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SOFT ROBOTIC ACTUATORS

Thu, 06 Apr 2017 08:00:00 EDT

A soft robotic device includes a flexible body having a width, a length and a thickness, wherein the thickness is at least 1 mm, the flexible body having at least one channel disposed within the flexible body, the channel defined by upper, lower and side walls, wherein at least one wall is strain limiting; and a pressurizing inlet in fluid communication with the at least one channel, the at least one channel positioned and arranged such that the wall opposite the strain limiting wall preferentially expands when the soft robotic device is pressurized through the inlet.



SYSTEM TO PUMP FLUID AND CONTROL THEREOF

Thu, 06 Apr 2017 08:00:00 EDT

A pump having a fluid driver disposed within the interior volume of the pump and to a method of delivering fluid from an inlet of the pump to an outlet of the pump using the fluid driver. The fluid driver includes a variable-speed and/or a variable torque prime mover and a fluid displacement assembly. The pump can be used in a fluid pumping system to provide fluid to an actuator that is operated by the fluid. At least one of a speed and a torque of the pump is controlled so as to adjust at least one of a flow and a pressure in the fluid pumping system to a desired set point, without the aid of another flow control device.



COMPRESSOR STATOR VANE, AXIAL FLOW COMPRESSOR, AND GAS TURBINE

Thu, 06 Apr 2017 08:00:00 EDT

Within a compressor case, a plurality of stages of high-pressure compressor statorsare disposed alternately with a plurality of stages of high-pressure compressor rotorsalong an axial direction. Each stage of the high-pressure compressor statorsincludes a plurality of compressor stator vanes. Each of the compressor stator vaneshas, on a camber line, a camber reference pointin which (θ−θe)/θk is 50% (θ, θe and θk represents a metal angle, an exit metal angle and a camber angle, respectively). In a vane-shaped cross-section, a distance from a leading edgeto the camber reference pointis set to a 26-38% chord.



Dual Compressor Turbocharger

Thu, 06 Apr 2017 08:00:00 EDT

A dual compressor turbocharger includes two compressors. One compressor supplies fuel pressure, and one compressor supplies air pressure. The dual compressor turbocharger includes a turbine driven by exhaust of an engine and a shaft coupled to the turbine. The first compressor is mounted on the shaft and includes a first inlet coupled to an air supply and a first outlet coupled to an air intake of the engine. The second compressor is mounted on the shaft and includes a second inlet coupled to a fuel supply and a second outlet coupled to a fuel supply rail of the engine.



SOLID PROPELLANT GRAIN

Thu, 06 Apr 2017 08:00:00 EDT

A solid rocket propellant grain having rocket propellant and a membrane in contact with the rocket propellant. The membrane includes a highly heat conductive pattern which affects the propellant burning rate through localized conductive heat transfer from the combustion zone and into the uncombusted propellant. Different geometries for the thermally conductive pattern produce different combustion results.



ENHANCED LIQUID OXYGEN-PROPYLENE ROCKET ENGINE

Thu, 06 Apr 2017 08:00:00 EDT

Provided herein are various improvements to rocket engine components and rocket engine operational techniques. In one example, a rocket engine propellant injection apparatus is provided that includes a manifold formed into a single body by an additive manufacturing process and comprising a fuel cavity and an oxidizer cavity. The manifold also includes one or more propellant feed stubs, the one or more propellant feed stubs protruding from the manifold and formed into the single body of the manifold by the additive manufacturing process, with at least a first stub configured to carry fuel to the fuel cavity and at least a second stub configured to carry oxidizer to the oxidizer cavity. The manifold also includes a plurality of injection features formed by apertures in a face of the manifold, ones of the plurality of injection features configured to inject the fuel and the oxidizer for combustion.



GAS TURBINE EXHAUST HAVING REDUCED JET NOISE

Thu, 06 Apr 2017 08:00:00 EDT

A nacelle exhaust nozzle having a deployable noise-reducing component is described. The noise-reducing component includes an annular perforated sleeve coinciding with the inner nacelle loft line and circumscribing a mixed exhaust gas flow exiting the nacelle. The annular perforated sleeve is radially spaced apart from of a displaceable wall of an inflatable envelope that is displaceable between a deployed position, wherein noise-reduction is active, and a retracted position, wherein noise-reduction is inactive. When the inflatable envelope is pressurized, portions of the displaceable wall project through openings in the perforated sleeve and into the exhaust gas flow to form a rough surface at the loft line which causes a reduction in noise level. The portions of the displaceable wall that project through the openings in the perforated sleeve when the inflatable enveloped is pressurized include a plurality of dimples formed on the inner wall and forming the rough surface.



Exhaust plume cooling using periodic interruption of exhaust gas flow to form ambient air entraining vortices

Thu, 06 Apr 2017 08:00:00 EDT

An exhaust plume cooling device for cooling an exhaust gas plume to reduce deleterious heat effects on impinged and surrounding surfaces. The device is supportable in a position downstream of an exhaust nozzle of an exhaust gas plume-producing engine and configured to periodically interrupt the flow of exhaust gases by injecting fluid into the exhaust plume zone.



SANDWICH STRUCTURE HAVING HINGE ASSEMBLIES FOR ACCOMMODATING DIFFERENTIAL IN-PLANE EXPANSION OF FACE SHEETS

Thu, 06 Apr 2017 08:00:00 EDT

A sandwich structure includes a first skin and a second skin spaced apart from each other and interconnected by a hinge assembly including a first hinge member and a second hinge member. The first hinge member proximal end is coupled to the first skin. The second hinge member proximal end is coupled to the second skin. The first hinge member distal end is coupled to the second member distal end at a member joint. The hinge assembly: prevents movement of the first skin relative to the second skin in an in-plane longitudinal direction of the first skin, allows movement of the first skin relative to the second skin in an in-plane transverse direction of the first skin, and allows movement of the first skin relative to the second skin in an out-of-plane direction that is normal to the in-plane longitudinal direction and the in-plane transverse direction.



THROAT AREA CONTROL SYSTEM

Thu, 06 Apr 2017 08:00:00 EDT

A system includes a combustion chamber that has a throat, and a regulator for changing area cross-sectional area of the throat. The regulator includes a first piston in fluid connection with the combustor, and a second piston that is moveable with the first piston. The second piston at least partially defining the throat.



METHOD FOR CONTROLLING EXHAUST GAS RECIRCULATION SYSTEM OF VEHICLE

Thu, 06 Apr 2017 08:00:00 EDT

A method for controlling an exhaust gas recirculation (EGR) system includes a first step of determining whether the EGR system is in an operation section under an ignition-on state, a second step of calculating a catalyst deterioration index with catalyst deterioration-diagnosing logic in a section that is determined to be the operation section of the EGR system, and for sensing an occurrence of a misfire in an engine with misfire-sensing logic, a third step of deciding whether the catalyst deterioration index is abnormal on a basis of a first predetermined value and whether a frequency of the misfire is abnormal on basis of a preset value for a reference duration, and a fourth step of controlling an opening amount of an EGR valve based on the decision of the abnormality of both the catalyst deterioration index and the misfire frequency.



METHOD FOR CONTROLLING ENGINE SYSTEM

Thu, 06 Apr 2017 08:00:00 EDT

A method for controlling an engine system having a supercharger and a turbocharger includes; an accelerator-pedal-opening-degree determination operation. of determining whether an opening degree of an accelerator pedal detected after an engine starts is a first reference value or more; a first coolant temperature determination operation of determining whether, when the opening degree of the accelerator pedal is less than the first reference value, a detected temperature of a coolant is a second reference value or more; a second coolant temperature determination operation of determining whether the temperature of the coolant is the second reference value or more and is within a temperature threshold; and a boosting operation of calculating boosting contribution rates of the supercharger and the turbocharger, respectively, when the determined temperature of the coolant is within the temperature threshold and driving the supercharger and the turbocharger using the calculated boosting contribution rates.



IMPROVED FUEL INJECTION ARCHITECTURE

Thu, 06 Apr 2017 08:00:00 EDT

The invention relates to a turbine engine fuel injection architecture including: two fuel injection manifolds (30A, 30B), each manifold being suitable for dispensing a fuel flow to at least one associated injector; a main fuel-proportioning device (32) suitable for proportioning a total fuel flow (Q) to be supplied to at least both injection manifolds (30A, 30B); and a distribution proportioning device (31), located between the main fuel-proportioning device (32) and the injection manifolds (30A, 30B) and suitable for distributing at least part of the total fuel flow between both manifolds. The architecture is characterized in that it also includes a bypass valve (35) suitable for discharging a flow from a first manifold (30A, 30B) to a second manifold (30B, 30A), in the event of excess fuel pressure in the first manifold. The invention also relates to a turbine engine combustion assembly including said architecture.



METHOD AND SYSTEM FOR MODULATED TURBINE COOLING

Thu, 06 Apr 2017 08:00:00 EDT

A method of transferring a fluid flow from a static component to a rotor of a gas turbine engine and a modulated flow transfer system are provided. The modulated flow transfer system includes an annular inducer configured to accelerate the fluid flow in a substantially circumferential direction in a direction of rotation of the rotor. The system further includes a first fluid flow supply including a compressor bleed connection, a feed manifold formed of bendable tubing, and a feed header extending between the compressor bleed connection and the feed manifold. The feed header includes a modulating valve configured to control an amount of fluid flow into the feed manifold. The system also includes a flow supply tube that extends between the feed manifold and the inducer and is couplable to at least one of the plurality of first fluid flow inlet openings through a sliding piston seal.



GEAR SYSTEM ARCHITECTURE FOR GAS TURBINE ENGINE

Thu, 06 Apr 2017 08:00:00 EDT

A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.



GEAR SYSTEM ARCHITECTURE FOR GAS TURBINE ENGINE

Thu, 06 Apr 2017 08:00:00 EDT

A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.



TURBOJET ENGINE WITH OFFSET FANS WITH A DIFFERENTIAL SYSTEM

Thu, 06 Apr 2017 08:00:00 EDT

The invention relates to a propulsion unit of an aircraft comprising a turbine (15), at least one fan (10) with an axis offset relative to the axis of the turbine and a power transmission mechanism between the turbine and the fan, characterized in that the power transmission mechanism comprises a speed reducing gear (20) with an input and a movement output, the input being in the extension of the axis (16) of the turbine and the output connected to the fan.



GAS TURBINE GEARBOX INPUT SHAFT

Thu, 06 Apr 2017 08:00:00 EDT

A gas turbine gearbox input shaft including a gear coupling engaged with an engine power gearbox and extending along a central engine axis thereof. The shaft may include a separable tuning segment coaxially joined to the gear coupling, and a spool coupling joined to the separable tuning segment opposite of the gear coupling, the spool coupling being engaged with an engine turbine spool. Methods of using the input shaft are also provided.



INTEGRAL OIL TANK HEAT EXCHANGER

Thu, 06 Apr 2017 08:00:00 EDT

The present innovation relates to a gas turbine engine comprising an engine core with a combustion section, a fuel circuit fluidly coupled to the combustion section, an oil circuit fluidly coupled to the engine core, and an oil heat exchanger comprising a portion of the fuel circuit forming part of the oil circuit.



GEAR SYSTEM ARCHITECTURE FOR GAS TURBINE ENGINE

Thu, 06 Apr 2017 08:00:00 EDT

A fan drive gear system for a gas turbine engine includes a gear system that provides a speed reduction between a fan drive turbine and a fan and a mount flexibly supporting portions of the gear system. A lubrication system supporting the fan drive gear system provides lubricant to the gear system and removes thermal energy produced by the gear system. The lubrication system includes a capacity for removing thermal energy equal to less than about 2% of power input into the gear system.



GAS TURBINE ASSEMBLY

Thu, 06 Apr 2017 08:00:00 EDT

A gas turbine assembly having a first shaft, a first compressor and a first turbine mounted on the first shaft, a combustor between the first compressor and the first turbine and a second shaft and a second turbine mounted on the second shaft, the second turbine having an inlet connected to an outlet of said first turbine. The gas turbine assembly further includes a third shaft on which an upstream compressor is mounted, the upstream compressor having an outlet which is connectable to an inlet of the first compressor.



METHOD OF TESTING A PROPER FUNCTIONING OF A SELECTIVE CATALYTIC REDUCTION SYSTEM

Thu, 06 Apr 2017 08:00:00 EDT

A method and system is disclosed to test for a proper functioning of a selective catalytic reduction system of an internal combustion engine. The engine is operated at idle speed and a functionality check of the pressure sensor is executed. The engine is operated to increase an exhaust gas temperature in the exhaust pipe upstream of the catalyst and a functionality check of the pump is executed. A functionality check of the injector is executed after the functionality check of the pump and once the exhaust gas temperature has reached a predetermined target value thereof. A functionality check of the supply conduit is executed after the functionality check of the injector. The selective catalytic reduction system is identified as functioning properly when all of the functionality checks yields a positive result or malfunctioning when any one of the functionality checks yields a negative result.



EXHAUST PURIFICATION SYSTEM OF INTERNAL COMBUSTION ENGINE

Thu, 06 Apr 2017 08:00:00 EDT

The exhaust purification system comprises a control apparatus performing main feedback control controlling the amount of fed fuel so that the output air-fuel ratio of the upstream side sensor becomes a target value, sub feedback control setting the target air-fuel based on the output air-fuel ratio of the downstream side sensor, main learning control controlling the amount of fed fuel based on a main learning value, and sub learning control controlling the amount of fed fuel based on a sub learning value. The control apparatus performs sub learning promotion control so that the sub learning value easily changes to a suitable value when a sub learning promotion condition, which is satisfied when the absolute values of the main learning value and the sub learning value are respectively predetermined reference absolute values or more and these learning values are opposite in sign, is satisfied.



Apparatus and Method for Detecting Urea Deposit Formation

Thu, 06 Apr 2017 08:00:00 EDT

An apparatus for detecting urea deposits in an exhaust pipe of an internal combustion engine is provided, where the urea is introduced into the exhaust pipe in an aqueous urea solution via a nozzle. The apparatus comprises at least one radiation receiver which, in use, is located within the exhaust pipe downstream of the nozzle. The apparatus further comprises an electronic control unit in communication with the receiver, wherein the receiver communicates radiation data to the control unit which allows the control unit to establish whether deposits have formed within the exhaust pipe. A control valve is also provided which controls flow of the solution to the nozzle in response to signals from the control unit. A method of detecting urea deposits in an exhaust pipe of an internal combustion engine is also provided, as in an automotive vehicle incorporating the aforementioned apparatus.



PASSIVE NOx ADSORBER

Thu, 06 Apr 2017 08:00:00 EDT

A NOx absorber catalyst for treating an exhaust gas from a diesel engine. The NOx absorber catalyst comprises a first NOx absorber material comprising a molecular sieve catalyst, wherein the molecular sieve catalyst comprises a noble metal and a molecular sieve, and wherein the molecular sieve contains the noble metal; a second NOx absorber material comprising palladium (Pd) supported on an oxide of cerium; and a substrate having an inlet end and an outlet end.



EXHAUST SYSTEM COMPRISING A PASSIVE NOX ADSORBER

Thu, 06 Apr 2017 08:00:00 EDT

An exhaust system for treating an exhaust gas produced by a lean burn engine comprising: (i) a NOx absorber catalyst comprising a molecular sieve catalyst disposed on a substrate, wherein the molecular sieve catalyst comprises a noble metal and a molecular sieve, wherein the molecular sieve contains the noble metal; (ii) means for introducing hydrocarbons into the exhaust gas; and (iii) a lean NOx trap; wherein the NOx absorber catalyst is upstream of both the means for introducing hydrocarbons into the exhaust gas and the lean NOx trap.



METHOD FOR STARTING A STEAM TURBINE SYSTEM

Thu, 06 Apr 2017 08:00:00 EDT

A method for starting a steam turbine system having a steam generator, a steam turbine which is connected to the steam generator and includes at least two turbine stages that, at the time of starting the steam turbine system, have different outlet temperatures, a condenser connected to the steam turbine and a consumer driven by the steam turbine, in which the steam generated in the steam generator is used to start the steam turbine, wherein, until the steam generated in the steam generator reaches a predetermined temperature that at least corresponds to the temperature requirement of the turbine stage with the higher outlet temperature, only the turbine stage with the lower outlet temperature is operated, and in that the turbine stage with the higher outlet temperature is brought on-line only once the predetermined temperature has been reached.



EXTRACTING STEAM FROM A TURBINE

Thu, 06 Apr 2017 08:00:00 EDT

A valve assembly for use to regulate a flow of steam in a flowpath of a turbine. The valve assembly can be configured with a body that circumscribes a rotor. The body is disposed upstream of the rotor blades. In one implementation, the body forms an annular ring with a plurality of arcuate segments, each being configured to move independently of the other segments in the ring to change the size of an annular gap between the arcuate segments and the rotor. The size of the annular gap corresponds with flow parameters for working fluid that flows across the rotor and that exits the turbine for use in pre-heaters and like collateral equipment.



FOREIGN SUBSTANCE REMOVAL APPARATUS FOR GAS TURBINE

Thu, 06 Apr 2017 08:00:00 EDT

A foreign substance removal apparatus for a gas turbine includes a combustor casing having a first cooling air passage formed in a tangential direction of a combustor in a gas turbine in order to move cooling air into the combustor, a first foreign substance collection unit disposed on a flow path in the first cooling air passage in order to primarily filter foreign substances contained in the cooling air, a second cooling air passage extending radially toward a turbine blade in a circumferential direction of a torque tube located in the combustor, and a second foreign substance collection unit disposed on a flow path in the second cooling air passage and communicating with the second cooling air passage to secondarily filter foreign substances contained in the cooling air introduced through the first cooling air passage.



Aircraft propulsion system having at least one anti-fire tank

Thu, 06 Apr 2017 08:00:00 EDT

A propulsion system comprising a nacelle substantially tubular around a longitudinal axis, having an inner wall extending from a front to a rear of the nacelle and by an outer wall, external of the inner wall, extending from the front to the rear of the nacelle, a turbojet comprising a fan and situated internally of the inner wall of the nacelle, at least one tank containing an extinguishing fluid, and a network of pipes hydraulically connected to the tank. The propulsion system comprises each tank being located in the nacelle, around the inner wall and internally of the outer wall. Such a propulsion system makes it possible to shift the one or more tanks, which no longer occupy the space at the mast, and makes it possible to carry a large volume of extinguishing fluid so as to be able to accommodate future regulations.



PROPULSION UNIT FOR AN AIRCRAFT

Thu, 06 Apr 2017 08:00:00 EDT

Propulsion unit for an aircraft, comprising a turbine, at least one propeller offset with respect to the turbine, and a power transmission disposed between the turbine and the propeller, the transmission comprising in series two constant velocity joints with a slide connection.