Abstract: The present disclosure is directed to a gas turbine engine structure and method for reducing or mitigating bowed rotor. The method includes coupling a rotor assembly to a mechanical energy storage device via a clutch mechanism when the rotor assembly is at or below a speed limit below an idle speed condition; storing mechanical energy at the mechanical energy storage device via rotation of the rotor assembly at or below the speed limit; releasing mechanical energy from the mechanical energy storage device to rotate the rotor assembly following shutdown of the gas turbine engine; and rotating the rotor assembly via the mechanical energy from the mechanical energy storage device.

Abstract: An annular fuel manifold includes an annular fuel plenum defined within the annular fuel manifold, an axial inlet into the annular fuel plenum, and a deflector downstream of the axial inlet, the deflector oriented such that fluid flow into the annular fuel plenum from the axial inlet is deflected by the deflector at least partially along a circumference of the annular fuel plenum.

Abstract: A control device for a power generation system whereby power is generated by a first power source that operates by burning a fuel. The control device identifies, on the basis of a pressure difference in a prior-stage mechanism that supplies the fuel to the first power source, a fuel capacity that compensates for the pressure difference in the prior-stage mechanism. The pressure difference is the difference between a pressure set for the fuel before a load change in the prior-stage mechanism and a pressure set for the fuel after the load change in the prior-stage mechanism. The control device calculates a fuel supply command value, which is a command value for adjusting the amount of fuel supplied to a fuel supply device that supplies the fuel to the first power source, and is output to the fuel supply device using a fuel supply acceleration command value.

Abstract: A turbine engine has a fan and a low pressure compressor that rotate at a common speed and in a common direction. A fan drive turbine drives a gear reduction to, in turn, drive the low pressure compressor and the fan at a speed which is slower than a speed of the fan drive turbine. A combustor intermediate the low pressure compressor and the fan drive turbine and a thrust bearing mount the fan drive turbine, the thrust bearing being aft of a location of the combustor. A shear section in a drive connection connecting the fan drive turbine to the gear reduction is weaker than other portions of the drive connection. The shear section is aft of the thrust bearing.

Abstract: A centrifugal separator for separating gas and liquid from a gas-liquid mixture, the centrifugal separator comprising: a housing having a cavity and a gas-liquid mixture inlet leading tangentially into the cavity along an inlet path to form a vortex therein, a separated gas outlet and a separated liquid outlet; and a rotor rotatably mounted to the housing inside the cavity in a manner to be freely rotatable around a rotation axis, the rotor having a hub extending axially along said axis, the rotor having a plurality of vanes extending radially from the hub inside the cavity, the vanes being disposed in the inlet path in a manner so that the rotor is rotated by the gas-liquid mixture during use.

Abstract: A particle separator system for use with a turbomachine is provided. The particle separator system includes a first end, a second end opposite the first end, a main separator body extending between the first and second ends, the main separator body including at least one step configured to cause a fluid flow to turn up to 180 degrees, and at least one transversely oriented cyclone separator disposed within the main separator body and defining at least one of a swirling cylinder, a bent cylinder, and a conical volume.

Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction extended from an axial centerline, and a circumferential direction. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in serial flow arrangement along the longitudinal direction. The gas turbine engine includes a low speed turbine rotor comprising a hub extended along the longitudinal direction and radially within the combustion section; a high speed turbine rotor comprising a high pressure (HP) shaft coupling the high speed turbine rotor to a HP compressor in the compressor section; a first turbine bearing disposed radially between the hub of the low speed turbine rotor and the HP shaft. The HP shaft extends along the longitudinal direction and radially within the hub of the low speed turbine rotor.

Abstract: A starter air valve comprising a housing comprising an inlet at a first end and an outlet at a second end opposite the first end, the inlet being fluidly connected to the outlet through a fluid pathway; a valve injected into the fluid pathway dividing the fluid pathway into a first chamber and second chamber, the valve in operation adjusts fluid flow through fluid pathway; an actuator operably connected to the valve; a solenoid in variable electrical connection with the actuator; and a rotary spool valve fluidly connected to the first chamber, the rotary spool valve operable to rotate to at least one of a normal start position, a full manual override position, and a plurality of partial manual override positions, wherein the rotary spool valve is in variable fluid connection with the actuator, wherein the solenoid is in variable electrical connection with the actuator through the rotary spool valve.

Abstract: A flow conditioner in a combustor of a gas turbine comprises a body and a flow conditioning portion configured to be placed in an air path providing air flow to a combustion chamber, the flow conditioning portion including a plurality of holes tuned to a damping frequency to dampen a pressure fluctuation caused by combustion dynamics from the combustion chamber.

Abstract: A cylinder for a combustor includes a cylindrical member, a first cooling passage defined in the cylindrical member and a second cooling passage defined in the cylindrical member, and a supply port extender. The first cooling passage includes a supply port that opens to an outer peripheral surface of the cylindrical member. The second cooling passage includes a discharge port that opens to the outer peripheral surface of the cylindrical member downstream of the supply port. The supply port extender includes a first wall that is disposed between the supply port and the discharge port and extends away from the outer peripheral surface of the cylindrical member and a second wall that is disposed upstream of the supply port and extends away from the outer peripheral surface of the cylindrical member.

Abstract: A thermal energy exchange system for cooling air of a gas turbine engine includes a heat exchanger located at a diffuser of the gas turbine engine. The diffuser is positioned axially between a compressor and a combustor of the gas turbine engine. A fuel source is operably connected to the heat exchanger to direct a flow of fuel through the heat exchanger via a fuel pipe and toward a fuel nozzle of the combustor. An airflow inlet directs a cooling airflow through the heat exchanger to reduce an airflow temperature via thermal energy exchange between the cooling airflow and the flow of fuel. An airflow outlet directs the cooling airflow from the heat exchanger toward one or more of components of the turbine to cool the one or more components.

Abstract: A system for retaining stators and reducing air leakage in a gas turbine engine having an axis includes a stator having an inner platform, an outer platform, a low pressure side, a high pressure side, and at least one foot, and designed to turn air. The system also includes a case positioned radially outward from the stator and having at least one recess designed to interface with the at least one foot to resist movement of the stator relative to the case. The system also includes a bladder positioned between the outer platform of the stator and the case and designed to receive pressurized fluid having a greater pressure than ambient pressures experienced at the low pressure side of the stator and to further resist movement of the stator relative to the case in response to receiving the pressurized fluid.

Abstract: The present disclosure is directed to a gas turbine engine defining a longitudinal direction, a radial direction extended from an axial centerline, and a circumferential direction. The gas turbine engine includes a compressor section, a combustion section, and a turbine section in serial flow arrangement along the longitudinal direction. The gas turbine engine includes a low speed turbine rotor including a hub extended along the longitudinal direction and radially within the combustion section; a high speed turbine rotor including a high pressure (HP) shaft coupling the high speed turbine rotor to a HP compressor in the compressor section; and a first turbine bearing disposed radially between the hub of the low speed turbine rotor and the HP shaft. The HP shaft extends along the longitudinal direction and radially within the hub of the low speed turbine rotor. The high speed turbine rotor defines a turbine cooling conduit extended within the high speed turbine rotor.

Abstract: A bowed rotor prevention system for a gas turbine engine includes a core turning motor operable to drive rotation of an engine core of the gas turbine engine. The bowed rotor prevention system also includes an auxiliary electric motor control operable to control the core turning motor to drive rotation of the engine core using electric power while a full authority digital engine control that controls operation of the gas turbine engine is either depowered or in a power state that is less than a power level used by the full authority digital engine control in flight operation.

Abstract: A method for operating a supply assembly configured for supplying fuel gas and an inert purge media to a gas turbine combustor, the method including supplying fuel gas in a fuel gas circuit with an upper flow rate; reducing the fuel gas flow rate in the fuel gas circuit from the upper flow rate to a lower flow rate; stopping the supply of the fuel gas in the fuel gas circuit; and starting the supply of the inert purge media in the inert purge media circuit, wherein the starting is performed before the stopping to have a temporary parallel supply of fuel gas and of inert purge media to a fuel distribution system.

Abstract: A heat exchanger array includes a first row of heat exchangers, a second row of heat exchangers, and side curtains. The first row heat exchangers are spaced apart to define first gaps. The second row heat exchangers are spaced apart to define second gaps and are positioned downstream of and staggered from the first row heat exchangers such that the second row heat exchangers are aligned with the first gaps and the first row heat exchangers are aligned with the second gaps. Each side curtain is in close proximity to a first row heat exchanger and a second row heat exchanger. The side curtains define a neck region upstream of and aligned with each first row heat exchanger and each second row heat exchanger. Each neck region has a neck area that is less than a frontal area of the heat exchanger with which it is aligned.

Abstract: A self-contained lubrication fluid circulation system for use with a gas turbine engine defining a core air flowpath includes a sump configured to collect lubrication fluid and a heat source coupled in fluid communication with the sump and configured to transfer heat to the lubrication fluid. The system also includes a heat sink positioned within the sump and coupled in fluid communication with the heat source. A lubrication fluid conduit of the system is configured to channel the lubrication fluid between the heat source and the heat sink, wherein the lubrication fluid conduit is positioned entirely within the sump.

Abstract: Aspects are directed to a system associated with a thrust reverser of an aircraft, comprising: a blocker door and a fan case, where when the thrust reverser is stowed the blocker door is stowed at least in part radially outboard of the fan case. Aspects include a thrust reverser system comprising: a fixed structure, a translating sleeve configured to translate relative to the fixed structure, at least one blocker door pivotally mounted to the translating sleeve, and a rod coupled to the fixed structure and to the at least one blocker door, where during a first phase of thrust reverser deployment the blocker door translates with the translating sleeve when the translating sleeve is translating toward its deployed position and does not rotate, and during a second phase following the first phase, the blocker door pivots relative to the translating sleeve from a stowed position to a deployed position.

Abstract: A method for providing negative control power for an electrical supply and/or transmission network by means of the operation of a gas turbine, includes the following steps: a dynamo-electric machine of the gas turbine is supplied with electric power for motor operation from the supply and/or transmission network; the electrical input power is regulated or controlled by the motor operation on the basis of a network signal from the supply and/or transmission network to which the gas turbine is connected; and an operating parameter of the gas turbine for motor operation is altered as a result of this regulation or control for the purpose of deliberately increasing the electrical input power from the supply and/or transmission network.

Abstract: An integrated inlet particle separator (IPS) blower/engine starter including a housing having an inlet and an outlet. A turbine member is rotatably supported in the housing. A geared member operatively connected to the turbine member extends outward from the housing. The integrated IPS blower/engine starter is operable in a first configuration receiving a first fluid flow to rotate the geared member and in a second configuration generating a fluid flow through powered rotation of the geared member.