The oil system is configured to supply oil to the gearbox. The rotor is rotatable about a rotation axis. The rotor expels oil radially outward when the rotor rotates. The gutter is positioned radially outward of the rotor to collect oil expelled by the rotor when the rotor rotates. The gutter is positioned eccentrically with respect to the rotor.

Abstract: A turbine engine having a drive shaft rotatable about an axis, a multi-stage compressor, a turbine section, a thrust bearing, and a balance cavity. The thrust bearing being provided between the drive shaft and at least a portion of the multi-stage compressor section and rotationally supporting the drive shaft. During operation of the turbine engine, a first axial force is applied to the thrust bearing by the drive shaft and a second axial force is applied to the thrust bearing in an opposite direction of the first axial force by the balance cavity.

Abstract: In a gas turbine and a control method thereof, and a combined cycle plant, the gas turbine includes a compressor that compresses air, a combustor that mixes and combusts compressed air compressed by the compressor and fuel, a turbine that obtains rotational power using combustion gas generated by the combustor, a compressed air cooling heat exchanger that cools the compressed air to produce air for heat exchange, air temperature adjusting heat exchangers that exchange heat between the air and the compressed air, a heat exchange amount adjusting device that adjusts a heat exchange amount of each of the compressed air cooling heat exchanger and the air temperature adjusting heat exchangers, and a control device that controls the heat exchange amount adjusting device, in which the control device controls the heat exchange amount adjusting device based on a temperature of the air to be taken into the compressor.

Abstract: A thermodynamic apparatus (10) comprising a compressor module (100), a turbine module (200), and a regenerative heat exchanger (300) centred on a central axis (12). The compressor module (100), turbine module (200) and regenerative heat exchanger (300) are arranged in series along the central axis (12) such that the regenerative heat exchanger (300) is provided between the compressor module (100) and the turbine module (200).

Abstract: Accelerators, methods of manufacturing accelerators, and gas turbine engines are provided. For example, an accelerator for a gas turbine engine defines a radial direction and an axial direction and comprises an annular outer wall, an annular inner wall, an annular channel defined between the outer and inner walls, and a plurality of vanes disposed within the channel. The channel has an inlet for ingress of a cooling fluid and an outlet for egress of the cooling fluid. Each vane extends from the outer wall to the inner wall adjacent the outlet, which is angled such that an exit angle of the cooling fluid is nonzero with respect to both the radial and axial directions. The accelerator may be manufactured using an additive manufacturing method. The accelerator outlet may be disposed immediately upstream of a first turbine rotor blade stage of a gas turbine engine to direct the cooling fluid thereto.

Abstract: A fuel system can include a selection and shutoff valve (SSOV) configured to allow a primary flow having a primary flow pressure to pass therethrough in a first state such that the primary flow can travel to an output line. The SSOV can also be configured to shut off the primary flow in a second state to prevent the primary flow from travelling to the output line. In the second state, the SSOV can be configured to allow a secondary flow from a secondary flow source to pass therethrough such that the secondary flow can travel to the output line.

Abstract: A system includes a recirculation conduit that recirculates working fluid and a permanent magnet generator module in communication with the recirculation conduit. The working fluid from the recirculation conduit drives the permanent magnet generator module.

Abstract: A fluid injection system can include a main flow line, a primary flow line connected to the main flow line, and a primary flow valve disposed between the primary flow line and the main flow line and configured to allow injectant flow to the primary flow line from the main flow line in an open primary flow valve state, and to prevent injectant flow to the primary flow line from the main flow line in a closed primary flow valve state. The system can include a secondary flow line connected to the main flow line and a secondary flow valve disposed between the secondary flow line and the main flow line and configured to selectively allow injectant flow to the secondary flow line from the main flow line in an open secondary flow valve state, and to prevent injectant flow to the secondary flow line from the main flow line in a closed secondary flow valve state.

Abstract: A method of operating a multi-engine system of an aircraft having first and second engines includes accumulating compressed air in a pressure vessel external to the engines, and operating the first and second engines asymmetrically, by controlling the first engine to operate in an active operating condition providing sufficient power and/or rotor speed for demands of the aircraft, and controlling the second engine to operate in a standby operating condition wherein the second engine produces less power output than the first engine. In response to a power demand request, the second engine is accelerated out of the standby operating condition by introducing therein compressed air from the pressure vessel at a location upstream of a combustor of the second engine.

Abstract: Methods and systems for starting an aircraft gas turbine engine are described. The method comprises, in a first phase of a startup upon receipt of a start request, modifying a first set of engine control parameters to cause light-up; in a second phase of the startup, modifying a second set of engine control parameters to set conditions for light-around; and in a third phase of the startup, modifying a third set of engine control parameters to propagate a flame around a combustor of the gas turbine engine.