46th week of 2016 patent applcation highlights part 29 |
Patent application number | Title | Published |
20160333705 | COMBINATION OF BLADE TIP CLADDING AND EROSION-RESISTANT LAYER AND METHOD FOR THE PRODUCTION THEREOF - A method for producing a blade for a turbomachine, the blade having a blade tip cladding on its blade tip and an erosion-resistant layer at least on its blade airfoil, wherein firstly a blade tip cladding is applied on the blade tip, subsequently a poorly adhering sublayer is deposited on the blade tip cladding, and then the erosion-resistant layer is produced on the poorly adhering sublayer and the blade airfoil, the poorly adhering sublayer being removed again together with the erosion-resistant layer following completion of the erosion-resistant layer. The invention also relates to a blade for a turbomachine, the blade having a blade tip cladding on its blade tip and an erosion-resistant layer at least on its blade airfoil. The blade tip cladding comprises a metal matrix with incorporated hard material particles and an oxide layer arranged on the metal matrix. | 2016-11-17 |
20160333706 | MASKING METHOD FOR PRODUCING A COMBINATION OF BLADE TIP HARDFACING AND EROSION-PROTECTION COATING - A method for manufacturing a blade ( | 2016-11-17 |
20160333707 | TURBO ENGINE ROTOR COMPRISING A BLADE-SHAFT CONNECTION MEANS, AND BLADE FOR SAID ROTOR - In a turbo engine, the rotor includes a shaft, blades, and a shaft-blade connection. The shaft blade connection can be provided as a fir tree connection, having a fir tree blade root and fir tree shaft grooves receiving the blade roots. The blade roots can include lobes, while the grooves can include undercut recesses receiving the lobes. The inclined mating bearing surfaces provided on a shaft post or on a lobe, respectively, are offset with respect to each other in the circumferential direction while partially overlapping. Each bearing surface is tangentially adjoined by a convexly curved end of bedding surface. | 2016-11-17 |
20160333708 | BLADED ROTOR FOR A GAS TURBINE ENGINE - A bladed rotor includes rotor disc having a peripheral region, and a plurality of rotor blades attached to and extending radially outwardly from peripheral region. Each rotor blade has a root portion which is located in a correspondingly shaped axially-extending slot provided in the peripheral region of rotor disc, and the root portion of each blade is axially retained in its respective slot by a plate located axially adjacent the root portion and rotor disc, and which extends circumferentially across respective slot. Retention plate is held in position by seal member having a first surface which engages radially-inwardly directed surface of rotor disc, and second surface which is located radially-outwardly of first surface and engages the retention plate. Seal member has a curved profile in radial cross-section so as to define a concavity located radially between first and second engaging surfaces and which is directed axially towards the rotor disc. | 2016-11-17 |
20160333709 | RADIAL CONTROL SHAFT FOR A DEVICE FOR CONTROLLING THE PITCH OF FAN BLADES OF A TURBINE ENGINE HAVING AN UNDUCTED FAN, AND A METHOD OF MOUNTING SUCH A SHAFT - The invention relates to a radial control shaft ( | 2016-11-17 |
20160333710 | VIBRATION DAMPING FOR STRUCTURAL GUIDE VANES - A stationary guide vane includes a top platform, a bottom platform, and a vane body located between the top platform and the bottom platform. The vane body includes one or more cavities formed on a side wall of the vane body. One or more of the cavities are filled with vibration damping material and a vane cover is bonded to the vane body over the one or more containers. | 2016-11-17 |
20160333711 | FLANGED SPRING GUIDE FOR A FACE SEAL ARRANGEMENT - A spring guide for use in a seal housing including a first body portion, a second body portion, and a flange portion, including a flange width, extending circumferentially between the first body portion and the second body portion. The flange width being less than or equal to approximately 2.1 millimeters. | 2016-11-17 |
20160333712 | CHORDAL SEAL - An airfoil for a gas turbine engine includes a first airfoil. A first chordal seal is located adjacent a first end of the airfoil. A second chordal seal is located adjacent a second end of the airfoil. The first chordal seal includes a first edge parallel to a first edge on the second chordal seal. | 2016-11-17 |
20160333713 | SYSTEM FOR THERMALLY ISOLATING A TURBINE SHROUD - In one aspect the present subject matter is directed to a system for thermally isolating a turbine shroud of a turbine shroud assembly. The system includes a shroud support having an inner surface and a turbine shroud that is connected to the shroud support. The turbine shroud includes a hot side surface that is radially spaced from a back side surface. At least a portion of the back side surface is oriented towards the inner surface of the shroud support. The system further includes a coating that is disposed along the back side surface of the turbine shroud. The coating regulates heat transfer from the turbine shroud to the shroud support or other hardware that may surround or be adjacent to the turbine shroud. | 2016-11-17 |
20160333714 | SEALING STRUCTURE AND ROTARY MACHINE - A sealing structure that seals a clearance between an outer peripheral surface of a rotor and an inner peripheral surface of a stator. The sealing structure includes: a plurality of step portions that are provided on a first surface which is one of the outer peripheral surface of the rotor and the inner peripheral surface of the stator so as to be arranged in the axial direction, and that protrude from the first surface toward a second surface which is the other of the outer peripheral surface of the rotor and the inner peripheral surface of the stator; and a seal fin that is provided on the second surface, and that forms a small clearance between a corresponding peripheral surface of the step portions. A portion in the vicinity of a tip of the seal fin in the radial direction is inclined toward the upstream side. | 2016-11-17 |
20160333715 | RETENTION CLIP FOR A BLADE OUTER AIR SEAL - One exemplary embodiment of this disclosure relates to a system having a static segment with a circumferentially extending slot. The system further includes a retention clip partially received in the slot, and partially contacting a circumferential end of the static segment. | 2016-11-17 |
20160333716 | BLADE OUTER AIR SEAL MOUNT - The present disclosure relates generally to blade outer air seal section mount including a resilient spring element that acts to provide re-centering forces to the blade outer air seal section when non-uniform forces applied to the blade outer air seal section causing it to move away from its nominal position. | 2016-11-17 |
20160333717 | NEAR NET SHAPE ABRADABLE SEAL MANUFACTURING METHOD - A method of manufacturing a net shaped seal comprises depositing a first layer of fine powder comprising an abradable feed stock material on a substrate. The method includes guiding a heat source over the fine powder material layer; fusing together the fine powder material; depositing a second layer of fine powder material over the first layer; fusing the second layer of fine powder material with a second pass of the heat source at predetermined locations; and repeating the depositing step and fusing step to form subsequent layers to form an abradable seal on the substrate. | 2016-11-17 |
20160333718 | COMPOSITE KEYSTONED BLADE TRACK - A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track. | 2016-11-17 |
20160333719 | METHOD OF MAKING A TURBINE SHROUD - A method of making a shroud assembly by: forming a shroud frame consisting of a one-piece hook and rail assembly which includes a first rail and a second rail disposed at lateral edges and a first support and a second support connected to the first rail and the second rail, the first and second rails and the first and second supports being integrally joined to one another and defining a central aperture therebetween; joining a metallic backsheet to the shroud frame covering the central aperture; and attaching a honeycomb rubs strip to the metallic backsheet via an upper edge of the honeycomb seal structure. | 2016-11-17 |
20160333720 | FLEXIBLE SMALL CAVITY SEAL FOR GAS TURBINE ENGINES - A seal assembly, comprising a first segment, a second segment, and a seal incorporated between the first segment and the second segment, the seal comprising a mesh. The first segment may comprise a blade outer air seal and the second segment may comprise a vane. In various embodiments, the first segment and the second segment may define a gap, and the seal may seal the gap. The seal may have a first member and a second member that enmeshes the first member. The seal may comprise a member that enmeshes a non-metallic member. The seal may comprise a ceramic fiber enmeshed by a member. The seal may comprise a non-metallic member enmeshed by a metallic member. The seal may comprise a plurality of annular connecting members, each annular connecting member extending about the seal. The seal may comprise a single annular member. | 2016-11-17 |
20160333721 | CAM-FOLLOWER ACTIVE CLEARANCE CONTROL - A blade outer air seal (BOAS) assembly is provided. The BOAS assembly may comprise an outer case, a first support arm, a second support arm, a control rod, a blade outer air seal (BOAS), and a unison ring. The unison ring may be located radially inward of the outer case and in mechanical communication with the control rod. The BOAS may be configured to expand or contract in response to a rotation of the control rod. The first support arm may be fixed to the outer case. The second support arm may be fixed to the outer case. The control rod may be coupled to the first support arm and the second support arm, wherein the control rod may be configured to rotate about a control rod axis. The BOAS may comprise a first segment and a second segment. | 2016-11-17 |
20160333722 | INTERSHAFT INTEGRATED SEAL AND LOCK-NUT - An intershaft integrated seal and lock-nut assembly includes spaced apart forward and aft shafts, forward lock-nut threaded onto aft end of forward shaft, aft lock-nut threaded onto a forward end of aft shaft, and seal ring sealingly engaging and disposed between forward and aft lock-nuts operable to seal annular gap between forward and aft shafts. Seal ring may be disposed in annular ring groove extending radially inwardly into one of forward and aft lock-nuts and annular cylindrical inner surface on other one of lock-nuts operable to seal against seal ring. Seal ring may be carbon seal ring and split. Aft lock-nut may include forwardly extending annular arm having annular cylindrical inner surface. Retention tabbed rings may engage lock-nuts and shafts and snap rings may engage retention tabbed rings and lock-nuts. Seal ring may be in ring groove in aft lock-nut. | 2016-11-17 |
20160333723 | DRAIN FOR A PRESSURE SENSING LINE - The invention provides a drain to allow water to flow out of a pressure sensing line. The drain comprises a tube including a plurality of restrictors in flow series, each restrictor comprising a constriction whose internal diameter is less than the internal diameter of the tube. | 2016-11-17 |
20160333724 | DRAIN FOR A PRESSURE SENSING LINE - A drain includes a vortex throttle, to remove water from a pressure sensing line. The vortex throttle resists the flow of air through it. Therefore, for a given diameter of inlet and outlet ports the mass flow rate through the vortex throttle is much smaller than through a plain hole of the same diameter. The inlet and outlet ports may therefore be made larger than in known arrangements (so reducing the risk of blockage), but the operation of the vortex throttle restricts the mass flow of air through the drain pipe (so minimising the detrimental effects on the engine's operation). Collected water effectively drains from the pressure sensing line, without the disadvantages of known arrangements. | 2016-11-17 |
20160333725 | COMPOSITE WEAR PAD FOR EXHAUST NOZZLE - A composite wear pad for being coupled to a slider block of a convergent nozzle of a gas turbine engine includes a high heat capacity composite having a resin and a plurality of carbon fibers bonded together by the resin. The composite wear pad also includes a first rod coupled to the high heat capacity composite at a first axial end of the composite wear pad such that a first end thickness. The composite wear pad also includes a second rod coupled to the high heat capacity composite at a second axial end of the composite wear pad such that the first axial end and the second axial end of the composite wear pad each have an end thickness that is greater than a middle thickness of the composite wear pad. | 2016-11-17 |
20160333726 | VANE STRUT POSITIONING AND SECURING SYSTEMS - A strut-flap vane system for a turbomachine includes a vane strut comprising an airfoil portion and a strut mount extending in a radially outward direction from the airfoil portion. The strut mount forms a hollow semi-cylinder and includes threading on an outer diameter thereof. The system includes an aft mount portion or portions defining a hollow semi-cylinder configured to form a strut cylinder with the strut mount such that the aft mount portion can be disposed in contact with the strut mount to form the strut cylinder. The strut cylinder defines a cylinder opening and the aft mount portion includes threading on an outer diameter thereof that aligns with the threading of the strut mount to allow a strut spanner nut to mesh with both the strut mount and the mount portion. | 2016-11-17 |
20160333727 | VANE STRUT POSITIONING AND SECURING SYSTEMS INCLUDING LOCKING WASHERS - A vane strut positioning and securement system includes a housing including a washer aperture defined in an inner diameter thereof and a lock washer disposed within the washer aperture of the housing, the lock washer configured to lock a vane strut orientation under compression against a vane strut washer. The washer aperture is defined partially through a thickness of the housing, and the housing includes a strut post opening defined through the housing from the inner diameter to an outer diameter of the housing. | 2016-11-17 |
20160333728 | NACELLE VENTILATION MANIFOLD - A gas turbine engine comprises a core engine housing. A nacelle is positioned radially outwardly of the core engine housing. An outer bypass housing is positioned outwardly of the nacelle. There is at least one accessory to be cooled positioned in a chamber radially between the core engine housing and the nacelle. A manifold delivers cooling air into the chamber, and extends ng circumferentially about a central axis of the core engine. The nacelle has an asymmetric flow cross-section across a circumferential extent. | 2016-11-17 |
20160333729 | TURBINE ENGINE HAVING VARIABLE PITCH OUTLET GUIDE VANES - A gas turbine engine including a core engine and a fan configured in mechanical communication with the core engine is provided. The gas turbine engine also includes a plurality of outlet guide vanes positioned downstream from the fan along an axial direction defined by the gas turbine engine. The plurality of outlet guide vanes extend outwardly from an outer casing the core engine generally along the radial direction defined by the gas turbine engine. Each outlet guide vane defines a center of pressure and a pitch axis. The pitch axis of each outlet guide vane is positioned forward the center of pressure of each outlet guide vane such that in the event of a mechanical failure, the outlet guide vane defaults to a neutral position. | 2016-11-17 |
20160333730 | AUTOMATED PROPELLER FEATHER TESTING - There is described herein the automation of propeller feather testing functions, whereby the test is automatically performed and a pass/fail signal is issued upon completion. | 2016-11-17 |
20160333731 | METHOD FOR OPERATING A GAS TURBINE AT PART LOAD - The invention refers to a method for controlling part load operation of a gas turbine comprising a controller wherein a load set point of the controller is greater or equal a minimum load set point. The minimum load set point depends on a hot gas temperature that is calculated based on a hot gas temperature model. | 2016-11-17 |
20160333732 | DEVICE AND METHOD FOR CLEANING THE CORE ENGINE OF A JET ENGINE - The object of the invention is a device for cleaning the core engine of a jet engine, having a supply unit, which provides the cleaning medium, a nozzle unit, which is configured for feeding the cleaning medium into the core engine, and a line connection between the supply unit and the nozzle unit. The invention provides that the nozzle unit has a means for the rotationally fixed connection to the fan shaft of the jet engine, and that a rotary coupling is provided between the nozzle unit and the line connection. The object of the invention is further an arrangement of such a device and a turbo fan jet engine, and a method for cleaning the core engine of a jet engine using the device. | 2016-11-17 |
20160333733 | Turbine Airfoil With Additive Manufactured Reinforcement of Thermoplastic Body - A component for a gas turbine engine comprises an airfoil body formed of a plastic. A reinforcement portion has webs formed of a metallic material and extend into the airfoil. A gas turbine engine, and a method of forming a component for use in a gas turbine engine are also disclosed. | 2016-11-17 |
20160333734 | IMMERSED CORE FLOW INLET BETWEEN ROTOR BLADE AND STATOR VANE FOR AN UNDUCTED FAN GAS TURBINE - An unducted thrust producing system is provided that can include a rotating element having an axis of rotation about a central longitudinal axis and comprising a plurality of blades attached to a spinner; a stationary element positioned aft of the rotating element; and an inlet positioned between the rotating element and the stationary element such that the inlet passes radially inward of the stationary element. The rotating element defines an annular valley positioned between a first annular crown and a second annular crown, and the inlet defines an open area positioned aft of the second annular crown. | 2016-11-17 |
20160333735 | ANGLED IMPINGEMENT INSERTS WITH COOLING FEATURES - An engine component assembly is provided with an insert having cooling features. The engine component comprises a cooled engine component surface having a flow path on one side thereof and a second component adjacent to the first component. The second component, for example an insert, may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component. The second engine component has a plurality of discrete cooling features disposed on a surface facing the first component and near the plurality of cooling openings. | 2016-11-17 |
20160333736 | ACTIVE SYSTEM FOR BEARING OIL DAMPER SUPPLY AND VIBRATION CONTROL - A bearing damping system includes a pump configured to pump a fluid. The system further includes a variable position valve having a plurality of open positions each configured to generate different pressures in the fluid downstream from the variable position valve. The system also includes a bearing assembly. The bearing assembly includes a bearing housing. The bearing assembly also includes a stationary bearing race positioned within the bearing housing. The bearing assembly also includes a rotating bearing race spaced apart from the stationary bearing race and configured to be attached to a rotating component. A bearing element is disposed between the stationary bearing race and the bearing housing. A fluid compartment is defined by the space between the bearing housing and the stationary race and is configured to receive the fluid from the second conduit. | 2016-11-17 |
20160333737 | Turbocharger with oil-free hydrostatic bearing - A turbocharger for an internal combustion engine, the turbocharger being supported by hydrostatic bearings in both a radial and an axial direction by a compressed air supplied from a compressor of the turbocharger and boosted in pressure by a separate boost pump to a high enough pressure to support the rotor of the turbocharger. | 2016-11-17 |
20160333738 | STEEL SOFT WALL FAN CASE - A steel soft wall fan case assembly according to one embodiment configured with a thin-walled steel support structure shell including a plurality of annular axial walls of thin sheet metal reinforced by a plurality of rings interconnecting axially adjacent annular axial walls. The steel support structure shell is structurally integrated with honeycomb materials and an annular metallic inner wall. A fabric containment layer may be wrapped around one of the annular axial walls of the steel support structure shell. | 2016-11-17 |
20160333739 | TIE ROD CONNECTION FOR MID-TURBINE FRAME - A mid-turbine frame for use in a gas turbine engine comprises at least one vane extending between a vane inner platform and a vane outer platform, and an inner case radially inward of the inner platform. A plurality of tie rods extend from a platform radially inward of the inner case to a radially outer location which is secured by a mount member. The tie rods are secured in the inner case by a forward bolt, and at least one rear bolt, with the forward bolt extending along an axis which is non-parallel to a center axis of the inner case. A gas turbine engine and a method for assembling a mid-turbine frame are also disclosed. | 2016-11-17 |
20160333740 | SHROUD RETENTION SYSTEM WITH KEYED RETENTION CLIPS - A shroud retention system may include a shroud hanger having an outer hanger wall that defines a clip groove including a narrow groove portion and an enlarged groove portion, with the enlarged groove portion defining a radial height that is greater than a radial height of the narrow groove portion. The system may also include a shroud segment having a shroud wall and a retention clip configured to couple the shroud segment to the shroud hanger. The retention clip may include an inner rail, an outer rail and a clip wall extending radially between the inner and outer rails. The inner rail may be configured to extend along an inner surface of the shroud wall. The outer rail may include a narrow rail portion configured to be received within the narrow groove portion and an enlarged rail portion configured to be received within the enlarged groove portion. | 2016-11-17 |
20160333741 | CMC HANGER SLEEVE FOR CMC SHROUD - According to some embodiments, a ceramic matrix composite (CMC) hanger sleeve is provided for retaining a ceramic matrix composite shroud panel. The sleeve may be connected to an upper hanger by a retainer or a casing. The hanger sleeve includes a radially inward opening with a flowpath panel disposed therein. When the CMC flowpath panel is worn due to time, rubs or both, the panel may be replaced without need to replace the entire assembly. | 2016-11-17 |
20160333742 | RAT FRAME FOR A SOFT AIRCRAFT INTERFACE - A mounting frame for a ram air turbine includes a front support block having a top side opposite a bottom side. A rear support block is disposed opposite the front support block, the rear support block also having a top side, and a bottom side. A top plate extends between the front support block and the rear support block, the top plate having a forward end connected to the front support block proximate the top side of the front support block, an aft end connected to the rear support block proximate the top side of the rear support block. A bottom plate extends between the front support and the rear support opposite the top plate. | 2016-11-17 |
20160333743 | GAS TURBINE OPERATION METHOD AND OPERATION CONTROL DEVICE - To remove water accumulated in a cooling air system while preventing performance loss of a gas turbine, the gas turbine is provided with a cooling air system that connects an intermediate stage or the exit of a compressor to a turbine to supply compressed air bled from the compressor to the turbine, a TCA cooler, i.e., a heat exchanger, that cools the compressed air on the route of the cooling air system, and a drain water discharge valve, i.e., a first drain water discharge valve and a second drain water discharge valve disposed downstream of the compressed air of the TCA cooler, wherein at least for a predetermined period of time after a rated speed of the gas turbine at start up has been reached, the drain water discharge valve is set to an open state, and thereafter, the drain water discharge valve is set to a closed state. | 2016-11-17 |
20160333744 | METHOD AND APPARATUS FOR GENERATING ELECTRICITY USING A THERMAL POWER PLANT - A method for generating electricity by means of a thermal power plant and a liquid vaporization apparatus involves producing heat energy by means of the power plant and using the heat energy to vaporize water or to heat water vapor, expanding the water vapor formed in a first turbine and using the first turbine to drive an electricity generator in order to produce electricity, vaporizing liquefied gas coming from a cryogenic storage in order to produce pressurized gas, reheating the pressurized gas with a part of the water vapor intended for the first turbine of the power plant and expanding the pressurized fluid in a second turbine to produce electricity. | 2016-11-17 |
20160333745 | METHOD AND APPARATUS FOR GENERATING ELECTRICITY USING A NUCLEAR POWER PLANT - A method for generating electricity by means of a nuclear power plant and a liquid vaporization apparatus involves producing heat energy by means of the nuclear power plant and using the heat energy to vaporize water or to heat water vapor, expanding the water vapor formed in a first turbine and using the first turbine to drive an electricity generator in order to produce electricity, vaporizing liquefied gas coming from a cryogenic storage in order to produce a pressurized gas, reheating the pressurized gas with a part of the water vapor intended for the first turbine of the power plant and expanding the pressurized fluid in a second turbine to produce electricity. | 2016-11-17 |
20160333746 | PLASMA ASSISTED DIRTY WATER ONCE THROUGH STEAM GENERATION SYSTEM, APPARATUS AND METHOD - A system and method can comprise a heat source, a plasma assisted vitrifier comprising a syphon valve; and a self-cleaning heat exchanger comprising a fired tube side and a water tube side. The self-cleaning heat exchanger can be configured to receive a heat source comprising an oxidized fossil fuel to one of the fire tube side or the water tube side and the self-cleaning heat exchanger can be further configured to receive a dirty water input on the other of the fire tube side and the water tube side to generate a steam. The plasma assisted vitrifier can be configured to process an organic or inorganic solid waste. The syphon valve is configured to assist in generating a reclaimed product, and the plasma assisted vitrifier is further configured to supply a portion of the process heat to the self-cleaning heat exchanger. | 2016-11-17 |
20160333747 | Prime Mover with Recovered Energy Induced Source and Sink Temperature - A system for using recovered energy to increase the source to sink temperature differential for heating and cooling the working fluid of a prime mover, and in particular to a heat of compression braking source and liquefied or solidified air sink. | 2016-11-17 |
20160333748 | METHOD AND A SYSTEM FOR DRIVING A TURBINE - In the method for driving a turbine according to the invention, at the moment of switching the direction of flow from the first tank ( | 2016-11-17 |
20160333749 | CAMSHAFT ADJUSTER AND METHOD FOR OPERATING A CAMSHAFT ADJUSTER - A method for operating a camshaft adjuster, which includes an adjusting transmission with an input shaft, an output shaft connected in a non-rotatable manner with a camshaft, and an adjusting shaft, whereby the adjusting shaft is driven by an actuator, characterized by the fact that the actuator drives the adjusting shaft by overcoming a torque that is dependent on its angular position. | 2016-11-17 |
20160333750 | LOCATOR FOR USE IN A VALVETRAIN OF A CYLINDER HEAD OF AN INTERNAL COMBUSTION ENGINE - A locator for use in a valvetrain of a cylinder head of an internal combustion engine having a valve substantially concentrically aligned with both a valve spring and a support, the support at least partially extending into the valve spring. The locator includes an annulus seat that supports the valve spring. The locator further includes a tapered ring operatively attached to the seat that has a tapered inner surface, for at least partially accommodating the support of the valvetrain therein, and a tapered outer surface, for at least partially engaging and concentrically aligning with the valve spring. The locator also includes a plurality of radially-spaced lobes. The lobes are disposed on the inner surface of the ring and at least partially engage the support such that the locator substantially concentrically aligns the valve spring with the valve and the support. | 2016-11-17 |
20160333751 | Engine Insert and Process for Installing - an engine insert having an insert appendage that projects outwardly from the insert body in a direction away from the seat face, into an engine, such as to form an engine finger void between the appendage and the insert axis, in which engine finger void a finger of engine material may be positioned between the insert appendage and the insert axis. | 2016-11-17 |
20160333752 | SUMP AND AN ENGINE - An engine, for example for use in a marine vessel, comprises an engine superstructure; and an oil sump for collecting oil from the engine superstructure. At a least a first baffle ( | 2016-11-17 |
20160333753 | BLOW-BY GAS PASSAGE STRUCTURE - A blow-by gas passage structure is provided inside a separator chamber that is formed between a cylinder head cover and a baffle plate joined to the cylinder head cover by vibration welding. A first rib is provided on the opposite surface of one member of the cylinder head cover and the baffle plate, while a second rib is provided on the opposite surface of the other member, at positions upstream of the first rib in the flow of the blow-by gas and adjacent a gap formed between the distal end of the first rib and the opposite surface of the other member. The second rib has a height that is equal to or larger than the height of the gap so as to prevent passing of the blow-by gas through the gap. | 2016-11-17 |
20160333754 | Crankcase Ventilation System Heater - A crankcase ventilation system having a heat transfer conduit included therein. The system includes a housing and a crankcase ventilation filter element within the housing, the crankcase ventilation filter element configured to separate oil and oil aerosol from blow-by gases from a crankcase. An oil inlet is configured to receive pressurized oil from a component of an internal combustion engine. The conduit is positioned within the housing. The conduit is positioned along a length of the housing and is configured to carry the pressurized oil from the oil inlet to a component of the crankcase ventilation system. The conduit is configured to transfer thermal energy from the pressurized oil to the housing. An oil outlet is configured to return the pressurized oil to the crankcase. | 2016-11-17 |
20160333755 | OIL SEPARATOR - An oil separator is configured in which oil collecting performance is maintained at a high level even when negative pressure acts on a blow-by gas circulation portion. An oil discharge port for discharging oil collected from oil mist downward is formed in a bottom portion of the blow-by gas circulation portion, in which blow-by gas flows. A concave portion, which suppresses a phenomenon in which an air current spreads along a wall portion when that air current flows upward from the oil discharge port due to the action of negative pressure, is formed in a wall portion that opposes the oil discharge port. | 2016-11-17 |
20160333756 | MUFFLER - A muffler ( | 2016-11-17 |
20160333757 | WATER RECOVERY DEVICE - A water recovery device includes: an exhaust gas pipe that is connected to a combustion device; a water generation unit that generates water by cooling exhaust gas in the exhaust gas pipe to condense water vapor in the exhaust gas; and a water container that stores water generated by the water generation unit. The water generation unit includes: an acoustic-wave generator that generates acoustic waves by absorbing heat from the exhaust gas pipe and giving the heat to working fluid, which transmits acoustic waves by oscillating, to cause the working fluid to oscillate; a transmission pipe that is internally filled with the working fluid and transmits acoustic waves generated by the acoustic-wave generator; and a cold-heat generator that generates cold heat to supply the cold heat to the exhaust gas pipe by receiving acoustic waves transmitted through the transmission pipe and giving heat to the acoustic waves. | 2016-11-17 |
20160333758 | Method and Apparatus for Sizing a Component Shell Having at Least Two Different Diameters - A method and apparatus forms an exhaust component that includes first and second substrates. An outer shell surrounds the first and second substrates. At least one sensor hole is formed in the outer shell at a location between the first and second substrates. A first end of the outer shell is surrounded with a plurality fingers to size the first end around the first substrate to a first diameter. The plurality of fingers includes an extended finger that is longer than the other fingers such that the extended finger at least partially covers the sensor hole during sizing of the first end. A second end of the outer shell is then surrounded by the fingers to size the second end around the second substrate to a second diameter. The extended finger at least partially covers the sensor hole during sizing of the second end. | 2016-11-17 |
20160333759 | METHOD OF OPERATING AN AFTERTREATMENT DEVICE IN AN AUTOMOTIVE SYSTEM - A method of operating an aftertreatment device in an automotive system. The aftertreatment device includes a catalytic element suitable to be crossed by an exhaust gas flow. A selected portion of the catalytic element is warmed-up earlier than the rest of the catalytic element to a temperature higher than or equal to an activation temperature value for activating an exothermic reaction in the exhaust gas flow. | 2016-11-17 |
20160333760 | SYSTEM AND METHOD FOR DETERMINING A PARAMETER INDICATIVE OF AN AMOUNT OF A REDUCING AGENT - A system is provided for determining a parameter indicative of an amount of a reducing agent in a selective catalytic reduction (SCR) module of a vehicle, the system including: the SCR module having at least one passage for transporting a stream of gas and an SCR catalyst for converting NOx emissions, and having an extension in an axial direction, at least one first antenna unit configured to transmit and receive a microwave signal. Moreover, the first antenna unit is arranged outside the SCR module and configured to transmit microwave signals towards the SCR catalyst and to receive a microwave signal reflected within the SCR module. The system further includes processing circuitry connected to the first antenna unit and configured to determine a difference between the transmitted microwave signal and the received reflected microwave signal and to determine a parameter indicative of the amount of a reducing agent in the SCR catalyst based on the determined difference between the transmitted microwave signal and the received reflected microwave signal. Moreover, the invention relates to a method for determining a parameter indicative of an amount of a reducing agent in a system of a vehicle. | 2016-11-17 |
20160333761 | SYSTEMS AND METHODS FOR REGENERATION OF A DIESEL OXIDATION CATALYST IN A DUAL-FUEL ENGINE - A timing-based method for regenerating a DOC included in an aftertreatment system fluidly coupled to a dual-fuel engine comprises performing at least one of the following: a temperature of the DOC is varied while flowing a mixed exhaust gas, which comprises a mixture of a diesel-only exhaust gas and a natural gas exhaust gas, generated by the dual-fuel engine through the DOC; alternately the method includes flowing (a) the mixed exhaust gas generated by the dual-fuel engine and (b) a diesel-only exhaust gas generated by the dual-fuel engine through the DOC. | 2016-11-17 |
20160333762 | ENGINE EXHAUST GAS ADDITIVE STORAGE SYSTEM - System for storing an internal combustion engine exhaust gas liquid additive, the said system comprising a tank for storing the additive and an “immersed” baseplate ( | 2016-11-17 |
20160333763 | EXHAUST EMISSION CONTROL SYSTEM AND PURIFICATION CONTROL DEVICE - An exhaust emission control apparatus is provided with a supply device, a catalyst, and a gas pressure reduction part. The supply device supplies a reducing agent to an exhaust passage. The catalyst purifies an exhaust gas by the use of the reducing agent. The gas pressure reduction part can make a gas pressure near the supply port lower than the gas pressure on the inside of a supply device body. A NOx catalyst adsorbs nitrogen oxide contained in the exhaust. NOx adsorbed by the NOx catalyst is desorbed from the NOx catalyst when the exhaust gas is purified. An ECU estimates an adsorption amount of NOx. Then, the ECU estimates a desorption amount of NOx desorbed from the NOx catalyst on the basis of the estimated adsorption amount of NOx. | 2016-11-17 |
20160333764 | ENGINE APPARATUS - At every ignition cycle, when a duration change amount ΔT30[i] is equal to or less than a reference value ΔT30ref2, a misfire counter Cmf is kept unchanged. When the duration change amount ΔT30[i] is greater than the reference value ΔT30ref2, on the other hand, the misfire counter Cmf is incremented by value 1. A misfire ratio Rmf is set to provide a smaller value when an amount increasing determination flag F[i] is equal to value 1 than a value when the amount increasing determination flag F[i] is equal to value 0. In the case where an ignition counter Ci reaches or exceeds a reference value Ciref, it is determined whether a conversion catalyst is overheated by comparison between the misfire counter Cmf and an accumulated misfire ratio Rmfsum that is an accumulated value of the misfire ratio Rmf. | 2016-11-17 |
20160333765 | PIPE CONNECTION ARRANGEMENT FOR CONNECTING TWO PIPE ENDS, IN PARTICULAR TWO PIPE ENDS ARRANGED IN AN EXHAUST LINE OF A COMBUSTION ENGINE - A pipe connection arrangement for connecting two pipe ends arranged in an exhaust line of a combustion engine, the two pipe ends being aligned axially with respect to one another and/or are spaced apart and, on the outer circumferential surface thereof, each have a raised spherical segment in a ring shape. The spherical segments are accommodated in a connecting pipe which surrounds the pipe ends in an overlapping section such that the circumference of the raised spherical segments rests radially on an inner wall of the connecting pipe in a spherical-segment contact region. | 2016-11-17 |
20160333766 | APPARATUS AND METHOD OF FOR CLEANING A THERMOSTAT IN AN INTERNAL COMBUSTION ENGINE - A thermostat assembly for a marine engine, having a housing with a first bore and a second bore in communication with the first bore. A thermostat mounts within the first bore for movement between an open and a closed position. A plunger removably mounts within the second bore for movement between an extended position for engagement with the thermostat, and a retracted position for disengagement with the thermostat. | 2016-11-17 |
20160333767 | THERMOSTATIC VALVE - Provided herein is a valve with a housing, a thermostatic element of which a first end part of a piston, which axially opposes the end submerged in a thermodilatable material contained in the body of the thermostatic element, is secured to the housing; a return spring; an electrical heating resistance arranged inside the second end part of the piston; electrical connection for feeding the resistance from outside the housing; and a check mechanism for controlling a flow of fluid circulating through the housing, in a direction leading from the first end part towards the second end part of the piston, and connected to the body of the thermostatic element such that the relative movements between the body and the piston, resulting from the dilation and contraction of the thermodilatable material, move the check mechanism in relation to the housing, between closed and open positions affecting the flow of fluid. | 2016-11-17 |
20160333768 | COOLING SYSTEM WITH A COOLANT PUMP FOR AN INTERNAL COMBUSTION ENGINE - A method is disclosed for operating a cooling system with a coolant pump for an internal combustion engine. The coolant pump is operated for a preset period of time after a starting of the internal combustion engine. The cooling system is switched over into a first warming-up operating mode, in which the coolant pump is not operated, in the case that a first warming-up condition is fulfilled. | 2016-11-17 |
20160333769 | COOLING SYSTEM WITH A COOLANT PUMP FOR AN INTERNAL COMBUSTION ENGINE - A method is disclosed for operating a cooling system with a heater and a coolant pump for an internal combustion engine. The cooling system is switched into a predetermined operating mode as a function of a heater request and a temperature. | 2016-11-17 |
20160333770 | RECIPROCATING PISTON INTERNAL COMBUSTION ENGINE, AND METHOD FOR OPERATING A RECIPROCATING PISTON INTERNAL COMBUSTION ENGINE - An internal combustion engine includes a piston reciprocally moving in at least one cylinder. An intake valve controls the supply of fresh air into a power chamber defined within the cylinder by the moving piston. An ancillary chamber is fluidly connected with the power chamber via a flow-through valve. An auxiliary piston is reciprocally movable in the ancillary chamber and determines the volume of the ancillary chamber. A fuel supply valve introduces fuel into the ancillary chamber. The flow-through valve, the fuel supply valve and the auxiliary piston are moved such that no fresh air from the power chamber goes into the ancillary chamber and such that fuel is expelled from the ancillary chamber into the power chamber via the flow-through valve for combustion with fresh air compressed in the power chamber. | 2016-11-17 |
20160333771 | Fuel Combustion System, Nozzle for Prechamber Assembly Having Coolant Passage, and Method of Making Same - A nozzle for a prechamber assembly of an engine includes a nozzle body which is hollow and includes an outer surface, an inner surface, and an orifice surface. The outer surface defines an outer orifice opening, and the inner surface defines an interior chamber and an inner orifice opening. The orifice surface defines an orifice passage extending between, and in communication with, the outer orifice opening and the inner orifice opening. The orifice passage is in communication with the interior chamber via the inner orifice opening. The nozzle body includes a coolant surface which defines a coolant passage within the nozzle body. The coolant surface includes an orifice interface portion disposed adjacent the orifice surface such that the orifice surface and the orifice interface portion of the coolant surface are in heat-transferring relationship with each other. | 2016-11-17 |
20160333772 | TWO-STROKE COMBUSTION ENGINE WITH IMPROVED FLUSHING PERFORMANCE - A combustion engine having a crankcase and a cylinder, wherein a piston is guided to be movable in strokes inside cylinder, piston movably limiting a combustion chamber, and wherein in cylinder at least one transfer port is inserted, which extends between crankcase and combustion chamber, and through which an ignition mixture can flow from crankcase into combustion chamber, and which opens out into combustion chamber in an upper discharge area in such a way that ignition mixture preferably does not reach transfer ports and thus the crankcase, while at the same time a direct connection of crankcase to combustion chamber is maintained via a transfer port, which is as short as possible, it is suggested that at least one storage chamber is provided which is connected to upper discharge area and in which exhaust gas flowing from the combustion chamber into discharge area can be temporarily stored. | 2016-11-17 |
20160333773 | INTERNAL COMBUSTION ENGINE SYSTEM - An internal combustion engine system includes an internal combustion engine, an exhaust system, an exhaust gas recirculation circuit and a turbocharger including a first turbine interacting with a first compressor for charging air to the internal combustion engine. An exhaust gas recirculation passage is arranged to divert exhaust gases from the internal combustion engine upstream the first turbine and to debouch the exhaust gases downstream the first compressor. The internal combustion engine includes a bleed air channel which is located to divert compressed air at a location in or down | 2016-11-17 |
20160333774 | TWIN SCROLL TURBOCHARGER IN A VARIABLE DISPLACEMENT ENGINE - Methods and systems are provided for operating an engine with variable displacement engine (VDE) operation coupled to a twin scroll turbocharger. One method comprises directing exhaust from a first outer cylinder and a first inner cylinder of four cylinders to a first scroll of the twin scroll turbocharger, directing exhaust from a second outer cylinder and a second inner cylinder of the four cylinders to a second scroll of the twin scroll turbocharger, and during a first condition, firing all four cylinders with uneven firing. | 2016-11-17 |
20160333775 | SPARK-IGNITED INTERNAL COMBUSTION ENGINE WITH ELECTRICALLY DRIVABLE EXHAUST GAS TURBOCHARGER, AND METHOD FOR OPERATING AN INTERNAL COMBUSTION ENGINE OF THIS TYPE - The disclosure relates to a spark-ignited charged internal combustion engine coupled to an exhaust gas turbocharger with a compressor mounted on a rotatable shaft, the rotatable shaft coupled to a turbine and to an electric auxiliary drive. The electric auxiliary drive of the exhaust gas turbocharger may be activated to increase rotational speed of the rotatable shaft to drive the compressor to supply boost to the engine. The electric auxiliary drive may be engaged or disengaged from the rotatable shaft, responsive to engine operating conditions, such as engine speed, rotation speed of the rotatable shaft, exhaust volume, and engine boost demand. | 2016-11-17 |
20160333776 | AN INTERNAL COMBUSTION ENGINE - An internal combustion engine including a first set of cylinders includes: a first two-stroke compression cylinder housing a first compression piston connected to a first crank shaft; an intermediate two-stroke compression cylinder housing an intermediate compression piston, wherein the second two-stroke compression cylinder is configured to receive compressed gas from the first two-stroke compression cylinder; and a first four-stroke combustion cylinder housing a first combustion piston, wherein the first four-stroke combustion cylinder is configured to receive compressed gas from the intermediate two-stroke compression cylinder; wherein the internal combustion engine further includes a second set of cylinders including: a second two-stroke compression cylinder housing a second compression piston connected to the first crank shaft, wherein the second two-stroke compression cylinder is configured to provide compressed gas to the intermediate two-stroke compression cylinder; and a second four-stroke combustion cylinder housing a second combustion piston, wherein the second four-stroke combustion cylinder is configured to receive compressed gas from the intermediate two-stroke compression cylinder; wherein each one of the intermediate compression piston and the first and second combustion pistons are connected to a second crank shaft, the second crank shaft being configured to rotate with a speed of at least twice the speed of the first crank shaft. | 2016-11-17 |
20160333777 | BASE-FRAME ASSEMBLY FOR A COMBUSTION ENGINE - A system includes a cast mounting tower having an upper portion configured to support an engine, a generator, or any combination thereof and a plurality of ribs coupled to and supporting the upper portion of the mounting tower. The plurality of ribs extend from the upper portion in a direction crosswise to the upper portion, the upper portion and the plurality of ribs are integrally coupled as a one-piece structure of the cast mounting tower, and the cast mounting tower is configured to couple to a frame. | 2016-11-17 |
20160333778 | AN INTERNAL COMBUSTION ENGINE - An internal combustion engine including a first set of cylinders includes: a first two-stroke compression cylinder housing a first compression piston connected to a first crank shaft; a first four-stroke combustion cylinder housing a first combustion piston connected to a second crank shaft, the first four-stroke combustion cylinder being configured to receive compressed gas from the first two-stroke compression cylinder; and a first two-stroke expansion cylinder housing a first expansion piston connected to the first crank shaft, the first two-stroke expansion cylinder being configured to receive exhaust gas from the first four-stroke combustion cylinder, wherein the first compression piston is positioned to reach a lower end position within the first compression cylinder and the first expansion piston is positioned to reach an upper end position within the first expansion cylinder when the first combustion piston reaches a lower end position within the first combustion cylinder; wherein the second crank shaft is configured to rotate with a speed of at least twice the speed of the first crank shaft. | 2016-11-17 |
20160333779 | CONSTANT-VOLUME COMBUSTION ENGINE - The invention relates to a constant-volume combustion engine ( | 2016-11-17 |
20160333780 | INTERNAL COMBUSTION ENGINE - The internal combustion engine comprises: operating members and operating by a predetermined pressure or more of oil pressure; a hydraulic oil path supplying hydraulic oil to the operating members through crank journals; a lubricating oil path supplying lubricating oil to crankpins through the crank journals; a hydraulic control valve linearly controlling an oil pressure supplied to the operating members due to change of that opening degree; and a control device. The control device controls the opening degree of the hydraulic control valve so that when operating the operating members, the predetermined pressure or more of oil pressure is supplied to the operating members, and controls the opening degree of the hydraulic control valve so that when not operating the operating members, less than the predetermined pressure of oil pressure is supplied to the operating members. | 2016-11-17 |
20160333781 | COMBUSTION STATUS DETECTION DEVICE FOR INTERNAL COMBUSTION ENGINE - A reciprocating internal combustion engine includes an in-cylinder pressure sensor and a crank angle sensor. Data of calculated heat release amount in synchronization with crank angle is calculated using in-cylinder pressure after absolute pressure correction. An amount of heat release amount variation is calculated as a difference between a first calculated heat release amount at a first crank angle on an advanced side of TDC and a second calculated heat release amount at a second crank angle symmetrical about TDC. An actual heat release amount is estimated based on the amount of heat release amount variation calculated using, as the first crank angle, a crank angle on an advanced side of a combustion start point and using, as the second crank angle, a crank angle on a retarded side of a combustion end point. | 2016-11-17 |
20160333782 | MULTIPLE TURBOSHAFT ENGINE CONTROL METHOD AND SYSTEM FOR HELICOPTERS - Electric power from the low spool of a turboshaft engine is transferred to drive the compressor of another turboshaft engine. This is used to assist in maintaining the other turboshaft idling while a single engine provides flight power or to increase acceleration for instance. | 2016-11-17 |
20160333783 | COOLING SYSTEMS FOR GAS TURBINE ENGINES - An air-oil cooler for a gas turbine engine includes an air cooling structure and a lubricant channel. The lubricant channel extends between a lubricant inlet and a lubricant inlet and is bounded by the air cooling structure. The air cooling structure has an arcuate shape for circumferentially spanning a portion of a gas turbine engine core. | 2016-11-17 |
20160333784 | A WALL COOLING ARRANGEMENT FOR A GAS TURBINE ENGINE - A wall arrangement for the main gas path of a gas turbine engine, including: a wall segment which defines the main gas path, the wall segment having a gas path side, an outboard side and a support wall extending from the outboard side towards a supporting structure, and a channel member abutting the support wall and having one or more channels defined by the abutment of the support wall and channel member, the one or more channel having radially separated inlet and outlet. | 2016-11-17 |
20160333785 | SHROUD RETENTION SYSTEM WITH RETENTION SPRINGS - A shroud retention system may generally include a shroud hanger and first and second hooked components extending from an outer hanger wall of the hanger. The first hooked component may include a first wall extending from the outer hanger wall and a first rail extending from the first wall. The second hooked component may include a second wall extending from the outer hanger wall and a second rail extending from the second wall. In addition, the system may also include a shroud segment having a shroud wall configured to be positioned radially between the outer hanger wall and the first and second rails. Moreover, the system may include a retention spring positioned within a radial space defined between the outer hanger wall and the first and second rails that is configured to apply a radial spring force against the shroud segment. | 2016-11-17 |
20160333786 | SYSTEM FOR SUPPORTING ROTOR SHAFTS OF AN INDIRECT DRIVE TURBOFAN ENGINE - In one aspect the present subject matter is directed to a system for supporting shafts of an indirect-drive turbofan engine. The system includes a fan frame assembly that is coaxially aligned with a centerline of the turbofan engine and positioned forward of a reduction gear that couples a low pressure rotor shaft to a fan shaft. A compressor frame assembly is aligned with the centerline aft of the reduction gear and is positioned axially between a low pressure compressor and a high pressure compressor of the turbofan engine. A turbine frame assembly is coaxially aligned with the centerline and is positioned axially between a high pressure turbine and a low pressure turbine of the turbofan engine. The turbine frame assembly rotatably supports an aft end portion of a high pressure rotor shaft and an aft end portion of the low pressure rotor shaft. | 2016-11-17 |
20160333787 | Thermal Adjustment Member for a Fuel Nozzle of a Gas Turbine Engine - A fuel nozzle for use in a gas turbine engine is provided. The fuel nozzle has a fuel nozzle tip with an outer tip housing. The tip housing has a recess formed at an inner surface of the tip housing. A shim is disposed within the recess and a surface of the shim contacts a diaphragm of the fuel nozzle tip. A thermal adjustment member is disposed within the recess against the shim. The tip housing, diaphragm and shim are formed of a base material having a coefficient of thermal expansion (α | 2016-11-17 |
20160333788 | SYSTEM FOR THERMALLY SHIELDING A PORTION OF A GAS TURBINE SHROUD ASSEMBLY - In one aspect the present subject matter is directed to a system for thermally shielding a portion of a shroud assembly for a gas turbine. The system includes a shroud support having a forward wall that includes a front side that is axially spaced from a back side and a radially inner surface that extends axially between the front and back sides. A shroud is mounted to the shroud support. The shroud includes a leading edge portion that extends towards the forward wall of the shroud support and a trailing edge portion that extends towards the aft wall of the shroud support. A radial gap is defined between a top surface of the leading edge portion and the radially inner surface of the forward wall. A thermal shield is disposed along a bottom portion of the forward wall and is oriented to face towards a flow of combustion gases. | 2016-11-17 |
20160333789 | FIRE PROTECTION OF A FAN CASING MADE OF COMPOSITE - Method (S) for protecting against fire a fan casing ( | 2016-11-17 |
20160333790 | ADDITIVE MANUFACTURED NON-ROUND, SEPTUM TIED, CONFORMAL HIGH PRESSURE TUBING - A septum-tied tube pack is provided that includes a first outer wall formed by a multiple of first connected radiuses. A second outer wall is formed by a multiple of second connected radiuses. A first end radius connects the first outer wall and the second outer wall. A second end radius connects the first outer wall and the second outer wall. A multiple of septum elements extend between the first outer wall and the second outer wall. A gas turbine engine is also provided that includes an engine case structure and a fluid conduit mounted to the engine case structure. The fluid conduit includes a septum-tied tube pack section. | 2016-11-17 |
20160333791 | GAS TURBINE ENGINE ACCESSORY ARCHITECTURE - A gas turbine engine comprises a compressor, a combustor and a turbine. A housing for the gas turbine engine includes a mount member to define a vertically upper location. Sides of the engine are defined on opposed sides of the mount, with a fuel filter, a fuel pump and a fuel flow meter being positioned on a first side and an oil pump, an oil filter and an oil tank positioned on a second of the sides. | 2016-11-17 |
20160333792 | ACCESSORY GEARBOX - An accessory gearbox for turbomachine equipment comprising a casing ( | 2016-11-17 |
20160333793 | ACCESSORY GEARBOX ASSEMBLY FOR AN AIRCRAFT TURBINE ENGINE - The invention relates to an accessory gearbox assembly for an aircraft turbine engine including: —a radial drive shaft ( | 2016-11-17 |
20160333794 | SYSTEM AND METHOD FOR FLOW CONTROL IN TURBINE - One embodiment of the present discloses includes a system. The system includes a turbine and a fluid supply system. The turbine includes a main flow path, a plurality of turbine blades disposed along the main flow path, at least one flow control area disposed along the main flow path, and at least one fluid injection port fluidly coupled to the main flow path. The fluid supply system is fluidly coupled to the at least one fluid injection port, wherein the fluid supply system is configured to supply a fluid to the at least one fluid injection port to adjust an effective area of the at least one flow control area. | 2016-11-17 |
20160333795 | COMBINED BUTTERFLY/BALL VALVE - A valve and valve assembly having a hybrid valve member are provided. The valve includes a housing, with an inlet, a primary outlet, and a secondary outlet. The hybrid valve member is rotatably positioned within the housing. The hybrid valve member has a fully closed position wherein the hybrid valve member prevents flow between the inlet and the primary outlet and prevents flow between the inlet and the secondary outlet. The hybrid valve member includes a planar portion and a hemispherical portion on a first side thereof. The planar portion faces the inlet in the fully closed position and the hemispherical portion faces the secondary outlet in the fully closed position. | 2016-11-17 |
20160333796 | Rotor Disk Having a Centripetal Air Collection Device, Compressor Comprising Said Disc and Turbomachine with Such a Compressor - The rotor disk ( | 2016-11-17 |
20160333797 | Adaptive Engine Exhaust Signature Suppressor - An exhaust system has an engine exhaust plane associated with an entrance to the exhaust system, an exhaust exit plane associated with an exit of the exhaust system, a forward cap movable relative to the engine exhaust plane and configured to selectively intersect the engine exhaust plane, and an aft cap movable relative to the exhaust exit plane and configured to selectively intersect the exhaust exit plane. | 2016-11-17 |
20160333798 | METHOD FOR REGULATING A GAS TURBINE - A method for regulating a gas turbine wherein the fuel quantity supplied to the burners of the gas turbine is regulated using a target value for the corrected turbine outlet temperature. A stable operation of the gas turbine is to be allowed with a particularly high degree of efficiency and a high output at the same time. The target value for the corrected turbine outlet temperature is set using a value which characterizes the combustion stability in the burners, wherein the target value for the corrected turbine outlet temperature is set additionally using the surrounding temperature. Furthermore, the target value for the corrected turbine outlet temperature is set only below a specified surrounding temperature using the value which characterizes the combustion stability in the burners. | 2016-11-17 |
20160333799 | METHOD AND SYSTEM FOR OPERATING A CAM-DRIVEN PUMP - A method for automatically operating a cam-driven pump is disclosed. The pump is monitored to determine whether a specified detachment condition or potential detachment of an actuator of the pump from a driving cam is occurring. The pump is operated in a minimal pressure holding mode to provide a minimal pressure within a working chamber of the pump so as to bias the actuator towards the cam if it is determined that the detachment condition is occurring. | 2016-11-17 |
20160333800 | DETECTING ACTUATION OF AIR FLOW CONTROL VALVE OF INTERNAL COMBUSTION ENGINE AND CORRESPONDING CONTROL THEREOF - An air flow velocity calculating device of a internal combustion engine, has a cylinder, a spark plug, an air intake passage, an air flow controlling valve, an air flow velocity calculating portion, and an electric discharge current controlling portion. An electric discharge between a center electrode and a ground electrode is sustained during an electric discharge sustaining period. The electric discharge sustaining period is a period from when the electric discharge begins to when the electric discharge is intercepted by the air flow. Energy is supplied to the spark plug, so that the electric discharge current is sustained at a constant value by the electric discharge current controlling portion during an ignition period. The ignition period is a sum of an electric discharge sustaining period of a first electric discharge and electric discharge sustaining periods of second and subsequent electric discharges in one cycle of the internal combustion engine | 2016-11-17 |
20160333801 | FOUR-CYLINDER ENGINE AND METHOD OF OPERATING FOUR-CYLINDER ENGINE - An engine includes a cylinder body, a cylinder head, and an ignition device including spark plugs. The engine also includes an intake device connected to intake ports, an exhaust device connected to exhaust ports, pistons, and a crankshaft connected to the pistons by connecting rods. Explosion intervals of the cylinders are 270°, 180°, 90°, and 180° as crank angles. The engine further includes a discomfort eliminator which, when the engine speed is lower than a predetermined value, makes the indicated mean effective pressure of at least one of two cylinders having an explosion interval of 90° lower than the indicated mean effective pressures of the other cylinders having an explosion interval of not 90°. The engine causes unequal-interval explosions but produces little change in the driving energy per unit time during an operating state in which an occupant is liable to feel torque fluctuations. | 2016-11-17 |
20160333802 | CONTROL DEVICE FOR INTERNAL COMBUSTION ENGINE - A control device for an internal combustion engine includes an in-cylinder pressure detector, an output shaft torque calculator, a target torque calculator, an input torque parameter calculator, and a controller. The output shaft torque calculator is to calculate an output shaft torque of an output shaft of the internal combustion engine based on an in-cylinder pressure. The target torque calculator is to calculate a target torque of the output shaft torque. The input torque parameter calculator is to calculate an input torque parameter representing an input torque such that the output shaft torque becomes equal to the target torque using a feedback control algorithm which is based on a controlled object model which models a controlled object that receives the input torque parameter as input and produces the output shaft torque as output. The controller is to control the output shaft torque using the input torque parameter. | 2016-11-17 |
20160333803 | SYSTEM AND METHOD FOR DETERMINING AN OIL CONTAMINATION LEVEL OF AN ENGINE BASED ON A SWITCHING PERIOD OF A VALVE LIFT ACTUATOR TO IMPROVE ENGINE STARTUPS - A system according to the principles of the present disclosure includes a switching period module and at least one of a valve lift control module and a start-stop control module. The switching period module determines a switching period that elapses as a valve lift actuator of an engine switches between a first valve lift position and a second valve lift position that is different than the first lift position. The switching period begins when a measured position of the valve lift actuator corresponds to the first lift position and the switching period ends when the measured position of the valve lift actuator corresponds to the second lift position. The valve lift control module controls the valve lift actuator based on the switching period. The start-stop control module determines whether to automatically stop the engine based on the switching period. | 2016-11-17 |
20160333804 | DEVICE AND METHOD FOR CONTROLLING INTERNAL COMBUSTION ENGINE FOR VEHICLE - In a vehicle with an automatic transmission, an internal combustion engine is provided with a variable compression ratio mechanism. A target compression ratio of the variable compression ratio mechanism is determined based on a demand load and an engine rotation speed with reference to a compression ratio map. A reverse-drive compression ratio map is selected when the automatic transmission is in a reverse drive position; a first compression ratio map is selected when an actual speed reduction ratio of the transmission is low; and a second compression ratio map is selected when the actual speed reduction ratio of the transmission is high. A variable control range of the compression ratio is narrower in the second compression ratio map than in the first compression ratio map and is narrower in the reverse-drive compression ratio map than in the first and second compression ratio maps. | 2016-11-17 |