Abstract: Conventionally, trim balancing for a power turbine has been performed at the equipment coupling. Disclosed embodiments comprise a hub that is installed on the shaft. This hub enables trim balancing to be performed on the shaft coupling, closer to the rotor, which is more effective. The disclosed hub also enables unbalance corrections to remain with the power turbine after uncoupling. In addition, the use of the hub improves efficiency and eliminates safety risks faced by personnel in the field during coupling of the power turbine to the equipment.

Abstract: A method comprises: flowing a potted component in a liquid state over a tip of an airfoil, the tip of the airfoil having a coating disposed thereon, the coating comprising a metal plating and a plurality of protrusions, each protrusion in the plurality of protrusions extending from the metal plating; allowing the potted component to harden to form a hardened potted component; and removing the hardened potted component from the tip of the airfoil.

Abstract: A test rotor blade includes a blade body and a plug. The blade body extends between and to a leading edge and a trailing edge. The blade body forms a first side surface and a second side surface. The blade body forms a hole. The blade body includes a first side wall and a second side wall. The first side wall extends between and to the hole and the first side surface. The second side wall extends between and to the hole and the second side surface. The plug is disposed within the hole. The plug forms a perimeter surface extending about the axial centerline. The perimeter surface includes a sealing surface portion and a diverging surface portion. The diverging surface portion forms a gap between the plug and the blade body. The gap is disposed between the first side wall and the diverging surface portion.

Abstract: In a method for manufacturing a turbine engine element such as a blade or vane, the element has an airfoil. The method includes: applying a load across an assembly of a first cast portion of the airfoil and a second cast portion of the airfoil; and applying current across a junction of the first cast portion and the second cast portion to fuse the second cast portion to the first cast portion.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed for passive fan blade tip clearance control. A fan blade for a gas turbine engine, the fan blade comprising a fan blade body including a tip region at a blade tip of the fan blade body and a blade tip insert disposed within the tip region of the fan blade body, the blade tip insert is formed from a material that passively adjusts a shape of the blade tip insert to maintain a blade tip clearance between the blade tip and an engine casing or nacelle by at least one of expanding or contracting based on temperature.

Abstract: A turbine blade includes a blade platform, a blade airfoil that extends from the blade platform toward a blade tip, the blade airfoil having a pressure side wall and a suction side wall joined at a blade leading edge and a blade trailing edge, a tip cap surface defined at an end of the blade airfoil facing the blade tip, a squealer tip wall that extends along a portion of the pressure side wall and a portion of the suction side wall from the tip cap surface to the blade tip and from the blade leading edge toward the blade trailing edge, and a chamfered surface formed as a part of the squealer tip wall at a region that is adjacent to the blade trailing edge.

Abstract: A turbine engine airfoil element has a plurality of main body passageways along a camber line and having two or more chordwise distributed protuberant portions with necks between the protuberant portions. A plurality of skin passageways include: at least one first skin passageway each nested between a first of the pressure side and the suction side and two adjacent main body passageways; and a plurality of second skin passageways each nested between first of the pressure side and the suction side and two said protuberant portions of a corresponding main body passageway.

Abstract: A turbine component includes an airfoil, a platform having a cold side, a hot side, a pressure side mate face, a suction side mate face, an upstream side face and a downstream side face with respect to a direction of a working flow. The airfoil is attached to the hot side of the platform. A platform pressure side cooling circuit is formed within the platform and positioned at a pressure side of the airfoil. The platform pressure side cooling circuit includes a plurality of pressures side mate face cooling holes defined at the pressure side mate face. A platform suction side cooling circuit is formed within the platform and positioned at a suction side of the airfoil. The platform suction side cooling circuit includes a plurality of downstream side face cooling holes defined at the downstream side face.

Abstract: A method of assembling a ceramic matrix composite (CMC) component is provided. The method includes assessing which portions of the CMC component require relatively high-temperature capability and which portions require at least one of strength, thickness and increased thermal conductivity, making the portions that require the relatively high temperature capability with chemical vapor infiltration (CVI), making the portions that require the at least one of strength, thickness and increased thermal conductivity with melt infiltration (MI) and combining the portions that require the relatively high temperature capability with the CVI and the portions that require the at least one of strength, thickness and increased thermal conductivity with the MI.

Abstract: A blade includes an airfoil section and a root section that extends in a chord-wise direction between leading and trailing root faces and in a radial direction that is perpendicular to the chord-wise direction from an inner root face to the second end of the airfoil section. The root section defines a dovetail cross-section that is perpendicular to the chord-wise direction. The airfoil section and the root section are comprised of a composite material architecture that includes inter-section fiber plies that each extend from the leading to the trailing edge and from the airfoil section into the root section. Wedges extend in the root section and are interleaved with the inter-section fiber plies. Each of the wedges tapers in the chord-wise direction and the radial direction.

Abstract: A pneumatically variable nozzle vane is disclosed that is capable of performing the same or similar function as a mechanically variable nozzle vane. Within its core, each pneumatically variable nozzle vane may comprise one or more cavities in fluid communication with one or more outlets to eject a gas from the nozzle vane into a flow path of working fluid through the nozzle. Each cavity may be shaped to match an internal pressure gradient to the external pressure gradient of the nozzle vane. The gas may be ejected as a curtain, substantially perpendicular to the flow path through the nozzle, to thereby manipulate the flow of a working fluid through the nozzle in a similar manner as a mechanically variable nozzle vane. In an embodiment, each nozzle vane may have two cavities supplying outlets on both the pressure-side and suction-side of the nozzle vane.

Abstract: A turbine engine is provided that includes a bypass flowpath, a plurality of upstream vanes and a plurality of downstream vanes. The bypass flowpath is fluidly coupled with and downstream of a fan section. The bypass flowpath bypasses a turbine engine core. The upstream vanes are arranged circumferentially about an axis in an upstream vane array. Each of the upstream vanes extends radially across the bypass flowpath. The downstream vanes are arranged circumferentially about the axis in a downstream vane array. The downstream vanes are circumferentially interspersed with the upstream vanes. Each of the downstream vanes extends radially across the bypass flowpath. A first of the downstream vanes is axially offset from a first of the upstream vanes along the axis.

Abstract: Combined cycle gas turbine (CCGT) power plants have become common for generation of electric power due to their high efficiencies. There are various problem related with improving the efficiency of CCGT plants by optimizing the manipulated variables. The method and system for optimizing the operation of a combined cycle gas turbine has been provided. The system is configured to calculate an optimal value of manipulated variables (MV) with efficiency as one of the key performance parameters. The MVs from the existing CCGT automation system, i.e. a first set of manipulated variables and the manipulated variables from the optimization approach, i.e. a second set of manipulated variables are combined to determine an optimal set of manipulated variables. The method further checks for the anomalous behavior of the system and define the root cause of the identified anomaly and the operational state of the CCGT plant.

Abstract: A rotational power plant using a working fluid in a closed-cycle path. The power plant has a single-shaft, compressor and turbine connected together along the path. There is heat source heat exchanger within the path moving from the compressor to the turbine. There is a heat sink and heat exchanger within the path from the turbine to the compressor. There is an Automated Fluid Inventory Management System (AFIMS). The AFIMS includes sensors to measure temperature and pressure of the working fluid at different locations within the path. There is an electronic control unit connected to the AFIMS.

Abstract: A system for readying sub-critical and super-critical steam generator, a servicing method of the sub-critical and the super-critical steam generator and a method of operation of sub-critical and super-critical steam generator is provided. The steam generator includes a first auxiliary heating device disposed on at least one water-steam separator for heating the at least one water-steam separator, and/or a second auxiliary heating device disposed at least on a part of furnace top-end piping for heating the furnace top-end piping. The auxiliary heating devices are heating steam producing components of the steam generator and thus allowing to keep them above the temperature in which materials creating the steam producing components are brittle. The method includes recirculation of the water through the steam generator.

Abstract: A heat engine comprises first and second heat sources; a module alternately displacing thermodynamic fluid between a cold portion and a hot portion connected to the first heat source and the second heat source, respectively, said module comprising a chamber containing the thermodynamic fluid and connected to a supply outlet of thermodynamic fluid, said module comprising a displacer moving in said chamber alternately between the cold and hot portions; a first conversion unit converting a pressure difference of the thermodynamic fluid into mechanical energy, the first conversion unit comprising a circuit including a motor and connected to the supply outlet of the thermodynamic fluid; a first control unit placed in the first conversion unit for controlling the phase of the thermodynamic cycle in said module; and a second control unit of said module controlling the displacement of said displacer alternately between the hot and cold portions.

Abstract: A rocker arm assembly can comprise a main rocker, an auxiliary rocker, and a lost motion spring mounted to press on the main rocker and the auxiliary rocker. The main rocker can comprise a main body surrounding a main rocker bore, a valve end, a main cam end, and a main latch bore between the valve end and the main cam end. The auxiliary rocker can comprise an auxiliary body that is forked. A first auxiliary rocker bore and a second auxiliary rocker bore can flank the main rocker bore. A first auxiliary cam end and a second auxiliary cam end can flank the main cam end. A first auxiliary latch bore and a second auxiliary latch bore can flank the main latch bore. The lost motion spring can span over the main latch bore.

Abstract: A valvetrain assembly comprising a first body and a second body, wherein the second body comprises a first wall and a second wall. The valvetrain assembly further comprises a first latch pin, wherein the first latch pin is configured to latch the second body to the first body and unlatch the second body from the first body. A portion of the first latch pin is located between the first wall and the second wall. The valvetrain assembly also comprises a movable shaft, wherein the movable shaft is configured to move the first latch pin. The valvetrain assembly comprises an electromagnet, wherein the electromagnet is configured to move the movable shaft.

Abstract: A lean-burn internal combustion engine and an exhaust aftertreatment system having an oxidation catalyst are described. A controller determines a fueling rate and a mass flowrate of the exhaust gas feedstream. An inlet temperature of the exhaust gas feedstream upstream of the oxidation catalyst is determined via the first temperature sensor, and an in-use outlet temperature of the exhaust gas feedstream is determined downstream of the oxidation catalyst via the second temperature sensor. An expected outlet temperature from the oxidation catalyst is determined based upon the inlet temperature, the fueling rate, and the mass flowrate of the exhaust gas feedstream. The oxidation catalyst is evaluated based upon the expected outlet temperature and the in-use outlet temperature.

Abstract: An exhaust gas aftertreatment system includes a housing assembly, a first catalyst member, and a second catalyst member. The housing assembly includes an upstream housing, a decomposition housing, a distributing housing, and a catalyst member housing. The upstream housing is centered on an upstream housing axis. The decomposition housing is coupled to the upstream housing and configured to receive exhaust gas from the upstream housing. The distributing housing is coupled to the decomposition housing and configured to receive the exhaust gas from the decomposition housing. The catalyst member housing is coupled to the distributing housing and configured to receive the exhaust gas from the distributing housing. The catalyst member housing is centered on a catalyst member housing axis that is parallel to the upstream housing axis. The first catalyst member extends within the catalyst member housing.

Abstract: An exhaust assembly includes a first tailpipe having an exit end and a curved portion along at least a portion of a length of the first tailpipe. The exhaust assembly further includes a baffle surrounding the first tailpipe at the exit end and defining a plurality of perforations therethrough. The exhaust assembly further includes a pair of shields. Each shield is attached to and at least partially surrounds each of the baffle and the first tailpipe. Each shield extends from a first end proximal to the exit end of the first tailpipe to a second end distal to the exit end of the first tailpipe. Each shield engages the baffle at the first end and engages the first tailpipe at least at or proximal to the second end. The pair of shields is adapted to allow fluid flow to or from the plurality of perforations of the baffle.

Abstract: The technology disclosed herein provides a particulate filter that can appropriately avoid PM from passing toward the outlet cell and can exhibit an excellent PM capturing performance. The particulate filter 1 disclosed herein includes: an outercoat layer 20 provided on an inlet surface 16a of a partition 16 of a base material 10. The outercoat layer 20 at least includes: a lower layer 22 provided on the inlet surface 16a of the partition 16; and an upper layer 24 provided to cover the lower layer 22. The mean particle diameter of granules contained in the upper layer 24 is higher than the mean particle diameter of granules contained in the lower layer. The mean particle diameter of the granules in the lower layer 22 is from 0.4 ?m to 2.0 ?m inclusive, and the mean particle diameter of the granules in the upper layer 24 is from 2.0 ?m to 7.0 ?m inclusive.

Abstract: A system, method, and apparatus for decreasing harmful emissions is provided. The system includes an aftertreatment system comprising an exhaust conduit that directs exhaust gas from an engine system; a heater coupled to the aftertreatment system and configured to provide heat; and a controller coupled to the heater. The controller is configured to: determine whether the engine system is idling; in response to determining that the engine system is idling, determine whether a conversion efficiency of the engine system is greater than a threshold value; in response to determining that the conversion efficiency is greater than the threshold value, determine whether a temperature regarding the aftertreatment system is greater than a threshold temperature; and in response to determining that the temperature of the aftertreatment system is greater than the threshold temperature, at least one of disable or partially disable the heater.

Abstract: An internal combustion engine includes a cylinder, a piston, a crankshaft, a cylinder igniter, an intake passage, a fuel supplier, an exhaust passage, a catalytic converter disposed in the exhaust passage, an exhaust igniter that is disposed upstream of the catalytic converter in the exhaust passage and s generates a spark in the interior of the exhaust passage, and a controller that controls a preheating process for heating the catalytic converter by controlling supply of the air-fuel mixture to the exhaust passage and ignition of the air-fuel mixture by the exhaust igniter. The internal volume of the exhaust passage from the cylinder to an installation position of the exhaust igniter is equal to or less than a volume of the air-fuel mixture discharged from the cylinder in one exhaust stroke in the exhaust passage.

Abstract: A heat sink can be coupled to an exhaust pipe of an internal combustion engine to cool the exhaust gas and thereby increase the efficiency of the internal combustion engine. The heat sink can include a plurality of heat transfer projections extending outward from the exhaust pipe. The heat sink is a separate component that is coupled to the exterior of the exhaust pipe.

Abstract: An outboard motor includes a bracket, an upper case, a lower case, a drive shaft, a propeller shaft, a cooling water passage, a water pump, and an electric motor. The outboard motor is attached to a watercraft via the bracket. The upper case is below the engine. The lower case is below the upper case. The drive shaft is in the upper case and the lower case. The propeller shaft is connected to the drive shaft. The propeller shaft is in the lower case. The cooling water passage is connected to the engine. The cooling water passage is in the upper case and the lower case. The water pump is below a lower end of the bracket to deliver cooling water to the engine through the cooling water passage. The electric motor is operable to drive the water pump.

Abstract: Provided is a thermostat device in which the direction of a radiator-side pipe can be easily changed and which can suppress cost. A housing includes a first housing member having a radiator-side pipe and a second housing member that is rotation-fastened to the first housing member by a bayonet structure. The bayonet structure has a plurality of claw parts that are formed side by side in a circumferential direction on one of the first and second housing members and a plurality of locking parts that are formed on the other of the first housing member and the second housing member and with which the claw parts engage. The radiator-side pipe, when seen from one side of a rotational axis X during the fastening of the first and second housing member, is inclined with respect to the rotational axis X.

Abstract: System and methods for an internal combustion engine are described. In one example, the internal combustion engine may be a boosted internal combustion engine that includes an igniter that is at least partially positioned in a cylinder of the internal combustion engine. The igniter includes an orifice that is configured to release exhaust from a pre-chamber of the igniter.

Abstract: A forced induction device for an internal combustion engine includes a compressor operable to provide compressed air, an intake line configured to supply an intake manifold of the internal combustion engine with the compressed air provided by the compressor, a turbine configured to generate mechanical power through expansion of at least a portion of exhaust gases of the internal combustion engine, an exhaust line configured to supply the turbine with the exhaust gas portion coming from an exhaust manifold of the internal combustion engine, characterized by further comprising a hydrostatic transmission configured to drive the compressor by means of the mechanical power generated by the turbine.

Abstract: A free-piston linear generator wherein the piston is a magnet propelled into reciprocating motion inside a non-conducting cylinder around which is wrapped one or more induction coils. The magnet-piston may be propelled into motion using either internal combustion of a diesel aerosol in a two-stroke or 4-stroke configuration, with ignition provided by compression, or by steam pressure provided by an external boiler. Sensor-controlled exhaust, fuel-intake, and air-intake valves are located at either end of the cylinder, although only a single intake valve would be required in a steam version. As the magnet-piston moves in the cylinder, the power stroke on one side of the magnet-piston is the compression stroke on the other side. The movement of the magnet-piston induces an electric current in the induction coil, by which energy is drawn from the engine as useful work.

Abstract: A system including: (i) a pumped-heat energy storage system (“PHES system”), wherein the PHES system is operable in a charge mode to convert electricity into stored thermal energy in a hot thermal storage (“HTS”) medium; (ii) an electric heater in thermal contact with the hot HTS medium, wherein the electric heater is operable to heat the hot HTS medium above a temperature achievable by transferring heat from a working fluid to a warm HTS medium in a thermodynamic cycle.

Abstract: A method of distributing power within a gas turbine engine is disclosed. In various embodiments, the method includes driving a high pressure turbine having a first stage and a second stage with an exhaust stream from a combustor, the first stage connected to a high pressure turbine first stage spool and the second stage connected to a high pressure turbine second stage spool; driving a high pressure compressor connected to a high pressure compressor spool via a differential system, the differential system having a first stage input gear connected to the high pressure turbine first stage spool, a second stage input gear connected to the high pressure turbine second stage spool and an output gear assembly connected to the high pressure compressor spool; and selectively applying an auxiliary input power into at least one of the high pressure compressor spool and the high pressure turbine.

Abstract: This gas turbine plant is provided with a gas turbine and a fuel supply facility. The fuel supply facility is provided with: a liquid ammonia line; a warm water line through which warm water can flow; a vaporizer which can perform the heat exchange between the warm water coming from the warm water line and liquid ammonia coming from the liquid ammonia line to heat and vaporize the liquid ammonia; a heat exchanger which can perform the heat exchange between the warm water in the warm water line and a medium; a heat exchange amount controller which can control the amount of heat exchange between the warm water and the medium to control the temperature of the warm water flowing into the vaporizer; and a gaseous ammonia line which can introduce gaseous ammonia that is ammonia vaporized by the vaporizer into the gas turbine.

Abstract: A combustion chamber of an aircraft turbomachine having a main axis includes: a body of revolution coaxial with the main axis having a plurality of combustion tubes extending mainly in the direction of the main axis and being distributed in a ring about the main axis; a first perforated rotary disc mounted at a first axial end of the body and rotatable about the main axis to selectively open or close a first end of each of the combustion tubes; and a second perforated rotary disc mounted at a second axial end of the body and rotatable about the main axis to selectively open or close a second end of each of the combustion tubes. The body includes a plurality of cooling segments extending mainly in the direction of the main axis, which are distributed in a ring about the main axis and around the combustion tubes.

Abstract: Systems and methods for carbon dioxide-based energy storage and power generation are described. An example system is presented that includes a compressor operable to receive supercritical carbon dioxide (sCO2) and produce compressed sCO2, one or more thermal energy storage (TES) units operable to heat the compressed sCO2, a turbine operable to receive the heated and compressed sCO2 and output an sCO2 exhaust, and at least one of a generator or a propeller coupled to the turbine, where the generator is operable to produce electricity and the propeller is operable to produce thrust.

Abstract: The present disclosure provides pumped heat energy storage systems that can be used to store and/or extract electrical energy. A pumped heat energy storage system of the present disclosure can store energy by operating as a heat pump, whereby net work input can be used to transfer heat from the cold side to the hot side. A working fluid of the system is capable of efficient heat exchange with heat storage fluids on a hot side of the system and on a cold side of the system. Such pumped energy storage systems can be beneficially integrated with thermal plants to provided heat transfer to and/or from the thermal plants.

Abstract: An energy storage plant includes a casing for the storage of a working fluid different from atmospheric air, in gaseous phase and in pressure equilibrium with the atmosphere; and a tank for the storage of said working fluid in liquid or super-critical phase with a temperature close to the critical temperature. The critical temperature is close to the ambient temperature. The plant is configured to perform a closed cyclic thermodynamic transformation, first in one direction in a charge configuration and then in an opposite direction in a discharge configuration, between said casing and said tank. In the charge configuration the plant stores heat and pressure and in the discharge configuration generates mechanical energy to drive a driven machine.

Abstract: A combined cycle power plant (CCPP) includes a heat recovery steam generator (HRSG) that includes a first economizer and a condensate supply line. The HRSG receives a flow of exhaust gas from the turbine section. The CCPP further includes a fuel heating system that has a fuel supply line and a high temperature heat exchanger. The fuel supply line is fluidly coupled to the combustion section. The high temperature heat exchanger is disposed in thermal communication on the fuel supply line. A high temperature input line fluidly couples the high temperature heat exchanger to the first economizer of the HRSG such that the high temperature heat exchanger receives water from the first economizer. A recirculation line fluidly coupling the high temperature heat exchanger to the condensate supply. A hydro turbine is disposed on the recirculation line.

Abstract: A propulsion system is provided for an aircraft. This propulsion system includes a turbine engine, and the turbine engine includes a propulsor rotor, an engine core and a heat exchanger. The propulsor rotor is configured to rotate about an axis and direct a first air stream along a primary flowpath that bypasses the engine core. The propulsor rotor is configured to direct a second air stream along a secondary flowpath with a geometry extending at least eighty degrees about the axis. The turbine engine is configured such that the first air stream enters the primary flowpath at a first pressure and the second air stream enters the secondary flowpath at a second pressure that is different than the first pressure. The engine core is configured to drive rotation of the propulsor rotor. The heat exchanger is disposed within the secondary flowpath.

Abstract: The invention relates to acoustic management, on an aircraft turbomachine or on a nacelle, via a panel (30,32). On a support (38) is reserved a recess (34), recessed with respect to a surrounding general surface (36) for contact with moving air. The recess (34) is adapted to receive the panel, as another so-called surface for contact with moving air. The support (38) and/or the panel comprise removable connecting elements for, in the recess, mounting the panel removably with respect to the support, the panel being an acoustic panel (30) or a non-acoustic panel (32).

Abstract: A fuel conditioning system includes a heater for selectively adjusting an operating temperature of the fuel and a controller communicatively coupled to the heater. The controller configured to determine a dew point temperature of the fuel and maintain the operating temperature of the fuel at least at the determined dew point temperature of the fuel.

Abstract: A system for energy conversion that includes a propulsion system, a fuel circuit, a combustion device, a turbine, and a load device. The fuel circuit is in fluid communication with a fuel tank and a fuel flow control device that separates a flow of fuel into a first portion and a second portion. The combustion device receives a flow of oxidizer and the second portion of fuel to generate combustion gases. The turbine receives the combustion gases from the combustion device via a fluid circuit. The load device is operably coupled to the turbine via a driveshaft and is configured to receive torque from the driveshaft.

Abstract: The present disclosure provides for improving flame propagation in a combustor, particularly in a combustor for use in a power production system and method. At least one stream being passed into the combustor (e.g., a fuel, an oxidant, a diluent, a coolant, a working fluid, water, or steam) can be independently heated to a temperature that is about the autoignition temperature of the fuel or greater. Further, flame stabilization, including promoting ignition, can be improved as described herein through controlled addition of one or more NOx species into the combustor or combustion chamber.

Abstract: A turbine engine including an engine core, an engine drive shaft, an accessory gear box (AGB), an air turbine starter (ATS) and a bleed air circuit. The engine core has a fan section, a compressor section, a combustion section, and a turbine section in serial flow arrangement. The engine drive shaft operably couples the fan section, the compressor section and the turbine section. The AGB and the ATS are operably coupled to the engine drive shaft.

Abstract: An aircraft turbomachine includes a lubricating circuit notably including a reservoir of lubricating fluid, a pump drawing lubricating fluid from the reservoir to inject it toward several components of the turbomachine, and an intake pipe connecting the reservoir to an intake orifice of the pump, the turbomachine further including a pneumatic starting circuit including a starting tube through which there circulates a flow of compressed air intended to supply a pneumatic starter of the turbomachine, wherein it includes a pneumatic line extending from the starting tube as far as the reservoir so as to supply the reservoir with compressed air so as to cause the lubricating fluid to circulate through the intake pipe towards the pump.

Abstract: A turbine engine that includes an engine core, an inner cowl, an outer cowl and an accessory gearbox. The engine core includes at least a compressor section, a combustion section, and a turbine section in axial flow arrangement. The accessory gearbox is operably coupled to the engine core and includes a first portion and a second portion.

Abstract: The coupling can have a female member having a plurality of female member connections circumferentially arranged along a radially inner face; a male member having a plurality of male member connections circumferentially arranged along a radially outer face; and a coupling member extending annularly around the axis, the coupling member having a strip, the strip having, circumferentially relative the axis, an alternating sequence of outer folds and inner folds, the outer folds connected to the female member via respective ones of the female member connections, the inner folds connected to the male member via respective ones of the male member connections, the inner folds being circumferentially offset from the outer folds in a given angular direction.

Abstract: A reduction gearbox is provided that includes a sun gear, planet gear assemblies, first and second ring gears, and a ring gear positional alignment system. Each planet gear assembly includes a main gear and first and second lateral gears coupled to one another. The ring gear positional alignment system includes a system controller, a ring gear actuator, and a sensor. The ring gear actuator is engaged with the first ring gear and is configured to rotate the first ring gear relative to the second ring gear. The system controller is in communication with the sensor, the ring gear actuator, and a non-transitory memory storing instructions. The instructions when executed cause the system controller to receive and process signals from the sensor relating to the position of the first ring gear, and control the ring gear actuator to selectively position the first ring gear using the signals from the sensor.

Abstract: Gearboxes for aircraft gas turbine engines, in particular arrangements for journal bearings such gearboxes, and related methods of operating such gearboxes and gas turbine engines. A gearbox for an aircraft gas turbine engine includes: a sun gear; a plurality of planet gears surrounding and engaged with the sun gear; and a ring gear surrounding and engaged with the plurality of planet gears, each of the plurality of planet gears being rotatably mounted around a pin of a planet gear carrier with a journal bearing having an internal sliding surface on the planet gear and an external sliding surface on the pin.

Abstract: The present application includes apparatuses and service methods including a valve cover assembly for an internal combustion engine. The valve cover assembly optionally including: a valve cover; a base extension coupled to the valve cover and having a recess that receives at least a portion of a rocker arm therein; and a grommet coupled to at least the base extension, the grommet having one or more openings for passage of one or more fuel tubes into the recess to deliver one or more fuels to a fuel injector. The at least one of the valve cover and the base extension is removable from the internal combustion engine without disturbing the one or more fuel tubes to provide access to the rocker arm for performing a valve lash adjustment thereon.