Abstract: An apparatus for engine exhaust sound attenuation includes a housing, a plurality of baffle plates arranged within the housing. The baffle plates are disposed apart from each other to define a plurality of intermediate chambers. The plurality of intermediate chambers includes a first resonant chamber proximate to the outlet chamber, a second resonant chamber proximate to the inlet chamber, a first intermediate chamber proximate to the second resonant chamber, and a second intermediate chamber proximate to the first intermediate chamber and the first resonant chamber. An inlet tube and an outlet tube are included. A first tube directs a flow of exhaust from the inlet chamber to one of the plurality of intermediate chambers via an interior of the first tube. Additionally, a second tube directs the flow of exhaust from a second one of the plurality of intermediate chambers to the outlet chamber via an interior of the second tube.

Abstract: A filter (30) traps particulate matter in an exhaust gas. A filter inlet side pressure sensor (34) is provided in an inlet side of the filter (30). An EGR valve inlet side pressure sensor (22) is provided in an inlet side of an EGR valve (20). A regeneration controller (38C) determines whether or not the filter inlet side pressure sensor (34) is in failure based upon a difference between a pressure value detected by the filter inlet side pressure sensor (34) and a pressure value detected by the EGR valve inlet side pressure sensor (22). When the filter inlet side pressure sensor (34) is in failure, the regeneration controller (38C) performs control of regeneration treatment using a differential pressure calculated based upon a pressure value detected by the EGR valve inlet side pressure sensor (22) and a pressure value detected by the filter outlet side pressure sensor (35).

Abstract: An exhaust passage includes a main passage and bypass passage, a catalyst, an exhaust control valve, and an HC adsorbent in the bypass passage. The exhaust control valve is controlled so that, when a temperature of the catalyst is higher than a predetermined sintering occurrence temperature, the quality of HC desorbed from the HC adsorbent is greater when the air-fuel ratio of the exhaust gas flowing through the upstream exhaust passage portion is a lean air-fuel ratio compared to when it is a stoichiometric air-fuel ratio or rich air-fuel ratio, or the quality of HC desorbed from the HC adsorbent is greater when the air-fuel ratio of the exhaust gas flowing through the upstream exhaust passage portion is a larger lean air-fuel ratio compared to when it is a smaller lean air-fuel ratio.

Abstract: The present inventive concept relates to a vehicle exhaust gas abatement apparatus. The vehicle exhaust gas abatement apparatus includes: an exhaust gas discharging unit having an exhaust gas discharging pass which is formed on one side thereof and along which an exhaust gas generated from an engine of a vehicle is discharged; a catalytic converter connected to a rear end of the exhaust gas discharging unit along a direction in which the exhaust gas is discharged and removing harmful components in the exhaust gas using a catalyst; and a surface combustion unit coupled to one side of the exhaust gas discharging unit and heating an inner portion of the exhaust gas discharging unit so that the exhaust gas is heated to an activation temperature or higher of the catalyst and then arrives at the catalytic converter.

Abstract: The purpose of the present invention is to provide a manufacturing method for an exhaust gas purification device that can uniformly coat a honeycomb substrate with slurry even when using a low viscosity slurry. The present invention pertains to a manufacturing method for an exhaust gas purification device that includes providing a slurry for catalyst layer formation from a shower nozzle onto a honeycomb substrate, coating the honeycomb substrate with the slurry, and firing the honeycomb substrate coated with the slurry, wherein the viscosity of the slurry at a shear rate of 4 s?1 is 800 mPA·s or less, the shower nozzle has a plurality of discharge openings for discharging the slurry, the relationship of the spacing a) of the discharge openings and the diameter b) of the liquid drops formed when starting supply of the slurry is 0.

Abstract: A control device includes a first exhaust temperature calculation part calculating a temperature of exhaust flowing into a PM trapping device as a first exhaust temperature, a second exhaust temperature calculation part calculating a temperature of exhaust flowing out from the PM trapping device as a second exhaust temperature, a rate of change over time calculation part calculating a rate of change over time of the first exhaust temperature and a rate of change over time of the second exhaust temperature, and a judgment part judging if the PM trapping device is in a removed state removed from the exhaust passage based on a difference between the rate of change over time of the first exhaust temperature and the rate of change over time of the second exhaust temperature.

Abstract: The invention relates to a diagnostic method for checking the functionality of a component for the exhaust-gas aftertreatment of an internal combustion engine. For this purpose, in an internal combustion engine, a secondary air supply is provided by means of which an excess of oxygen can be generated in the exhaust gas channel essentially independently of the operating conditions of the internal combustion engine, and wherein said excess of oxygen is utilized for the measurement of an oxygen storage capacity of the component or of a signal change at the component. It is provided that the component is subsequently subjected to a substoichiometric exhaust gas in order that the oxygen release capacity or the signal change upon a change from superstoichiometric exhaust gas to a substoichiometric exhaust gas is also taken into consideration in the diagnosis. The invention also relates to a device for exhaust-gas aftertreatment, which is designed to be able to carry out a method of said type.

Abstract: The invention relates to a sealing gasket, for sealing a connection between an exhaust manifold and a turbine of a vehicle, the sealing gasket comprising two flow passage openings separated by a dividing wall and a first sealing portion extending around the two openings. The sealing gasket includes at least a second sealing portion extending around one of the two openings, and preferably a third sealing portion extending around the other of the two openings.

Abstract: A fluid circuit for a trucking vehicle having a transport refrigeration unit is provided. The fluid circuit includes a first regulator assembly defining a first fuel inlet that is arranged to receive fuel from a first fuel tank and a first fuel outlet that is arranged to provide fuel to a first engine. The first regulator assembly having a first heat exchanger assembly defining a first coolant inlet that is arranged to receive coolant from a cooling system associated with the first engine and a first coolant outlet that is arranged to provide coolant to the cooling system.

Abstract: Systems are provided for a pre-chamber. In one example, a pre-chamber comprises a passage outside of a primary combustion chamber for flowing fuel directly from a fuel injector to an interior volume of the pre-chamber.

Abstract: An exhaust system is provided to an engine having an output shaft extending in a vehicle front-and-rear direction. The system includes an exhaust passage including a first passage part extending forward from a turbine housing of a turbocharger, a fourth passage part extending in the front-and-rear direction below the turbine housing, a second passage part disposed so that it extends vertically and its center axis inclines forward and upward, and a third passage part having a downstream connecting part extending forward from a front end of the fourth passage part, and an upstream connecting part extending forward and upward from an upper part of a front end of the downstream connecting part. The downstream part has, at a lower part of its front end, an attaching part extending downwardly from a lower edge of the upstream part, and to which a sensor or an injector is attached.

Abstract: The disclosure relates to an exhaust gas conduction system for a gasoline engine, comprising an exhaust gas line which can be connected to an exhaust manifold of the gasoline engine, an intake line which can be connected to an intake manifold of the gasoline engine, a charge air compressor which is arranged in the intake line, and a turbine which is arranged in the exhaust gas line. The exhaust gas line has at least one bypass line with a bypass throttle valve, said line branching off from the exhaust gas line upstream of the turbine and branching back into the exhaust gas line at an opening downstream of the turbine. At least one exhaust gas recirculation line with an EGR throttle valve is provided, said line opening into the intake line, wherein the exhaust gas recirculation line branches off from the bypass line at a branch, and the bypass throttle valve is arranged upstream of the branch of the exhaust gas recirculation line.

Abstract: The invention involves a system and method for providing a liquid fuel or a liquid and gaseous fuel to a diesel or Otto cycle engine for operation of the engine. The system includes a primary electronic control module (ECM), which monitors engine sensors and contains a first three-dimensional fuel map for the liquid fuel. A second ECM is connected for bi-directional transfer of information to the first ECM, the second ECM contains a second three-dimensional fuel map for delivery of the gaseous fuel through a secondary gaseous fuel injection assembly. The bi-directional communication between the two ECMs while monitoring the engine sensors allows both ECMs to “learn” an efficient fuel map for delivery of both fuels in the same cycle for improved efficiency, reduction in slip and lower emissions.

Abstract: The invention concerns a flap arrangement 10 for a turbine 2 of an exhaust-gas turbocharger 2, in particular for a wastegate valve of the turbine, having a spindle 100 for rotatable mounting of the flap arrangement 10 in a turbine housing 3, a lever arm 200, the lever arm 200 being coupled to the spindle 100, and a flap plate 300, the flap plate 300 being coupled to the lever arm 200. The flap plate 300 has a flexible part 330 in a radially outer region of the flap plate 300, such that by applying a closing force to the flap arrangement 10 when the flap plate 300 is in contact with a flap seat 500 in the turbine housing 3, elastic and/or plastic deformation of the flexible part 330 of the flap plate 300 can be caused to compensate for thermal deformation of the turbine housing 3, exhaust deposits and/or wear.

Abstract: A flap configuration opens and closes a wastegate channel in a turbine housing of a turbocharger. The flap configuration has a lever element having a through-bore in which a cylindrical bushing is arranged. A flap having a pin is arranged on the lever element such that the pin passes through the bushing. A cover disk is arranged on an opposite side from the flap and has an opening through which the pin of the flap passes. The flap is riveted to the lever element by the pin.

Abstract: An engine system and method of operating the same includes a two stroke engine, an exhaust manifold coupled to the two-stroke engine, a tuned pipe coupled to the exhaust manifold coupled to the exhaust manifold, a stinger pipe coupled to the tuned pipe, a silencer coupled to the tuned pipe and an exhaust pipe, and an exhaust bypass valve. Exhaust gases are directed from the two stroke engine through an exhaust manifold and through a tuned pipe. An opening of the exhaust bypass valve is changed to redirect exhaust gases away from the tuned pipe to change a pressure within the tuned pipe. In response to changing the opening of the exhaust bypass valve, the airflow through the engine is changed.

Abstract: A turbine includes: a turbine impeller; a housing disposed so as to enclose the turbine impeller, and including a scroll passage positioned on an outer circumferential side of the turbine impeller and an inner circumferential wall part defining an inner circumferential boundary of the scroll passage; a plurality of nozzle vanes disposed inside an intermediate flow passage which is positioned, in an exhaust gas flow direction, on a downstream side of the scroll passage and on an upstream side of the turbine impeller; and a plate disposed on a side of the intermediate flow passage with respect to the inner circumferential wall part so as to face the intermediate flow passage such that a gap is formed between the plate and the inner circumferential wall part in an axial direction. The plate has at least one through hole through which the intermediate flow passage and the gap are communicated with each other.

Abstract: An engine having a cylinder fastened to the engine ease with the biconcave internal partition, which divides the cylinder into the upper and bottom parts. Sparking plugs are mounted on both sides of the partition. The upper and the bottom parts of the cylinder have side scavenging channels which connect suction spaces to the working spaces of both parts of the cylinder. The upper and bottom parts of the cylinder have inlet and outlet orifices. Inside the upper and inside the bottom part of the cylinder and the upper and bottom piston are placed respectively, while both pistons are directed towards each other by the working surfaces. The pistons are connected by a rod that is led through the linear bearing that is embedded in the partition forming a seal. The connecting rod is fastened to the bottom piston and by its other end it is connected to the crankshaft.

Abstract: An air supply system for a gas turbine engine including a first duct which is connected or capable of being connected to a first compressor bleed air supply of a gas turbine engine; a second duct which downstream of the first compressor bleed air supply is connected or capable of being connected to a second compressor bleed air supply of the gas turbine engine; a nozzle by way of which air from the second duct is capable of being blown into the first duct; and an exhaust air duct having an opening which downstream of the nozzle is disposed in the first duct in such a manner that air blown by way of the nozzle into the first duct can flow out of the first duct through the opening into the exhaust air duct. A gas turbine engine and an aircraft are furthermore provided.

Abstract: An oil thermal management system for a gas turbine engine includes a control system operable to selectively heat oil in the oil system with the heater system greater than a predetermined temperature prior to engine start. A method of starting a gas turbine engine includes sensing an oil temperature with respect to a predetermined oil temperature for engine start; and heating the oil to the predetermined oil temperature for engine start in response to the oil temperature being less than the predetermined oil temperature.

Abstract: An aircraft turbomachine blade includes an aerodynamic part manufactured in one piece by additive manufacturing, this aerodynamic part including a pressure-side wall, a suction-side wall and an internal fluid passage, this internal fluid passage being crossed by a plurality of disruptive elements that each connect the pressure-side wall to the suction-side wall, being irregularly spaced apart according to varied parameters in a chosen and optimized range, the junction of the disruptive elements with the pressure-side and suction-side walls not following a particular arrangement along the internal passage so as to form a disorderly arrangement.

Abstract: A heat exchanger for cooling a component is coupled with a cowl at least partially surrounding the component. The cowl defines a cowl plenum and a peripheral gap for receiving the heat exchanger. The heat exchanger includes a housing defining a heat exchange plenum for receiving a cool fluid stream and a plurality of heat exchange tubes passing through the heat exchange plenum for receiving a hot fluid stream. A discharge manifold defines a discharge plenum that provides fluid communication between the heat exchange plenum and the cowl plenum through a fluid outlet. In addition, an impingement baffle at least partially defines the discharge manifold and defines a plurality of cooling holes for impinging cooling air on the component proximate the heat exchanger.

Abstract: A gas turbine engine has a compressor section with a downstream most end and a cooling air tap at a location spaced upstream from the downstream most end. The cooling air tap is passed through at least one boost compressor and at least one heat exchanger, and then passed to a turbine section to cool the turbine section. The boost compressor is driven by a driveshaft which is driven by the turbine section. A boost turbine selectively drives the boost compressor.

Abstract: The invention aims to shorten the time required for start-up and prevent excessive increases in the heat loads on turbine blades.

Abstract: A diffuser case support structure for a gas turbine engine includes a fairing disposed circumferentially about a longitudinal axis. The fairing defines a plurality of passages circumferentially spaced apart and forming at least a portion of a fluid path between a compressor and a combustor of the gas turbine engine. A diffuser frame includes a plurality of struts. Each of the plurality of struts is disposed between a pair of adjacent passages of the plurality of passages. The diffuser frame is configured to couple an inner diffuser case to an outer diffuser case. A sliding joint is formed between the fairing and the diffuser frame, the sliding joint comprising a fastener extending generally axially through an aperture disposed in the fairing.

Abstract: An aircraft gas turbine engine includes a main engine shaft, a main engine shaft bearing arrangement for rotatably supporting the main engine shaft, and an electric machine including a rotor and a stator. The rotor is mounted to the main engine shaft and is rotatably supported by a further electric machine bearing arrangement extending between the rotor and the stator, and the stator is mounted to static structure of the gas turbine engine.

Abstract: An example gas turbine engine includes a propulsor assembly including at least a fan module and a fan drive turbine module; a gas generator assembly including at least a compressor section, a combustor in fluid communication with the compressor section, and a turbine in fluid communication with the combustor; and a geared architecture driven by the fan drive turbine module for rotating a fan of the fan module. A weight of the fan module and the fan drive turbine module is less than about 40% of a total weight of a gas turbine engine.

Abstract: A combustor for a gas turbine engine comprising: a combustion chamber; at least one fuel spray nozzle operable to deliver a fuel-air mixture into the combustion chamber, wherein during operation of the gas turbine engine the fuel-air mixture is combusted in the combustion chamber, thereby producing a combustion flame; a microwave generator coupled to a waveguide arranged to guide microwaves from the microwave generator into the combustion chamber such that the microwaves are incident on at least a portion of the combustion flame; and a detector operable to detect at least a portion of the microwaves reflected by the combustion flame and/or atomised fuel droplets.

Abstract: Methods and systems for operating a gas turbine engine having variable geometry mechanisms are described. The method comprises detecting a failure event associated with the gas turbine engine, identifying a location of the failure event, selecting an aerodynamic load modulation schedule for the variable geometry mechanisms of the gas turbine engine as a function of the location of the failure event, and applying the aerodynamic load modulation schedule as selected to the variable geometry mechanisms during the failure event.

Abstract: A fuel pump system for a turbomachine engine can include a boost pump driven by an electric motor and configured to be in fluid communication with a fuel tank, a primary pump configured to be driven by a shaft connected to the turbomachine engine, wherein the primary pump is in fluid communication with the boost pump downstream of the boost pump by a boost branch, a bypass flow branch that connects the boost branch to a downstream branch that is downstream of the primary pump, the downstream branch is in fluid communication with one or more metering valves and/or one or more fuel nozzles, and a bypass valve disposed in the bypass flow branch and/or the downstream branch and configured to selectively directly fluidly communicate the boost branch and the downstream branch.

Abstract: A control system operable includes a modified primary control parameter for an aircraft, the control system includes: a primary control parameter leg configured to output a demand in an aircraft primary control parameter; a primary control parameter compensation leg configured to receive a change in absolute levels and/or spatial distributions of swirl angle and/or fan pressure at a primary control parameter relative to a reference and convert the change into the primary control parameter; a processor adapted to receive the demand in the primary control parameter output from the primary control parameter leg and the change to the primary control parameter output from the primary control parameter compensation leg; compare the demand in the primary control parameter output from the primary control parameter leg and the change to the primary control parameter output from the primary control parameter compensation leg; and generate a modified primary control parameter for the aircraft.

Abstract: A two-stroke engine with a supercharger is provided that can prevent occurrence of abnormal combustion under high load and can improve fuel efficiency when compression self-ignition combustion is carried out under low load, and spark ignition combustion is carried out under high load. When an operation state of an engine body is in a high-load side operation range, an intake variable valve mechanism and an exhaust variable valve mechanism are actuated to retard at least closing timing of an intake valve and at least opening timing of an exhaust valve from those in the case where the operation state of the engine body is in a low-load side operation range at the same engine speed as the engine speed detected by engine speed detection means while particular conditions are satisfied.

Abstract: A method of adjusting operation of an internal combustion engine includes injecting fuel into cylinders of the internal combustion engine (first fuel operation); obtaining a first fuel exhaust temperature profile during the first fuel operation; injecting two fuels into the cylinders in a duel fuel operation; obtaining a duel fuel exhaust temperature profile; and adjusting the injection quantity and/or an injection timing of one fuel in a cylinder(s), based on a difference between the first fuel exhaust temperature profile and the duel fuel exhaust temperature profile. Other methods of operating with single fuel and using sensors other than exhaust temperature sensors are disclosed.

Abstract: A conventional gasoline engine is retrofitted and calibrated to operate as a bi-fuel engine using Hydrogen as the second fuel. When operated with Hydrogen, which typically leads to a reduction of engine output power, the engine is preferably operated in a charged mode and in a lean mode with the engine throttle kept in a wide open position during charged and lean mode operation resulting in a more efficient engine with a reduction of engine output power loss.

Abstract: An internal combustion engine for a motor vehicle includes a combustion chamber with a gas exchange valve which is movable between an open position and a first closed position. The gas exchange valve is movable on its path from the open position in a direction of the first closed position into an intermediate position located between the open position and the first closed position and is holdable in the intermediate position at least during a part of a compression cycle of the combustion chamber following the open position of the gas exchange valve and is movable into a second closed position following the intermediate position. The part comprises more than a half of the compression cycle and less than a whole of the compression cycle. The gas exchange valve is an inlet valve via which the combustion chamber is supplyable at least with air.

Abstract: A method for controlling the temperature of re-circulated exhaust gas in an internal combustion engine includes operating the internal combustion engine on a base line mode, receiving a signal indicative of an engine operating temperature, wherein the engine operating temperature is one of coolant temperature, exhaust temperature and oil temperature, comparing the engine operating temperature to a predetermined IEGR threshold, when the engine operating temperature is less than the predetermined IEGR threshold, activating an IEGR mode and activating an EEVO mode, and when the engine operating temperature is greater than the first predetermined IEGR threshold, deactivating the IEGR mode and deactivating the EEVO mode.

Abstract: In various aspects, internal combustion engines, engine controllers and methods of controlling engines are described. The engine includes a camshaft and a two cylinder sets. Cylinders in the first are deactivatable and cylinders in the second set may be fired at high or low output levels. The air charge for each fired working cycle is set based on whether a high or low torque output is selected. In some implementations, the camshaft is axially shiftable between first and second positions. First cam lobes are configured to cause their associated cylinders to intake a large air charge during intake strokes that occur when the camshaft is in the first position. Second cam lobes for cylinders in the second set cause their associated cylinders to intake a smaller air charge when the camshaft is in the second position. Second cam lobes for cylinders in the first set deactivate their associated cylinders.

Abstract: A variety of engine controllers and methods are described for controlling engines operating in a cylinder output level modulation mode. In one aspect transitions between different effective firing fractions are managed by gradually ramping an effective firing density. In another, when an engine transitions to a multi-level skip fire firing density that has more than one possible high/low/skip sequence, the phase of the high/low pattern is set relative to the phase of the firing pattern to ensure that a preferred high/low/skip sequence is generated. In another aspect, rapid large torque changes can be implemented in part by immediately changing the operational high/low fraction in response to a command to increase or reduce the desired engine torque.

Abstract: Disclosed herein is a method of predicting engine knocking, which includes calculating initial pressure in cylinder based on operating data and pressure in intake manifold measured using manifold absolute pressure sensor, calculating pressure at spark timing in the cylinder by interpreting compression process as polytropic process based on the calculated initial pressure in the cylinder, calculating heat release rate for individual operating conditions based on the calculated pressure in the cylinder at spark timing, calculating pressure change in the cylinder based on the calculated heat release rate, calculating unburned gas temperature in adiabatic compression process based on the calculated pressure change in the cylinder, and determining whether knock occurs by calculating ignition delay based on the calculated unburned gas temperature and calculating unburned gas mass fraction at crank angle at the end of the ignition delay.

Abstract: A fuel injection control apparatus including a microprocessor. The microprocessor is configured to perform calculating a target injection time, determining a first crank angle defining a start of fuel injection and a second crank angle defining an end of fuel injection, controlling a fuel injector in a first injection mode in which the fuel is injected for the first target injection time from a first time point corresponding to the first crank angle or a second injection mode in which the fuel is injected for the second target injection time from a second time point corresponding to a target crank angle, and the controlling including controlling the fuel injector so as to inject the fuel in the first injection mode first and in the second injection mode last when the fuel is injected multiple times between an intake stroke and a compression stroke.

Abstract: An injector failure cylinder diagnosis method based on signal deviation of an injector failure diagnosis system measures, by a controller, noise/vibration signals due to the combustion of an engine, separates an injector abnormal frequency band signal as an injector signal from the noise/vibration signals, divides cylinder number time series data, which use a signal maximum value of the noise/vibration signals as a cylinder #1, into segments, extracts a feature vector after confirming a segment number of the cylinder #1 with a vibration reduction signal of the noise/vibration signals re-measured using one of the cylinders as an idle cylinder and sorting it by injector causing vibration time series data, and confirms a failure injector with the feature vector, thereby independently diagnosing whether the injector for each cylinder is normal or abnormal considering the deviation of the noise/vibration signals between the injectors for each cylinder from the measured noise and vibration signals.

Abstract: Methods and systems are provided for monitoring a fuel injector of an internal combustion engine. In one embodiment, a method includes: receiving a set of feature data, the feature data sensed from a fuel injector during a fuel injection event; processing, by a processor, the set of feature data with a decision tree model to generate a prediction of a fault status; and selectively generating, by the processor, a notification signal based on the prediction.

Abstract: The present invention provides a high-efficiency and highly-reliable fuel injection control device that controls a fuel injection valve of an internal combustion engine and can perform injection amount control in accordance with a deterioration degree of the fuel injection valve. A fuel injection control device controlling a fuel injection valve of an internal combustion engine includes a deterioration determination unit that determines a deterioration state of the fuel injection valve, an injection amount learning unit that learns the injection amount of the fuel injection valve, and a learning frequency change unit that changes the learning frequency of the injection amount learning unit in accordance with the deterioration state of the fuel injection valve.

Abstract: An internal combustion engine according to one or more embodiments of the present disclosure may include an engine cylinder having a cylinder head and cylinder sidewalls and a piston that reciprocates within the engine cylinder. The piston, the cylinder head, and the cylinder sidewalls may at least partially define a combustion chamber. The internal combustion engine may also include a fuel injector that is positioned to inject fuel directly into the combustion chamber. The internal combustion engine may further include an engine control module that is in electronic communication with the fuel injector. The engine control module may determine if the internal combustion engine is operating at conditions corresponding to a super knock condition may occur and commands the fuel injector to operate under a split injection mode in which fuel is injected into the combustion chamber in a plurality of injection pulses.

Abstract: An installation tool installs a camshaft to a lower supporting portion. A cylinder head of an internal combustion engine includes the lower supporting portion, a cam holder, and a half-thrust washer. The camshaft is sandwiched between the cam holder and the lower supporting portion via a bearing. The half-thrust washer is inserted into respective annular groove disposed in an outer peripheral surface of the bearing and half annular groove disposed in the cam holder. The installation tool includes a bearing holder that holds the bearing, a head abutting portion abutted against a reference surface of the lower supporting portion with the bearing held, and an opposed concave knock portion into which a knock collar disposed in the cam holder is inserted to adjust a position of the half annular groove with respect to the half-thrust washer.

Abstract: The subject matter of this specification can be embodied in, among other things, a system includes a turbofan engine, a nacelle surrounding the engine and defining an annular bypass duct through the engine to define a generally forward-to-aft bypass air flow path, a thrust reverser movable to and from a reversing position where at least a portion of the bypass air flow path is reversed and comprising a first reverser portion having a first latch element, and a second reverser portion having a second latch element that is reversibly engageable with the first latch element to reversibly secure the second reverser portion to the first reverser portion, and an actuator comprising a catch element coupled to a portion of at least one of the first latch element and the second latch element to move the first reverser portion and the second reverser portion into and out of the reversing position.

Abstract: A nacelle for a gas turbine engine includes a ring shaped body defining a center axis and having a radially outward surface and a radially inward surface. An aft portion of the radially inward surface includes an axially extending convergent-divergent exit nozzle. An axially extending secondary duct passes through the nacelle in the convergent-divergent exit nozzle. The axially extending secondary duct includes an inlet at a convergent portion of the convergent-divergent exit nozzle and an outlet at a divergent portion of the convergent-divergent exit nozzle.

Abstract: The jet engine comprising a ramjet air path extending from an intake, into a combustion chamber, and out an exhaust nozzle, a fuel inlet leading into the combustion chamber, an oxidizer inlet leading into the combustion chamber and a partition being operable to selectively close the ramjet air path upstream of the combustion chamber to allow operation of the jet engine in rocket mode and open the ramjet air path to allow operation of the jet engine in ramjet mode.

Abstract: A catalytic thruster includes a reaction chamber that extends between first and second opposed chamber ends. The first chamber end includes a thermal standoff cup. There is a catalyst bed in the reaction chamber, and a feed tube extends into the reaction chamber through the thermal standoff cup.

Abstract: An improved primary pump for a carburetor is provided. The primary pump has a reduced cost and reduced space construction. The primary pump includes: a flexible cap having a cavity; an inlet open to the cavity of the flexible cap; an inlet side path fluidly coupled to the inlet; an inlet side check valve disposed in the inlet side path; an outlet open to the cavity of the flexible cap; an outlet side path fluidly coupled to the outlet; and an outlet side check valve disposed on the outlet side path, wherein at least one among the inlet side check valve and the outlet side check valve comprises a flap formed in a pump diaphragm of a fuel pump of the carburetor.