Abstract: An oil level regulating apparatus includes a valve unit and a solenoid unit. The valve unit includes a housing having an inflow hole, an outflow hole, and a leak hole, a partition separating the outflow hole and the leak hole, defining a valve chamber close to the outflow hole, and having a partition continuous hole, a valve dividing the valve chamber into an introduction chamber and a pressure chamber and having a valve continuous hole, and a valve biasing member biasing the valve. The solenoid unit has a shaft configured to open and close a leak channel. The shaft can open and close the leak channel on the downstream side of the pressure chamber. When the shaft closes the leak channel, the valve is switched to a closed valve state of closing the outflow hole.

Abstract: A relief device including: an oil pump; an upstream flow passage provided from a discharge section side of the oil pump to an engine; an oil-pressure relief valve relieving oil by a valve body moving due to oil pressure; and a temperature-sensitive relief valve B relieving oil by detecting an oil temperature and opening and closing steplessly. The oil-pressure relief valve and the temperature-sensitive relief valve are disposed in parallel in the upstream flow passage. A portion of the pump housing of the oil pump is formed in an integrated fashion with a casing of an oil circulation mechanism. An oil filter 102 is provided in the upstream flow passage 61, and the temperature-sensitive relief valve B is positioned on the upstream side of the oil filter.

Abstract: A control device for a variable-capacity oil pump provided in an engine using alcohol-containing fuel includes an electronic control unit. The electronic control unit is configured to: (i) estimate an alcohol concentration in oil of the engine, and (ii) correct a capacity of the oil pump to be increased in a correction condition as compared with a case where the correction condition is not established when the correction condition is established. The correction condition is that an estimated alcohol concentration is a predetermined concentration or more and a temperature of the oil is a predetermined temperature or more.

Abstract: The present invention concerns a process for the production of a cylinder oil comprising the steps: providing a used oil, providing a fresh cylinder oil, and blending the used oil with the fresh cylinder oil, wherein the used oil has a lower TBN value than the fresh cylinder oil. The invention further concerns a process for the operation of an internal combustion engine comprising the steps of: preparing a cylinder oil according to a process for the production of a cylinder oil as described herein and using the cylinder oil in the internal combustion engine.

Abstract: A modular assembly having a press-fit fastener hole. The press-fit fastener hole may include a plurality of lobe regions and a plurality of contact regions that may be spaced between lobe regions for a press-fit engagement with a fastener. The fastener may have a first diameter and the contact regions collectively may define an imaginary second diameter that is less than or equal to the first diameter.

Abstract: Disclosed herein is a method and an insert device for an internal combustion engine including: a central exhaust passage; a first expansion chamber in an upstream portion of the exhaust system and in fluidic communication with the central exhaust passage; a second expansion chamber in a downstream portion of the exhaust system and in fluidic communication with the central exhaust passage and the first expansion chamber, forming a continuous expansion chamber throughout a length of the insert device.

Abstract: An internal combustion engine system includes an engine and an aftertreatment system that is connected to the engine to receive exhaust flow from the engine. The aftertreatment system includes a passive storage device for passively storing NOx and/or hydrocarbons produced by the engine during cold start and low temperature operating conditions, and a NOx reduction catalyst downstream of the passive storage device for receiving the NOx released from the passive storage device when temperature conditions in the exhaust flow and/or NOx reduction catalyst are above an effective temperature for NOx reduction. Diagnostics of the passive storage device and/or a sensor downstream of the passive storage device are contemplated that are based at least in part on an expected sensor output in response to a storage mode of operation or a release mode of operation of the passive storage device. Furthermore, reductant injection control is provided in response to a NOx amount released from the passive storage device.

Abstract: A method for heating a device for delivering a liquid additive, the device having at least one pump having at least one pump chamber and at least one movable pump chamber wall, the movable pump chamber wall being displaceable for the delivery of the liquid additive, includes: a) generating a vibration movement by at least one actuator; b) transmitting the vibration movement to the movable pump chamber wall; and c) converting the vibration movement into heat in the movable pump chamber wall.

Abstract: An exhaust gas line section, through which an exhaust gas can flow, includes a flow guiding structure, a feed unit configured to supply a liquid additive to the exhaust gas, and a permeable impingement structure, the flow guiding structure, the feed unit, and the permeable impingement structure being positioned one behind the other in the flow direction. The feed unit and the flow guiding structure are arranged and configured such that an impingement region of the liquid additive on the impingement structure overlaps the center of gravity of a flow distribution of the exhaust gas flowing through the impingement structure.

Abstract: A metering valve having a valve housing, a channel, a valve body that can be moved in order to open and close the metering valve, and a spring, which applies a spring force to the valve body and thus keeps the valve body in a rest position. The spring is supported on at least one calibration body. The valve body, the spring, and the at least one calibration body are arranged in the channel, and the at least one calibration body is supported by a supporting component fastened in the valve housing by a material-bonding connection. A segment of the supporting component protrudes from the valve housing.

Abstract: A method for operating a device for providing a liquid additive having at least one suction point for removing liquid additive from a tank, a valve-free conveying line extending from the suction point to a supply unit, and a valve-free displacement pump, the displacement pump being configured to convey the liquid additive from the tank via the suction point along the conveying line to the supply unit, the displacement unit having at least one seal of the conveying line, displaceable along the conveying line for conveying the liquid additive, includes: a) detecting a stoppage of operation of the device; b) establishing a position of the seal within the positive-displacement pump; and c) changing the position of the seal if the position of the seal does not correspond to a provided park position of the seal.

Abstract: A fluid control valve device includes a seal part disposed to a valve seat of a housing. The seal part is elastically deformable and contacts a valve part when a fluid passage is closed. The seal part has a surface opposing the valve part, a first projection part projected from the surface toward an upper surface of the valve part, and a second projection part defined to surround the first projection part and projected from the surface toward the upper surface of the valve part. The second projection part is adjacent to the upper surface of the valve part than the first projection part is.

Abstract: A dual fuel engine system is provided. The dual fuel engine system includes a dual fuel engine. The dual fuel engine system also includes a turbocharger connected to the dual fuel engine having a turbine portion and a compressor portion. The dual fuel engine system further includes a methane reduction module positioned downstream of the turbocharger. The methane reduction module is configured to receive a flow of exhaust gas from the turbine portion of the turbocharger. The methane reduction module includes a combustor. The methane reduction module is adapted to increase a temperature of the exhaust gas flow received from the turbine portion of the turbocharger. The methane reduction module is also adapted to combust methane constituents present in the exhaust gas based on the increase in the temperature.

Abstract: A honeycomb structure body has main cells having a tubular shape and main cell walls. Each main cell is surrounded by the main cell walls. A virtual base structure body has base cell walls and base cells. The honeycomb structure body has an improved structure obtained by modifying a structure of the virtual base structure body. Each base intersecting point, at which base cell walls intersect, is determined by a polar coordinate (r, ?) using a radius vector r and a deflection angle ?. Each main intersecting point is formed on a polar coordinate (r?, ?) using the deflection angle ? and a main radius vector r? which is obtained by multiplying the radius vector r and a constant magnification without changing the deflection angle ?. A cell density varying section varies its cell density and is formed in at least a part of the honeycomb structure body.

Abstract: An exhaust gas aftertreatment device for an internal combustion engine comprises a housing, first and second catalytic substrates arranged inside the housing such that the first catalytic substrate is arranged upstream of the second catalytic substrate, and a reductant injector arranged in between the first and second catalytic substrates. Further, the first and second catalytic substrates are arranged such that a fluid flow direction through the exhaust gas aftertreatment device is angled. A flow redirecting wall is arranged downstream of the first catalytic substrate such that the fluid flow between the first and second catalytic substrates at least partially passes an outer circumference of the first catalytic substrate before reaching the second catalytic substrate. The redirecting wall is inclined to an outlet surface of the first catalytic substrate and the reductant injector is arranged at the redirecting wall at a position distant from the outlet surface.

Abstract: The disclosure relates to an exhaust gas aftertreatment device for purification of exhaust gas emissions. The exhaust gas aftertreatment device is arranged in an exhaust gas passage subsequently of an internal combustion engine and includes an encapsulating portion, a first catalytic substrate and a second catalytic substrate. The second catalytic substrate may be of SCR type. The exhaust gas aftertreatment device includes a reductant injecting device, a pipe and an obstructing portion, where the reductant injecting device is arranged such that reductant is injectable within the pipe and the exhaust gas flow through the pipe can be controlled by the obstructing portion.

Abstract: A reducing agent tank is provided which enables detachment of a top cover and a heat exchanger while maintaining a long path length of a heat exchanger in a reducing agent tank. A first pipeline and a second pipeline respectively have extension portions which extend from lower ends of a suspended portion along a bottom face toward a side face of a container main body, and rising portions which extend from leading ends of the extension portions along the side face toward an upper face of the container main body. A length of the extension portions along the bottom face is larger than a maximum inside length of an opening. The rising portions and a turning portion form a leading end bent portion, and a rising length of the leading end bent portion is smaller than a minimum inside length passing through a center of the opening.

Abstract: A muffler unit configured to be attached to a vehicle includes a first exhaust pipe. The muffler unit includes a muffler and a second exhaust pipe. The muffler includes a first main body preferably having a tubular shape and including a first support with a first opening and a second support with a second opening, and a first lid. The first and second openings are oriented in a radial direction of the first main body. The second exhaust pipe includes a second main body, a second lid covering a right end of the second main body, and an exhaust inlet disposed in a left end of the second main body. The second exhaust pipe extends into the first and second openings and is supported by the first and second supports. The second main body includes a communication port in communication with an inner space of the first main body.

Abstract: The present invention is configured such that: a cylinder block includes an introducing portion provided at a first side of a cylinder row, cooling liquid being introduced through the introducing portion to a water jacket, a restrictor portion provided in a vicinity of the introducing portion and configured to restrict the cooling liquid, introduced through the introducing portion, from flowing to an intake-side portion of the water jacket, and a discharging portion provided at a middle portion of the cylinder row at an intake side, the cooling liquid being discharged from the water jacket through the discharging portion; and an exhaust-side portion of the water jacket is formed such that a passage cross-sectional area of a cylinder axis direction upper side of the exhaust-side portion is larger than the passage cross-sectional area of a cylinder axis direction lower side of the exhaust-side portion.

Abstract: An MBT ignition time and a knock ignition time are acquired from an engine rotation speed and engine load, and an ignition time on a delay angle side, out of these ignition times, is set as the most advance angle ignition time. An ignition time on the delay angle side only by the KCS learning value with respect to the most advance angle ignition time is set as a required ignition time, and when an actual ignition time set by a knock control system exceeds a predetermined amount and is positioned on the delay angle side with respect to the required ignition time, it is determined that abnormality occurs in an oil jet. Fail-safe processing to the effect that the opening degrees of a throttle valve are corrected to a closed side is executed in response to the abnormality determination.

Abstract: A cooling air bypass is disclosed which prevents premature failure of an engine in the event the cooling air from an external blower is somehow obstructed or shut off.

Abstract: A stratified scavenging two-stroke engine includes a first scavenging passage that extends from a first scavenging intake that opens to the inside of the crankcase to a scavenging port that opens to the inside of a cylinder, and a second scavenging passage that branches from the first scavenging passage and extends to a second scavenging intake that opens to the inside of the crankcase. An air passage is provided to supply air for pre-scavenging into the first scavenging passage at a position closer to the first scavenging intake than a position at which the second scavenging passage branches from the first scavenging passage. A first check valve inhibits a flow of air from the first scavenging passage during an upward stroke of the piston, and a second check valve inhibits a flow of air and a gaseous mixture from the first scavenging passage during a downward stroke of the piston.

Abstract: The object of the invention is to suppress the generation or accumulation of deposits in a compressor of a turbocharger of an engine provided with a blowby gas recirculation device. The invention relates to a cooling device for the turbocharger (60) of the engine (10) provided with the blowby gas recirculation device (50). The cooling device has a cooled air introduction passage (70). The blowby gas recirculation device introduces a blowby gas to an area upstream of the compressor. The cooled air introduction passage introduces a cooled air to a diffuser passage (64) of the compressor. The cooled air introduction passage introduces the cooled air to the diffuser passage in a direction having an acute angle with respect to a flow direction (IA) of the intake air flowing through the diffuser passage.

Abstract: A control arrangement (9) of an exhaust-gas turbocharger (1), having a regulating unit (4) which has a regulating rod (5), and having a guide piece (6) which is connected to a free end region (8) of the regulating rod (5). The free end region (8) is connected to the guide piece (6) by way of a spring clip (10) which engages around the free end region (8) and which is clamped to the guide piece (6).

Abstract: A variable compression ratio internal combustion engine is equipped with a variable compression ratio mechanism that changes an engine compression ratio depending on the rotational position of a first control shaft arranged in an oil pan, and an actuator that changes and holds the rotational position of the first control shaft, and a linking mechanism configured to link the actuator and the first control shaft. The linking mechanism has a lever linked to the first control shaft, and a connecting pin configured to rotatably link the tip of an arm part extending radially outward from the center of the first control shaft and one end of the lever. At least when having been set to the highest compression ratio, the first connecting pin is configured to be submerged below an oil level of the oil pan.

Abstract: The technique disclosed increases the energy conversion efficiency by means of substantial reduction of friction between the cylinder walls and the associated piston rings. The result is achieved by eliminating the unwanted carbonaceous deposits on cylinder walls and associated piston rings by means of vapor nitric acid (HNO3) delivered to the combustion chambers of an engine. Nitric acid is produced by means of chemical reaction between oxygen (O2) and water vapor (H2O) in air and nitric dioxide (NO2) generated throughout an electrical discharge in the air intake path.

Abstract: A turbofan engine includes an engine case, a gaspath through the engine case, a fan having an array of fan blades, a compressor in fluid communication with the fan, a combustor in fluid communication with the compressor, and a turbine in fluid communication with the combustor. The turbine has a fan drive turbine section having 3 to 6 blade stages. A speed reduction mechanism couples the fan drive turbine section to the fan. A ratio of maximum gaspath radius along the low pressure turbine section to maximum radius of the fan blades is less than about 0.55. A bypass area ratio is greater than about 6.0. A ratio of a fan drive turbine section airfoil count to the bypass area ratio is less than about 170 and a second turbine section.

Abstract: A turbofan engine comprises a fan having fan blades. A compressor is in communication with the fan section. The fan is configured to communicate a portion of air into a bypass path defining a bypass area outwardly of the compressor and a portion into the compressor. A bypass ratio is defined as air communicated through the bypass path relative to air communicated to the compressor being greater than about 6.0. A combustor is in fluid communication with the compressor. A turbine is in communication with the combustor. The turbine has a first turbine section that includes two or more stages and a second turbine section that includes at least two stages. A ratio of airfoils in the first turbine section to the bypass ratio is less than about 170. The first turbine section includes a maximum gas path radius. A ratio of the maximum gas path radius to a maximum radius of the fan blades is less than about 0.50. A speed reduction mechanism is coupled to the fan and rotatable by the turbine.

Abstract: A turbofan engine includes an engine case, a gaspath through the engine case, a fan having a circumferential array of fan blades, a compressor in fluid communication with the fan, a combustor in fluid communication with the compressor, and a turbine in fluid communication with the combustor. The turbine has a fan drive turbine section having 3 to 6 blade stages. A speed reduction mechanism couples the fan drive turbine section to the fan. A bypass area ratio is between about 8.0 and about 20.0. A ratio of maximum gaspath radius along the fan drive turbine section to maximum radius of the fan is less than about 0.50. A ratio of a turbine section airfoil count to the bypass area ratio is between about 10 and about 170. The fan drive turbine section airfoil count being the total number of blade airfoils and vane airfoils of the fan drive turbine section.

Abstract: The engine (10) includes a low spool (16) disposed aft of an air inlet (12) and a high spool (34) disposed aft of the low spool (16). An intake reverse-duct (44) is disposed radially outward of the high spool (34) and reverses direction of low pressure compressed air from the low spool (16) into a forward-flow high pressure compressor (40) of the high spool (34). A discharge reverse-manifold (48) directs flow of an exhaust gas stream (50} from a forward-flow low pressure turbine (20) into a rearward-flow direction and into at least one pulse detonation firing tube (54). An annular bypass air duct (72) directs cooling air along the engine (10)—The at least, one firing tube is positioned radially outward of the high spool (34), overlies the high spool (34) and is also positioned within the bypass air duct (72).

Abstract: The present application provides a gas turbine engine. The gas turbine engine may include a compressor, a combustor, a number of auxiliary systems, and a common auxiliary system manifold. The common auxiliary system manifold is in communication with the compressor, the combustor, and the auxiliary systems.

Abstract: Disclosed is a gas turbine engine including a compressor section in communication with a bleed flow path. A rotary valve is provided in communication with the bleed flow path to selectively regulate a flow of fluid within the bleed flow path.

Abstract: A nacelle (N) has a built-in system (10) for anti-icing protection and acoustic absorption and includes a casing or cowling (C), which has a substantially tubular shape and comprises an outer barrel (OB) and an inner barrel (IB), and a coupling edge or lip (L), which is frontally arranged and radially connects said barrels (OB, IB). The system (10) includes a panel structure (12) having electrically conductors (22), which are adapted to generate heat when they are flown through by an electric current, and a sound attenuating layer (18). The inner barrel (IB) houses the system (10).

Abstract: Systems and methods for de-icing a fan of a gas turbine engine are disclosed. The systems and methods may include an electrical coil operatively associated with a first rotating surface of the fan; a magnet operatively associated with a second rotating surface of the fan, the second rotating surface rotating in a direction counter to the first rotating surface, the magnet and the electrical coil thereby producing electricity when the fan is in motion; and a heating element operatively associated with a surface on the fan, the heating element being powered by the electricity produced by the magnet and the electrical coil.

Abstract: A thermal management system for a gas turbine engine includes a heat exchanger in fluid communication with a geared architecture and a heating compartment.

Abstract: A system for preventing objects from entering the intake of a jet engine including a deflector mounted to the turbine shaft and including a de-icing device to minimize collection of ice on the deflector. The deflector includes a sensor in one embodiment for measuring object strikes so that comprehensive impact data may be obtained to generate an impact report so that measures can be taken to minimize object impacts.

Abstract: The present disclosure provides an aircraft nacelle including: an outer aerodynamic wall having an upstream air intake lip; an inner aerodynamic wall, the air intake lip connecting the two outer and inner aerodynamic skins; a front wall arranged downstream of the air intake lip and connecting the two outer and inner aerodynamic skins; and a network for the circulation of a first fluid for cooling a second fluid. The network includes two air/oil-type heat exchangers, one air/air type heat exchanger, an air scoop to collect air from the outside of the nacelle, an orifice to collect cold air, and an outlet orifice to discharge air.

Abstract: An object of the present invention is to spray water uniformly to intake air even during partial operation. An intake-air cooling device is disposed on a rear-stage side of a pre-filter disposed on an intake-air inlet side of an intake-air duct for guiding intake air taken in from an intake-air inlet to a compressor, for cooling the intake air by spraying water to the intake air. The intake-air cooling device includes a plurality of nozzles configured to spray the water to the intake air, a plurality of water conduit pipes including the plurality of nozzles arranged in an axial direction of the water conduit pipes, and a plurality of supply pumps configured to supply the water to corresponding one of the plurality of water conduit pipes. Each of the plurality of water conduit pipes is an endless member which has a different perimeter.

Abstract: The invention relates to a transition piece assembly for a gas turbine. A transition piece having one end adapted for connection to a gas combustor and an opposite end adapted for connection to a first turbine stage. The transition piece having at least one external liner and at least one internal liner. The internal liner forms the hot gas flow channel. A first section of the transition piece assembly upstream of a first turbine stage has a plurality of cooling apertures. Cooling medium through the cooling apertures enters the plenum, which is created between external and internal liners and a cooling medium flows along at least the first section of the transition piece assembly. At least one second section upstream of the first section with respect to the hot gas flow has at least one additional air inlet system.

Abstract: A method and system for a heat exchanger are provided. The heat exchanger includes a plurality of arcuate heat exchanger segments, each including a first header configured to extend circumferentially about at least a portion of a circumference of an internal surface of a fluid duct. The heat exchanger also includes a second header configured to extend circumferentially about the portion spaced axially apart from the first header in a direction opposite of fluid flow through the fluid duct and a first plurality of heat exchanger tubes extending generally axially between the first header and the second header, the first plurality of heat exchanger tubes each including a first flow path separate from a second flow path of any other of the first plurality of heat exchanger tubes, the first flow path changing direction along the flow path from the first header to the second header.

Abstract: Bypass turbojet engine comprising a fan casing (5) at the front and an exhaust casing at the rear, said turbojet engine further comprising a cold stream duct (7) which comprises an annular rear end connected to the exhaust casing and on which is positioned at least one attachment point (4) able to transmit the load from the exhaust casing to the structure of an aircraft, characterized in that a plurality of attachment points (4g, 4d) is positioned on the circumference of said annular rear end of the cold stream duct (7), said plurality of attachment points comprising either two points (4g, 4d) that are diametrically opposed on said circumference or at least three points that form a polygon through which the axis of symmetry of the cold stream duct (7) passes, and in that the turbojet engine is equipped with a rear suspension hoop (8) fixed to said attachment points and able to be fixed to the structure of the aircraft.

Abstract: A hanger includes a connector assembly for coupling the hanger to a first annular duct, a bracket for coupling the hanger to a second annular duct concentrically disposed within the first annular duct, and a cable formed by a plurality of wires bound together that extend from the connector assembly to the bracket. A plurality of circumferentially-spaced hangers placed in tension support an exhaust duct liner relative to an exhaust duct. The hangers permit circumferential and axial displacement at each hanger of the exhaust duct liner relative to the exhaust duct. The displacement of the exhaust duct liner relative to the exhaust duct at each hanger is permitted in a first radial direction that decreases tension in the cable and is restrained in a second radial direction that increases tension in the cable.

Abstract: A system with a gas turbine engine is provided. The gas turbine engine includes a first combustor comprising a first fuel nozzle, a second combustor comprising a second fuel nozzle, and a first fuel pressure oscillation system. The first fuel pressure oscillation system includes a first rotary device coupled to a first fuel circuit. The first fuel circuit is disposed along a first fuel passage leading to the first fuel nozzle. The first rotary device is configured to generate a first fuel pressure oscillation through the first fuel nozzle. The gas turbine engine also includes a second fuel pressure oscillation system having a second rotary device coupled to a second fuel circuit. The second fuel circuit is disposed along a second fuel passage leading to the second fuel nozzle, and the second rotary device is configured to generate a second fuel pressure oscillation through the second fuel nozzle.

Abstract: An exhaust flue (40) includes an exhaust chimney body (43), and an open end multi-hole area (51). The exhaust chimney body (43) is a passage for discharging exhaust gas. The open end multi-hole area (51) is an area in which multiple holes (50) have been opened around the total circumference of an open end (44) of the exhaust chimney body (43). The exhaust flue (40) is capable of minimizing the release of noises with low-frequency components to the outside by means of a simple construction in which holes (50) are opened in the exhaust chimney body (43).

Abstract: In one embodiment, a system includes a drive train starter system. The drive train starter system includes a generator mechanically coupled to a drive train of a gas turbine system and an exciter system electrically coupled to the generator and configured to provide a magnetic field. The drive train starter system additionally includes a load commutated inverter (LCI) electrically coupled to the generator and configured to provide electrical power to the generator and a controller communicatively coupled to the generator, the exciter system, and the LCI. The controller is configured to start up the drive train via the LCI and the generator up to less than a drive train operating speed, wherein the generator is converting electricity into mechanical motion; drive the drive train via a gas turbine up to the drive train operating speed; and to drive the drive train via the generator at the drive train operating speed.

Abstract: A method of determining a duration of a movement of a starter air valve of a turbine engine, the valve for regulating the passage of a flow of pressurised air from upstream to the downstream of pipework, where the downstream side is connected to a pneumatic starter of the turbine engine, the method including determining an instant of initiation and an instant of completion of a movement of the valve during a movement phase of the valve, determining the duration of the movement of the valve, by subtracting the instant of initiation from the instant of completion, calculating a difference between the determined duration of the movement and a theoretical value of the duration.

Abstract: A gas turbine engine comprises a first compressor, a second compressor, a starter generator and a clutch. The starter generator is coupled to the first compressor. The clutch selectively couples the second compressor and the first compressor. The clutch is disposed between a first shaft and a second shaft to engage the first shaft with the second shaft at rest. A flyweight system is engaged with the clutch mechanism to permit freewheeling of the first shaft relative to the second shaft when subject to rotational motion beyond a threshold speed. A method for starting a gas turbine engine comprises engaging a low pressure compressor with a high pressure compressor utilizing a clutch, rotating the low pressure compressor and the high pressure compressor utilizing a starter generator coupled to the low pressure compressor, igniting the gas turbine engine, and disengaging the clutch at an operational speed of the gas turbine engine.

Abstract: A gas turbine engine includes a fan shaft arranged along an engine central axis, a frame supporting the fan shaft, a gear system rotatably coupled with the fan shaft, and a flexible coupling at least partially supporting the gear system. The flexible coupling defines, with respect to the engine central axis, a torsional stiffness TS and a lateral stiffness LS such that a ratio of TS/LS is greater than or equal to about 2.0 to reduce loads on the gear system from misalignment of the gear system with respect to the engine central axis.

Abstract: A gas turbine engine assembly according to an exemplary aspect of the present disclosure includes, among other things, a geared architecture configured to rotatably couple a turbine and a compressor of an engine to rotate the compressor at a different speed than the turbine and a fan.

Abstract: A method and apparatus for local loop closure is provided. The apparatus includes a component for use in a gas turbine engine. The component includes at least one of an actuator and a servo-valve or electric motor, at least one sensor, and an electronic module comprising controller electronics and memory. The electronic module is configured to receive and process commands for the at least one of an actuator and a servo-valve and queue received commands in an input buffer.