Abstract: Systems and methods for controlling temperature and total hydrocarbon slip in an exhaust system are provided. Control systems can comprise an oxidation catalyst, a particulate filter, a fuel injector, and a processor for controlling a fuel injection based on an oxidation catalyst model. Example system includes a virtual sensor comprising a controller for calculating and providing the total hydrocarbon slip to subsystems for after-treatment management based on modeling the oxidation catalyst. Example methods for controlling the temperature and the total hydrocarbon slip in an exhaust system include the steps of providing an oxidation catalyst model, monitoring a condition of the exhaust system, calculating a hydrocarbon fuel injection flow rate and controlling a fuel injection. The example methods further include the steps of determining an error in the oxidation catalyst model based on the monitored condition and changing the oxidation catalyst model to reduce the error.

Abstract: A method is provided for detecting urea deposits in an exhaust line of an automotive vehicle and includes determination if an exhaust gases temperature is reached, if the result of determination is positive, stoppage of urea injection, and determination of the quantity of NOx in the exhaust gases on the outlet of the selective catalytic reduction system. A comparison is performed between the quantity of NOx determined on the outlet of the selective catalytic reduction system and a theoretical quantity or a measured quantity of NOx produced by the internal combustion engine. If the comparison shows that the quantities are different, it is considered that urea deposits are present in the exhaust line.

Abstract: [Problem] To provide a reducing agent supply apparatus that can quickly melt urea aqueous solution solidified in a reducing agent injection valve to allow early start of the injection control of urea aqueous solution, a method for controlling the reducing agent supply apparatus, and an exhaust gas purification apparatus.

Abstract: A failure of a filter is detected with a higher degree of accuracy. There are provided a filter that is arranged on an exhaust passage of an internal combustion engine for collecting a substance contained in an exhaust gas, a substance amount detection part that is arranged on the exhaust passage at a downstream side of the filter for detecting an amount of substance in the exhaust gas, a flow speed detection part that detects or estimates a flow speed of the exhaust gas which passes through the filter, and a determination part that makes a determination that the filter is in a failure, when the higher the flow speed of the exhaust gas passing through the filter, the larger a ratio of an amount of change in the amount of substance to an amount of change in the flow speed of the exhaust gas becomes.

Abstract: An exhaust emission control apparatus for an internal combustion engine includes: an exhaust gas purification catalyst arranged in an exhaust gas passage of the internal combustion engine; an air/fuel ratio sensor installed on an upstream side of the exhaust gas purification catalyst and detects an air/fuel ratio of an exhaust gas discharged from the internal combustion engine; air/fuel ratio feedback control means that performs feedback control of the air/fuel ratio based on an output of the air/fuel ratio sensor; and sensor output correcting means that corrects a shift in the output of the air/fuel ratio sensor. The sensor output correcting means is configured so as to correct a shift in the output of the air/fuel ratio sensor using a lean shift amount of the air/fuel ratio sensor output in accordance with a quantity and/or a proportion of an aldehyde included in the exhaust gas.

Abstract: An emission control system for an engine includes a catalyst and an exhaust-gas sensor provided downstream of the catalyst in a flow direction of exhaust gas. The exhaust-gas sensor includes a sensor element that includes a pair of electrodes and a solid electrolyte body located between the electrodes. The emission control system further includes a constant current supply portion that changes an output characteristic of the exhaust-gas sensor by applying a constant current between the electrodes, a rich direction control portion that performs a rich direction control after a fuelling-stop control, and a characteristic control portion that performs a rich responsiveness control during the rich direction control. In the rich direction control, an air-fuel ratio of the exhaust gas is made to be richer. In the rich responsiveness control, the constant current supply portion increases a detection responsiveness of the exhaust-gas sensor with respect to rich gas.

Abstract: An emission control system for an engine includes a catalyst and an exhaust-gas sensor provided downstream of the catalyst in a flow direction of exhaust gas. The exhaust-gas sensor includes a sensor element that includes a pair of electrodes and a solid electrolyte body located between the electrodes. The emission control system further includes a constant current supply portion that changes an output characteristic of the exhaust-gas sensor by applying a constant current between the electrodes, a catalytic-state determination portion which determines a rich/lean state of the catalyst, a rich direction control portion which performs and terminates a rich direction control depending on the rich/lean state of the catalyst, a lean direction control portion which performs a lean direction control after the rich direction control, and a characteristic control portion which performs a lean responsiveness control at least during the lean direction control.

Abstract: In an internal combustion engine, inside of an engine exhaust passage, a hydrocarbon feed valve (15) and an exhaust purification catalyst (13) are arranged. On the exhaust purification catalyst (13), platinum Pt (51) is carried and a basic layer (53) is formed. At the time of engine operation, a main concentration changing action in which the concentration of hydrocarbons which flow into the exhaust purification catalyst (13) is made to change by a predetermined amplitude (?HA) and predetermined period (?TA) is performed. Furthermore, before each main concentration changing action, an auxiliary concentration changing action in which the concentration of hydrocarbons is made to change by an amplitude (?HB) smaller than the amplitude (?HA) at the time of each main concentration changing action is performed.

Abstract: A control system for an internal combustion engine is provided, and includes an exhaust gas conduit, an oxidization catalyst (“OC”) device, a temperature sensor, an intake mass air flow sensor, an engine air intake mechanism, and a control module. The exhaust gas conduit is in fluid communication with, and is configured to receive an exhaust gas. The OC device is in fluid communication with the exhaust gas conduit. The OC device has an OC light-off temperature. The OC device is selectively activated to the light-off temperature to induce oxidization of the exhaust gas. The temperature sensor is situated in the exhaust stream upstream of the OC device. The temperature sensor monitors an exhaust gas temperature. The intake mass air flow sensor measures an air mass entering the internal combustion engine. The engine air intake mechanism is selectively activated to modulate the air mass entering the internal combustion engine.

Abstract: A control method for monitoring a soot sensor of an exhaust treatment system is provided. The control method includes: determining when regeneration has completed; comparing soot sensor data to an estimated soot data based on the determining; and generating a message based on the comparing.

Abstract: The present invention is related to an improved thermal insulation of an exhaust tube (6) for use in a rocket engine. The thermal insulation is provided for as a layered structure wherein respective layers comprises a composite material, and wherein dominant directions of fibres in respective adjacent layers are different with respect to each other. In addition, a flexible layer might be used to attach the thermal insulation to an inner wall of the exhaust tube (6).

Abstract: An energy storage system utilizing compressed gas as a storage medium, may include one or more turbines configured to convert energy in gas expansion and compression processes. One or more axial and centrifugal turbines may be used to store energy by compressing gas, and to recover energy from expanding gas. A plurality of orifices/nozzles may introduce a liquid into the gas as a heat exchange medium. Orifices/nozzles may be disposed on various surfaces of a turbine and/or in a separate mixing chamber flowing to a turbine. Structures of the turbine may be designed to mitigate damage caused by liquid injection, for example the turbine blades may be flexible and/or comprise impact-resistant materials.

Abstract: The invention relates to engineering hydraulics, in particular to hydraulic drives with closed working fluid circulation system used, for example, in mechanical engineering, shipbuilding, machine-tool and aircraft building. The hydraulic drive with closed working fluid circulation system contains a hydraulic accumulator (1) connected through a pipeline with an unregulated single-rotating hydraulic pump (2) with a drive motor. The hydraulic pump (2) is connected through pressure (4) and drainage (5) pipelines to a hydraulic distributor (6) with a control lever (7), at the same time the hydraulic distributor (6) is connected through pressure-drainage pipelines (8, 9) to the chambers of a double-acting hydraulic motor (12) with a piston (13) and rods(14, 15). Between the pressure and drainage pipelines is connected a check valve (16).

Abstract: An energy conversion device, a removable assembly for use with the energy conversion device and an associated methods. The energy conversion device comprises a flexible diaphragm configured to be located between a first fluid and a second fluid and being moveable in response to variations in at least one of the first and second fluids to permit energy transfer between said fluids; and a limit apparatus configured to limit movement of the diaphragm at a limit position, wherein the limit apparatus defines a contoured contact surface configured to be engaged by the diaphragm when in its limit position.

Abstract: An energy conversion system including an annular member disposed around a shaft and at least partially defining a first radial flow passage that is fluidly coupled to a wave chamber and a second radial flow passage that is fluidly coupled to a port; a first plurality of nozzle vanes extending at least partially through the first radial flow passage, and configured to impart a first exit swirl angle in a fluid; a turbine wheel coupled to the shaft, disposed radially between the shaft and the annular member, defining an axial flow passage that is fluidly coupled to the first and second radial flow passages, and including a first plurality of impulse blades; and a second plurality of nozzle vanes disposed around the shaft, extending at least partially through the second radial flow passage, and configured to impart a second exit swirl angle in the fluid.

Abstract: An in-built energy conservation device has been described for offshore turbines. The energy conservation device includes a heat engine and a generator. The heat engine extracts a portion of heat energy from a coolant flowing the through the wind turbine. The heat engine further converts the heat energy into the mechanical energy. The generator converts the mechanical energy into the electrical energy. The electrical energy is further used for the operation of at least one of a heat exchanger unit and an air treatment plant present in the offshore wind turbine. The energy conservation device further includes an inlet. The inlet allows the passage of treated air through the energy conservation device for thermal conditioning of the treated air. The thermal conditioning makes up for the thermal losses of the treated air while passing though a plurality of flow lines within a wind turbine tower.

Abstract: A heat machine having an external heat source and an external heat sink may be configured as a Stirling engine having a hot pair of cylinder-and-displacer combinations 15 and a cold pair of cylinder-and-displacer combinations 16 though advantageously two pairs of hot combinations 15 and two pairs of cold combinations 16 are provided, arranged mutually at right angles. Mechanisms 20 associated with the hot and cold displacers controls the movement thereof to be truly sinusoidal and are contained within casings 21. The pressure in the working fluid spaces remote from the mechanisms 20 and also the pressure in the casings 21 is monitored and compared, and then is controlled such that the casing pressure is slightly less than the minimum working fluid pressure in the working fluid spaces. The relative phase of the two mechanisms 20 associated respectively with the hot displacers and the cold displacers is adjustable (28,29,30,31; and FIG. 4).

Abstract: An electric booster includes a housing having one end including a coupling surface where the housing is coupled to a master cylinder, and the other end including an attachment surface where the housing is attached to a vehicle. A controller includes a flat plate-like control board, and the control board is disposed so as to be positioned between a first plane including the attachment surface of the housing where the housing is attached to the vehicle, and a second plane including the coupling surface of the housing where the housing is coupled to the master cylinder.

Abstract: An exhaust system for an engine includes a first exhaust manifold configured to receive exhaust from the engine, a second exhaust manifold configured to receive exhaust from the engine in parallel with the first exhaust manifold, and at least two turbochargers configured to receive exhaust from the first and second exhaust manifolds. The system also includes a first turbocharger valve fluidly connected to one of the at least two turbochargers. The first turbocharger valve is configured to selectively fluidly connect the one of the at least two turbochargers to the first and second exhaust manifolds. The system further includes a recirculation circuit in fluid communication with the first exhaust manifold. The recirculation circuit includes a first recirculation valve configured to regulate passage of exhaust through the recirculation circuit.

Abstract: An internal combustion engine wherein an exhaust purification catalyst and a hydrocarbon feed valve are arranged downstream in an exhaust passage. A first NOX purification method, which removes NOX by making a concentration of hydrocarbons that flows into the exhaust purification catalyst vibrate within predetermined amplitude and period ranges and a second NOX purification method which utilizes an adsorption action of NOX to the exhaust purification catalyst are used. A high pressure exhaust gas recirculation system (HPL) causing recirculation of high pressure exhaust gas and a low pressure exhaust gas recirculation system (LPL) causing recirculation of low pressure exhaust gas are provided.

Abstract: The invention relates to a device and a method for the recovery of waste heat from an internal combustion engine (2). A feed pump (6), a heat exchanger (8), an expansion engine (10) and a capacitor (12) are arranged in a circuit (4) containing a circulating working medium. A steam accumulator (40) for storing the vaporous working medium is also arranged in the circuit (4).

Abstract: A tubular heat-absorbing element partly enclosed in an insulating layer or jacket, has absorbing surface that is accessible to solar radiation. The thermal insulation is designed to provide entry to solar radiation by way of a cavity. The absorbing surface can be substantially planar.

Abstract: A device (1) for producing pressurized hot or cold water comprising: a water heating and storing tank (5); a steam generator (6),—a cold water source (13); at least one pressurizable transfer tank (4) provided with: at least an inlet (14) for filling the tank (4) with water, an inlet (7) for introducing steam from the steam generator (6), and an outlet (8) for evacuating pressurized water; and separate valve means (31, 91, 71) to respectively fill the tank (4) with water, introduce steam in the tank, and evacuate pressurized water from the tank (4).

Abstract: The disclosed process and apparatus provide for air separation and steam generation in a combined system that comprises a steam system (10) and an air separation plant (9), wherein a feed air stream (1) is introduced into a multistage air compression system (101, 102, 103) having n stages (n>=3) and compressed to a first high pressure that is equal to the final pressure of the air compression system, and, at this final pressure, is introduced (8) into the air separation plant (9). An intercooler is arranged between an i-th stage (102) (1<=i<n) and an i+1-th stage (103) of the air compression system; there, the feed air stream (4) is cooled in indirect heat exchange with a feed water stream (11).

Abstract: A method of operating a combined gas and steam turbine system is provided. The system includes a gas turbine, a waste heat steam generator with an evaporator heating area, and a steam turbine. Fluid is fed to the waste heat steam generator as feed water. A primary control loop controls a feed water flow rate. Taking into account heat stored in the evaporator heating area, a primary desired value for the feed water flow rate is determined based upon a desired overheating value characteristic of a temperature by which the fluid exceeds a boiling point as the fluid exits the evaporator heating area and based upon a heat flow parameter characteristic of a heat flow transfer from fuel gas to the fluid via the evaporator heating area. The desired overheating value is lowered from a first value to a second value in order to activate an instantaneous power reserve.

Abstract: A power plant includes a boiler, a stream turbine generator, a post combustion processing system, a feed water regeneration processing system and a heat exchanger. Heat from the heat exchanger is used to regenerate (a) a reagent that absorbs carbon dioxide from flue gas and (b) a water-lean desiccant used to increase plant operating efficiency.

Abstract: The invention relates to a turbine wheel arrangement for a gas turbine comprising two successive turbine wheels (18, 20) rotating in opposite directions, wherein the first turbine wheel (18) comprises flow channels (42) of a Laval cross-sectional shape, distributed over the circumference and having radially inner gas inlets (43) and radially further out gas outlets (45), in each case with a substantially tangential flow direction component, wherein the gas outlets (45) act an the second axially or radially acting turbine wheel (20) in the direction of flow. This has the effect that the thermal energy and compressive energy of the gas at the nozzle inlet is largely converted into flow energy at the outlet of the turbine stage. The rotational speeds of the two rotors coupled to the turbine wheels can be set as desired, allowing the operational states of the two systems to be optimally set without adjusting systems.

Abstract: The present invention relates to an annular combustion chamber of a gas turbine with—relative to the engine axis—a radially outer combustion chamber wall and a radially inner combustion chamber wall, with the combustion chamber walls forming an annular combustion space, with a combustion chamber head having a plurality of fuel nozzles and air inlet openings, with the respective central axes of the fuel nozzles forming an envelope rotationally symmetrical to the engine axis, the envelope dividing the combustion chamber into an annular and radially outer area and an annular and radially inner area, with the radially outer area and the radially inner area having the same volumes.

Abstract: A heat shield includes a panel having a forward face and an aft face, a circumferential outer side and a circumferential inner side such that the panel subtends a predetermined arc, and a first radially extending side and a second radially extending side each extending from the circumferential outer side to the circumferential inner side. The panel defines an opening extending between the forward face and the aft face, a lip projecting from the forward face and extending around the opening, a rail projecting from the forward face and extending around the lip to define a cavity region between the lip and the rail, and a plurality of holes in the cavity region. Each of the plurality of holes extends from the forward face to the aft face. A region of the panel extending from the lip to the circumferential outer side is free of any aft-projecting features.

Abstract: A method for reducing emissions in a turbo machine is disclosed. The method includes providing fuel to a multi-tube nozzle and reducing the differences in the mass flow rate of fuel into each tube. An improved multi-tube nozzle is also disclosed. The nozzle includes an assembly that reduces the difference in the mass flow rate of fuel into each tube.

Abstract: A mid-turbine frame (MTF) for a gas turbine engine includes an inner manifold directing air to a turbine rotor of the gas turbine engine.

Abstract: A method for transferring fuel includes flowing water to at least one nozzle of a main fuel circuit. Also included is flowing oil to the at least one nozzle of the main fuel circuit. Further included is flowing liquid fuel to the at least one nozzle of the main fuel circuit, wherein flowing water to the at least one nozzle of the main fuel circuit occurs prior to flowing oil to the at least one nozzle of the main fuel circuit and flowing liquid fuel to the at least one nozzle of the main fuel circuit.

Abstract: A fuel injector system for a turbine engine may include a center body disposed about a longitudinal axis and a barrel housing positioned radially outwardly from the center body to define an annular passageway therebetween. The fuel injector may also include one or more fuel discharge outlets positioned in the annular passageway. The one or more fuel discharge outlets may be configured to discharge pulses of a fuel into the annular passageway. The fuel injector may further include one or more fluidic oscillators fluidly coupled to the one or more fuel discharge outlets. The one or more fluidic oscillators may be configured to induce pulsations in the fuel discharged by the one or more fuel discharge outlets.

Abstract: A gas turbine engine includes a buffer system that communicates a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and a valve that selects between the first bleed air supply and the second bleed air supply to communicate the buffer supply air to the portion of the gas turbine engine.

Abstract: A gas turbine engine includes a buffer system that includes a first circuit and a second circuit. The first circuit can communicate a first buffer supply air to a first portion of the gas turbine engine and the second circuit can communicate a second buffer supply air to a second portion of the gas turbine engine.

Abstract: A buffer system for a gas turbine engine includes a heat exchanger having a first inlet and outlet and a second inlet and outlet. The first outlet is configured to provide a cooled pressurized fluid. First and second air sources are selectively fluidly coupled to the first inlet. A third air source is fluidly coupled to the second inlet. Multiple fluid-supplied areas are located remotely from one another and are fluidly coupled to the first outlet. The multiple fluid-supplied areas include multiple bearing compartments. A method of providing pressurized air in a gas turbine engine includes selectively providing pressurized air from multiple air sources to a heat exchanger to cool the pressurized air. The cooled pressurized air is distributed to multiple fluid-supplied areas within the gas turbine engine.

Abstract: A method of managing a gas turbine engine operating line includes detecting an air speed and a fan speed. A data table is referenced that includes a desired variable area fan nozzle position based upon air speed and fan speed. The detected air speed and detected fan speed are compared to the data table to determine a target variable area fan nozzle position. An actual variable area fan nozzle position is adjusted to the target variable area fan nozzle position.

Abstract: A gas turbine engine includes a fan, a fan drive gear system coupled to drive the fan, a compressor section including a first compressor and a second compressor and a turbine section. The turbine section includes a first turbine coupled to drive a first spool, which is coupled at a first axial position to a compressor hub that is coupled to drive the first compressor. The first spool is also coupled at a second axial position to a fan drive input shaft that is coupled to drive the fan drive gear system. A second turbine is coupled through a second spool to drive the second compressor. A speed sensor probe is operable to determine a rotational speed of the first spool. The speed sensor probe is located axially aft of the first axial position and the second axial position.

Abstract: A fuel nozzle assembly for use with a turbine engine includes at least one fuel conduit coupled to at least one fuel source. The fuel nozzle assembly also includes at least one swirler that includes at least one wall having a porous portion. The at least one wall is coupled to the at least one fuel conduit. The porous portion is formed from a material having a porosity that facilitates fuel flow therethrough. At least one fuel flow path is thereby defined through the porous portion of the at least one wall.

Abstract: A fuel system for an auxiliary power unit includes a mechanical fuel pump, an electric fuel pump, and a controller. The mechanical fuel pump provides fuel flow to the auxiliary power unit and has an output dependent upon an operational speed of the auxiliary power unit. The electric fuel pump provides fuel flow to the auxiliary power unit, and is located in flow series with the mechanical fuel pump. The controller causes the electric fuel pump to provide fuel flow during starting of the auxiliary power unit.

Abstract: A gas turbine combustor has a chamber supplied with fuel and air and a multi-burner having a plurality of burners provided with an air hole plate having a plurality of air holes, and fuel nozzles for supplying fuel to the air holes in the air hole plate; the multi-burner is made up of a center burner disposed in the center and a plurality of outer burners around the center burner, the outer burners are divided into inner fuel nozzles and outer fuel nozzles to separately supply fuel through fuel systems, and the fuel is supplied to the fuel nozzles in the center burner or to the fuel nozzles in the center burner and the inner fuel nozzles in the outer burners disposed around the center burner in a partial load condition in which the load is lower than that of when all the fuel systems are used to supply fuel.

Abstract: A dual fuel engine control system comprising a first fuel control system configured to control the flow of a first fuel to an aircraft gas turbine engine, and a second fuel control system configured to control the flow of a second fuel to the aircraft gas turbine engine.

Abstract: A method of managing a gas turbine engine variable area fan nozzle includes the steps of evaluating an icing condition to determine the likelihood of ice presence. A variable area fan nozzle position is altered if ice is likely present or actually present. The gas turbine engine includes a fan nacelle including a flap configured to be moveable between first and second positions. An actuator is operatively coupled to the flap. A controller is configured to evaluate an icing condition to determine the likelihood of ice presence. The controller is configured to alter a variable area fan nozzle position schedule if ice is likely present by providing a command to the actuator to adjust the flap from the first position to the second position.

Abstract: A gas turbine engine includes a buffer system. The buffer system can include a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the buffer supply air at an acceptable temperature to anti-ice the hardware of said fan section.

Abstract: According to one aspect of the invention, an engine system includes one or more fuel circuits configured to provide gaseous fuel from a fuel source for combustion. The system further comprises a conduit in fluid communication with the one or more fuel circuits, wherein the conduit is configured to receive a first gaseous fuel flow and an oxidant flow for a reaction within the conduit, wherein a temperature of the conduit is controlled by a second gaseous fuel flow along an outer wall of the conduit.

Abstract: A gas turbine engine includes a buffer system that can communicate buffer supply air to a portion of the gas turbine engine. The buffer system can include a first circuit and a second circuit. The first circuit selects between a first bleed air supply having a first pressure and a second bleed air supply having a second pressure that is greater than the first pressure to render a first buffer supply air having an intermediate pressure. The second circuit selects between a third bleed air supply and a fourth bleed air supply to communicate a second buffer supply air.

Abstract: A gas turbine engine includes a buffer system that can communicate a buffer supply air to a portion of the gas turbine engine. The buffer system includes a first bleed air supply having a first pressure, a second bleed air supply having a second pressure that is greater than the first pressure, and an ejector that selectively augments the first bleed air supply to prepare the buffer supply air for communication to the portion of the gas turbine engine.

Abstract: A gas turbine engine includes a buffer system that communicates a buffer cooling air to at least one bearing structure and at least one shaft of the gas turbine engine. The buffer system includes a first bleed air supply and a conditioning device that conditions the first bleed air supply to render the first buffer supply air at an acceptable temperature to pressurize the at least one bearing structure and cool the at least one shaft.

Abstract: A gas turbine engine includes a first zone and a second zone downstream from the first zone. A buffer system can communicate a buffer cooling air to at least the first zone. A bleed source can communicate a bleed air to the second zone.

Abstract: A gas turbine engine has a fan, a compressor section, a combustor, and a turbine section. The fan delivers a portion of air into the compressor, and into a duct, as bypass air. A bleed air system bleeds a quantity of air from the compressor into a chamber at least at low power conditions of the engine. The bleed air system has an opening which may be selectively closed to block bleed air, or opened to allow bleed flow from the compressor into the chamber. A heat exchanger is positioned such that a first surface of the heat exchanger is contacted by bypass air in the duct, and a second surface of the heat exchanger is contacted by bleed air when the bleed air system directs air from the compressor into the chamber.