Abstract: An apparatus for adjusting power and noise characteristics of an internal combustion engine comprises a wall configured to define an engine cylinder that includes a bore and a compression relief passage. A compression relief valve is configured to selectively adjust fluid flow capacity of the compression relief passage. A manifold is configured to be in fluid communication with the exhaust passage and includes an exhaust bypass valve to permit exhaust to at least partially bypass a noise suppressor. Operational characteristics of the engine can be adjusted along a range that extends from a first set of operational characteristics present when both the compression relief valve and the exhaust bypass valve are in a fully open position to a second set of operational characteristics present when both the compression relief valve and the exhaust bypass valve are in a fully closed position.

Abstract: In the specified cylinder, the heat shield film is formed on the top surface of the piston, the surface of the parachute part of the exhaust valve, and the wall surface of the exhaust port. On the other hand, in cylinder other than the specified cylinder, the heat shield film is formed only on the top surface of piston. The heat shield film is also formed on the inner wall of the exhaust manifold, the inner wall of the exhaust pipe, and the inner wall of the housing. Among the exhaust manifold, however, the heat shield film is not formed on the inner wall of the branch pipe connected to the exhaust port of the other cylinder.

Abstract: A support structure for an exhaust system part that configures an exhaust system of an internal combustion engine for a vehicle includes a bracket and a support member. The bracket includes a first plate and a second plate. The first plate has both end portions attached to the second plate, and the second plate has both end portions attached to the exhaust system part. A first space is defined between the first plate and the second plate, and a second space is defined between the second plate and the exhaust system part. Each of the first space and the second space has a first open end disposed on the vehicle front side, and has a second open end disposed on the vehicle rear side. The first plate, the first space, the second plate, and the second space are disposed between the support member and the exhaust system part.

Abstract: A noise abatement system including at least one fluid circulation chamber to receive at least one flow of fluid; at least one vorticity-inducing component adjacent to the at least one fluid circulation chamber, the at least one vorticity-inducing component to redirect the at least one flow of fluid tangentially to an inside perimeter wall of the at least one fluid circulation chamber to create fluctuations in a flow and pressure of the fluid causing increased and variable vorticity within the at least one fluid circulation chamber; and at least one vorticity-interaction region in communication with the at least one vorticity-inducing component to attenuate acoustics caused by the at least one flow of fluid.

Abstract: An engine cooling system for a vehicle may relate for flowing the coolant from the front side to the rear side based on an arrangement direction of the cylinder and simultaneously cooling the coolant by a cross flow type to flow from an exhaust side to an intake side between each combustion chambers while separating and cooling the coolant flowing through the cylinder block and the cylinder head, maximizing an entire cooling efficiency through a flow control of the coolant and reducing a fuel consumption.

Abstract: An aircraft engine assembly having a turbo-compounded internal combustion engine having an engine shaft. A coolant cooler is fluidly connected to a coolant circuitry of the internal combustion engine and to the environment. A plenum is connected with the environment via the coolant cooler and via an air outlet. A fan is disposed adjacent the air outlet and is operable to drive an airflow from the environment into the plenum via the coolant cooler. The fan is spaced apart from the internal combustion engine in a direction perpendicular to the engine shaft. A method of defining a cooling air circulation is also discussed.

Abstract: An air blowing fan device includes an electric motor including a rotation shaft, and an air blowing fan including an attachment portion, a boss portion, and an outer circumferential side air blowing blades. The attachment portion is attached to the rotation shaft. The boss portion includes a tubular portion that is positioned radially outward of the attachment portion and of which the outer diameter dimension is larger than the outer diameter dimension of the electric motor, and a linkage portion. The electric motor is disposed in the tubular portion, the outer circumferential side air blowing blade extends radially outward from an outer circumferential surface of the tubular portion, the linkage portion includes a ventilation hole, and an area occupied by the electric motor and an area occupied by the outer circumferential side air blowing blade partially overlap each other in the direction in which the rotation shaft extends.

Abstract: A coolant control valve unit includes: a valve housing including an inlet through which coolant is supplied, first and second coolant chambers fluidly isolated from each other, first and second passages respectively communicating the inlet with the first and second coolant chambers, and first and second outlets respectively communicated with the first and second coolant chambers; first and second valves disposed respectively in the first and second passages to be movable in a predetermined direction and respectively closing or opening the first and second passages; a driving plate connected with the first and second valves respectively through first and second stems and simultaneously moving the first and second valves in the predetermined direction by a distance; and an actuator moving the driving plate in the predetermined direction to control opening or closing of the first and second passages.

Abstract: An anomaly diagnosing apparatus is adapted for a cooling device in an internal combustion engine. The apparatus is configured to execute an enlarging process, a rate calculating process, and an anomaly determining process. The enlarging process includes enlarging the cross-sectional area of the flow passage between an inner channel and an outer channel in the cooling device. The rate calculating process includes calculating a reference rate for a rate of rise of temperature of cooling water. The anomaly determining process includes determining that an anomaly is present in the check valve if a rate of rise of a detection value of cooling water temperature is smaller than the reference rate. The rate calculating process includes calculating the reference rate such that the reference rate has a smaller value in a case where the enlarging process is executed than in a case where the enlarging process is not executed.

Abstract: The present disclosure relates to a separate cooling system of a vehicle, including an engine including a cylinder head and a cylinder block transmitting a coolant to the cylinder head, a coolant pump, a plurality of parts disposed on a plurality of coolant lines, an electronic thermostat mounted on the cylinder block so as to selectively transmit the coolant from the cylinder block to the plurality of coolant lines, a cooling coolant temperature sensor measuring a coolant temperature of the cylinder block, a controller controlling an operation of the electronic thermostat depending on a vehicle operation state output signal including the cooling coolant temperature sensor, and a mechanical thermostat disposed at an upstream of the coolant pump so as to selectively block the coolant via a radiator and a reservoir tank among the coolant transmitted from the plurality of coolant line to the coolant pump.

Abstract: The present disclosure provides a water pump for a vehicle including an impeller with an impeller discharging port configured to pump and discharge coolant, a shroud movably installed to open and close the impeller discharging port, a first pushing unit configured to push the shroud in a direction of opening the impeller discharging port, and a second pushing unit configured to push the shroud in a direction of closing the impeller discharging port.

Abstract: A cooling system may include a cylinder block; an exhaust gas recirculation (EGR) cooler that receives some of a coolant of the cylinder block and transmits the received coolant back to the cylinder block; a cylinder head that receives a coolant from the cylinder block; a thermal management module that selectively transmits the coolant received from the cylinder head to a plurality of coolant lines; a water pump that transmits the coolants transmitted from the plurality of coolant lines to the cylinder block; and a controller that is connected to the thermal management module and configured to control operation of the thermal management module.

Abstract: A piston comprises a crown portion with a contoured bowl having a reentrant surface extending from the top squish surface that connects to a lower sidewall surface that connects to a swirl pocket surface disposed adjacent the bottom bowl surface.

Abstract: A method for operating an internal combustion engine includes using a 3-front combustion method. When the fuel is injected into the combustion chamber the fuel flows through an injection element with a hydraulic flow of more than 1000 cubic centimeters per 60 seconds and under an injection pressure of 100 bar and 1 liter capacity per cylinder if the internal combustion engine is used in a truck application. The fuel flows through the injection element with a hydraulic flow of more than 1900 cubic centimeters per 60 seconds and under an injection pressure of 100 bar and 1 liter capacity per cylinder if the internal combustion engine is used in a car application.

Abstract: In an intake structure of an internal combustion engine, on an intake upstream side from a valve seat of an intake port, a convex portion is provided which protrudes to an inside of the intake port in a place near an outer circumferential portion of a cylinder chamber when viewed from an upper side of the cylinder chamber. The convex portion includes an upstream guide surface extending from an apex of the convex portion to the intake upstream side, and a downstream guide surface extending from the apex to an intake downstream side and including a curved surface recessed inside the convex portion at a middle portion thereof.

Abstract: A cooling system includes a charge air cooler system that includes a first stage that receives charge air via a charge air flow path and receives coolant fluid via a first coolant fluid flow path. A second stage receives charge air from the first stage via the charge air flow path, outputs the charge air, and receives the coolant fluid via a second coolant fluid flow path. A third stage receives and outputs the charge air from the second stage via the charge air flow path and receives the coolant fluid via a third coolant fluid flow path. The cooling system includes a low temperature radiator system that includes a low temperature radiator that directs the coolant fluid toward the third stage via the third coolant fluid flow path and includes a high temperature radiator system that directs the coolant fluid toward the first stage and second stage.

Abstract: An inlet tank for a charge cooler comprises a manifold portion, a turbocharger inlet port, and a supercharger inlet port. The turbocharger inlet port is in fluid communication with a compressor wheel of a turbocharger and the manifold portion of the inlet tank. An opening is formed in a sidewall of the turbocharger inlet port. The supercharger inlet port is in fluid communication with an electric supercharger and intersects the turbocharger inlet port. The opening formed in the sidewall of the turbocharger inlet port provides fluid communication between the supercharger inlet port and the turbocharger inlet port. A valve element selectively determines when a flow of air from the supercharger inlet port enters the turbocharger inlet port through the opening based on a pressure differential present between the air exiting the compressor wheel of the turbocharger and the air exiting a compression mechanism of the electric supercharger.

Abstract: A cooling system includes a charge air cooler system that includes a first stage and a second stage. The first stage receives charge air via a charge air flow path. The first stage receives coolant fluid via a first coolant fluid flow path. The second stage receives the charge air from the first stage via the charge air flow path, such the second stage of the charge air cooler system outputs the charge air and receives the coolant fluid via a second coolant fluid flow path. The cooling system includes a low temperature radiator system that includes a low-temperature radiator that directs the coolant fluid toward the second coolant fluid flow path and a third coolant fluid flow path. The cooling system includes a high temperature radiator system that directs the coolant fluid toward the first stage via the first coolant fluid flow path.

Abstract: An intercooler for a turbocharged internal combustion heat engine; the intercooler has: a cooling chamber, which is provided with an air inlet opening and an air outlet opening opposite one another; a plurality of exchanger plates, which are stacked on top of one another inside the cooling chamber, are arranged parallel to an air flowing direction from the inlet opening to the outlet opening, are spaced apart from one another so as to define corresponding air passage channels between one another, and are internally hollow; a circulation circuit, which allows a cooling fluid to circulate inside the exchanger plates; and a plurality of thermoelectric cells, each of which is mounted on a corresponding exchanger plate, and has a cold side resting on the exchanger plate and a hot side delimiting a corresponding air passage channel.

Abstract: A turbocharging system for an internal combustion engine includes a turbocharger having a shaft supported for rotation about an axis. The turbocharger also includes a turbine wheel mounted on the shaft and configured to be rotated about the axis by the exhaust gas, and a compressor assembly mounted on the shaft and configured to pressurize an airflow received from the ambient for delivery to the cylinder. The turbocharging system additionally includes an electric motor configured to generate electric motor torque. The turbocharging system further includes a one-way clutch configured to selectively connect the electric motor to the compressor assembly, such that the electric motor torque assists the turbocharger in generating boost pressure. An internal combustion engine employing such a turbocharging system is also disclosed.

Abstract: A turbocharger includes a housing, a turbine wheel, a bypass channel formed in the housing, a wastegate assembly having a valve and configured to selectively allow a flow of exhaust gas to bypass the turbine wheel via the bypass channel, and a wastegate outer housing having an aperture fluidly coupled to the bypass channel, and an outer valve seating surface, the valve configured to selectively seat against the outer valve seating surface over the aperture. A shroud extends outwardly from the wastegate outer housing and is configured to direct the bypass exhaust gas flow toward a catalytic converter.

Abstract: Described herein is a turbocharging system comprising a compressor having an air inlet and a compressed air outlet, the compressed air outlet to couple with the intake manifold of the internal combustion engine, a first turbine coupled to the compressor, the compressor driven without using power from the internal combustion engine; and a vacuum compressor coupled directly or indirectly to the first turbine. The first turbine can drive a common drive shaft that includes the compressor and the vacuum compressor or output of the first compressor can drive a second compressor that is coupled with the vacuum compressor. The vacuum compressor can be used to scavenge exhaust from the internal combustion engine.

Abstract: An auxiliary power unit for an aircraft includes a rotary intermittent internal combustion engine drivingly engaged to an engine shaft, a turbine section having an inlet in fluid communication with an outlet of the engine(s), the turbine section including at least one turbine compounded with the engine shaft, and a compressor having an inlet in fluid communication with an environment of the aircraft and an outlet in fluid communication with a bleed duct for providing bleed air to the aircraft, the compressor having a compressor rotor connected to a compressor shaft, the compressor shaft drivingly engaged to the engine shaft. The driving engagement between the compressor shaft and the engine shaft is configurable to provide at least two alternate speed ratios between the compressor shaft and the engine shaft.

Abstract: An auxiliary power unit for an aircraft, including an internal combustion engine having a liquid coolant system, a generator drivingly engaged to the internal combustion engine and having a liquid coolant system distinct from the liquid coolant system of the internal combustion engine, a first heat exchanger in fluid communication with the liquid coolant system of the internal combustion engine, a second heat exchanger in fluid communication with the liquid coolant system of the generator, an exhaust duct in fluid communication with air passages of the heat exchangers, and a fan received in the exhaust duct and rotatable by the internal combustion engine for driving a cooling air flow through the air passages. The liquid coolant system of the engine may be distinct from fuel and lubricating systems of the auxiliary power unit. A method of cooling a generator and an internal combustion engine is also discussed.

Abstract: A connecting rod for an internal combustion engine with an eccentrical element adjustment arrangement for adjusting an effective connecting rod length, the eccentrical element adjustment arrangement including at least one ball joint including a ball head that is arranged at a support rod and supported in a ball head receiver of a piston, wherein the ball head is secured at its outer surface in the ball head receiver by safety devices against sliding out of the ball head receiver, and wherein the safety devices are configured as a one-piece or a multi-piece annular safety element which is arranged in the piston at least partially bonded or form locking.

Abstract: The disclosure relates to an internal combustion engine (1) with at least one double cylinder (2), in which two inner pistons (6) and two outer pistons (7) are arranged such that they reciprocate in the double cylinder (2) by at least one respective inner connecting rod (8) or a respective first outer connecting rod (11a) and a respective second outer connecting rod (11b) with the aid of a crankshaft (4). The present disclosure provides an internal combustion engine (1) in which the outer connecting rods do not pivot. The two first outer connecting rods (11a) of the two outer pistons (7) are coaxial and integrally formed; and the two second outer connecting rods (11b) are coaxial and integrally formed.

Abstract: A thermal barrier for component surfaces of an engine. The thermal barrier includes a plurality of modules, each module includes a shield. An edge of at least one shield in the array is spaced apart from an edge of an adjacent shield in the array.

Abstract: A segmented thermal barrier for a combustion chamber surface of an internal combustion engine. The segmented thermal barrier includes a plurality of modules, each module with a support and a shield. The edges of shields of at least two adjacent modules are spaced apart by a distance.

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, a fan including fan blades, an outer housing that surrounds the fan to define a bypass flow path, a compressor section in fluid communication with the fan, the compressor section including a low pressure compressor section and a high pressure compressor section, a turbine section including a fan drive turbine section driving the fan and the low pressure compressor section and a high pressure turbine section driving the high pressure compressor section. A gear reduction including an epicyclic gear train is between the fan drive turbine section and the low pressure compressor section such that the low pressure compressor section and the fan are rotatable at a common speed and such that the fan is rotatable at a lower speed than the fan drive turbine section.

Abstract: The purpose of the present invention is to provide a furnace wall in which a throat section with a smaller channel diameter than other regions can be formed using all peripheral wall tubes. Provided is a furnace wall comprising: a plurality of peripheral wall tubes (142), which are disposed so as to form a cylindrical shape when aligned in one direction and through the interior of which cooling water flows; and fins (140) that connect neighboring peripheral wall tubes (142) in an airtight manner. In a throat section in which the diameter of a horizontal cross-section of the cylindrical shape is reduced in comparison to other regions, the peripheral wall tubes (142) are disposed so as to be in mutual contact and the fins (140) are disposed on the inner circumferential sides of the cylindrical shapes.

Abstract: A method of reducing rotor bow in a high pressure rotor of a gas turbine engine that has in axial flow a low pressure rotor and a high pressure rotor. The method involves storing bleed air from the gas turbine engine when the engine is running to provide stored pneumatic energy; and using that stored pneumatic energy after the engine has been shut-down to rotate the high pressure rotor at a speed and for a duration that reduces rotor bow. A gas turbine engine wherein rotor bow in the high pressure rotor after engine shut-down has been reduced by carrying out the aforesaid method is also disclosed.

Abstract: A method of controlling electrical power supplied to a component of a vehicle, the method comprising: receiving a signal comprising information associated with an operating condition of a gas turbine engine; determining whether a parameter exceeds a predetermined threshold value using the information in the received signal; and controlling a reduction in electrical power supplied to a component of a vehicle from a generator of the gas turbine engine if the parameter exceeds the predetermined threshold value.

Abstract: A recuperator includes a monolithic heat exchanger core having a first side proximal to a combustor inlet and a turbine outlet, and a second side that includes an exhaust outlet. A compressed air inlet is located on the second side, and a compressed air outlet is located on the first side. The compressed air outlet supplies air to a combustor. A first plurality of passageways connects the compressed air inlet to the compressed air outlet. A turbine exhaust inlet is located on the first side, and a turbine exhaust outlet is located on the second side. A second plurality of passageways connects the turbine exhaust inlet to the turbine exhaust outlet. The first and second plurality of passageways are defined by parting plates that extend radially outward in a spiral pattern that maintains a substantially equal distance between adjacent parting plates.

Abstract: A heat-exchanger device for an aircraft engine, having a fuel-oil heat exchanger for exchanging heat between fuel and oil, and a housing with an air inlet and an air outlet, wherein the fuel-oil heat exchanger is arranged at least partially within the housing such that air flowing from the air inlet to the air outlet can flow over or around the fuel-oil heat exchanger. The invention further relates to a method for operating an aircraft engine.

Abstract: Various embodiments of the present disclosure address problems associated with non-uniform flow of cooling air by providing a turbine engine including a cooling air chamber in fluid communication with a cooling air source, a turbine chamber, and multiple conduits fluidly connecting the cooling air chamber and the turbine chamber. The system is configured such that, when cooling air is flowing from a cooling air source the static pressure within the cooling fluid chamber is substantially uniform and such that the mass flow rates of cooling air through the conduits and into the turbine chamber are substantially uniform.

Abstract: A turbomachine fuel injector system includes an air distributor configured to be mounted to and contained within a casing and to provide air to mix with a fuel from one or more fuel distribution systems. The system includes a fuel manifold configured to be mounted indirectly to the casing such that the fuel manifold system is contained within the casing but is independent such that fuel manifold does not touch or directly mount to either an interior of the casing or touch the air distributor within the casing to prevent or reduce thermal transfer from the air distributor to the fuel manifold.

Abstract: An example system can include a combustion chamber of a jet engine, a radio-frequency power source, a direct-current power source, a resonator, and a fuel conduit. The resonator can be electromagnetically coupled to the radio-frequency power source and have a resonant wavelength. Further, the resonator can include (i) a first conductor, (ii), a second conductor, and (iii) a dielectric between the first conductor and the second conductor. The resonator can be configured to provide at least one of a plasma corona or electromagnetic waves. The fuel conduit can be configured to couple to a fuel source and have a fuel outlet for expelling fuel into a combustion zone of the combustion chamber. A portion of the fuel conduit is disposed within the first conductor.

Abstract: An example system can include a combustion chamber of a jet engine, a radio-frequency power source, a resonator, and a fuel conduit. The resonator can be electromagnetically coupled to the radio-frequency power source and have a resonant wavelength. Further, the resonator can include (i) a first conductor, (ii), a second conductor, and (iii) a dielectric between the first conductor and the second conductor. The resonator can be configured such that, when the resonator is excited by the radio-frequency power source with a signal having a wavelength proximate to an odd-integer multiple of one-quarter of the resonant wavelength, the resonator provides at least one of a plasma corona or electromagnetic waves. The fuel conduit can be configured to couple to a fuel source and have a fuel outlet for expelling fuel into a combustion zone of the combustion chamber. A portion of the fuel conduit is arranged proximate to the dielectric.

Abstract: Provided are turbine engines and methods of operating thereof by heating and evaporating liquid fuels in a controlled manner prior to burning. Specifically, a fuel is heated and evaporated while avoiding coking. Coking is caused by pyrolysis when the fuel contacts a metal surface within a certain temperature range, which is referred herein to a coking temperature range. In the described methods, the fuel is transferred from one component, maintained below the coking temperature range, to another component, maintained above this range. The fuel is airborne and does not contact any metal surfaces during this transfer, and coking does not occur. In some examples, the fuel is also mixed with hot air during this transfer. The heated fuel, e.g., as an air-fuel mixture, is then supplied into a combustor, where more air is added to reach flammability conditions.

Abstract: A method of starting a gas turbine engine is generally provided. The engine includes a rotor assembly including a compressor rotor and a turbine rotor each coupled to a shaft. The rotor assembly is coupled to a bearing assembly within a casing enabling rotation of the rotor assembly. The method includes determining, based on a lubricant parameter, a period of time within which a rotational speed of the rotor assembly is maintained within a bowed rotor mitigation speed range; rotating the rotor assembly for the period of time within the bowed rotor mitigation speed range; and accelerating the rotor assembly to the combustion speed to ignite a fuel-oxidizer mixture for combustion.

Abstract: An example system and corresponding method can include a combustion chamber of jet engine, a radio-frequency power source, and a resonator. The combustion chamber can include a liner defining a combustion zone, and include a fuel inlet configured to introduce fuel into the combustion zone. The resonator can have a resonant wavelength and include: a first conductor, a second conductor, a dielectric, and an electrode coupled to the first conductor. The resonator can be configured such that, when the resonator is excited by the radio-frequency power source with a signal having a wavelength proximate to an odd-integer multiple of one-quarter (¼) of the resonant wavelength, the resonator provides a plasma corona in the combustion zone. The controller can be configured to cause the radio-frequency power source to excite the resonator with the signal so as to provide the plasma corona.

Abstract: An example system and corresponding method can include a combustion chamber of a power-generation gas turbine, a radio-frequency power source, and a resonator. The combustion chamber can include a liner defining a combustion zone, and include a fuel inlet configured to introduce fuel into the combustion zone. The resonator can have a resonant wavelength and include: a first conductor, a second conductor, a dielectric, and an electrode coupled to the first conductor. The resonator can be configured such that, when the resonator is excited by the radio-frequency power source with a signal having a wavelength proximate to an odd-integer multiple of one-quarter of the resonant wavelength, the resonator provides a plasma corona in the combustion zone. The controller can be configured to cause the radio-frequency power source to excite the resonator with the signal so as to provide the plasma corona.

Abstract: An example system can include a combustion chamber of a power-generation gas turbine, a radio-frequency power source, a direct-current power source, a resonator, and a fuel conduit. The resonator can be electromagnetically coupled to the radio-frequency power source and have a resonant wavelength. Further, the resonator can include (i) a first conductor, (ii), a second conductor, and (iii) a dielectric between the first conductor and the second conductor. The resonator can be configured to provide at least one of a plasma corona or electromagnetic waves. The fuel conduit can be configured to couple to a fuel source and have a fuel outlet for expelling fuel into a combustion zone of the combustion chamber. A portion of the fuel conduit is disposed within the first conductor.

Abstract: An example system can include a combustion chamber of a power-generation gas turbine, a radio-frequency power source, a resonator, and a fuel conduit. The resonator can be electromagnetically coupled to the radio-frequency power source and have a resonant wavelength. Further, the resonator can include (i) a first conductor, (ii), a second conductor, and (iii) a dielectric between the first conductor and the second conductor. The resonator can be configured such that, when the resonator is excited by the radio-frequency power source with a signal having a wavelength proximate to an odd-integer multiple of one-quarter of the resonant wavelength, the resonator provides at least one of a plasma corona or electromagnetic waves. The fuel conduit can be configured to couple to a fuel source and have a fuel outlet for expelling fuel into a combustion zone of the combustion chamber. A portion of the fuel conduit is arranged proximate to the dielectric.

Abstract: An example system can include a combustion chamber of a power-generation gas turbine, one or more radio-frequency power sources, a plurality of resonators, and a fuel conduit. The plurality of resonators can be electromagnetically coupled to the one or more radio-frequency power sources and each have a respective resonant wavelength. Further, each resonator can include (i) a respective first conductor, (ii) a respective second conductor, and (iii) a respective dielectric between the first conductor and the second conductor, and can be configured to provide at least one of a plasma corona or electromagnetic waves. The fuel conduit can be configured to couple to a fuel source and have a fuel outlet for expelling fuel into a combustion zone of the combustion chamber. A portion of the fuel conduit is disposed within the first conductor of a given resonator of the plurality of resonators.

Abstract: A system includes a radio-frequency power source, a resonator, a fuel outlet, and an afterburner. The afterburner includes a duct that defines a channel, and can receive gas from a turbine of a jet engine into the channel and output a gas resulting from combusting fuel within the channel. The resonator can be configured to be electromagnetically coupled to the power source and has a resonant wavelength. The resonator includes first and second conductors, a dielectric between the first and second conductors, and an electrode coupled to the first conductor and disposed within the afterburner. The fuel outlet outputs fuel into the channel for mixing with the gas from the turbine. The resonator, when excited by the power source with a signal having a wavelength proximate to an odd-integer multiple of one-quarter of the resonant wavelength, provides electromagnetic waves and/or a plasma corona proximate to a concentrator of the electrode.

Abstract: An example system can include a combustor of a jet turbine engine, a radio-frequency power source, a plasma-distributing structure, and a resonator having a first concentrator. The combustor can include one or more fins protruding into a combustion zone and can be configured to guide combustion of fuel along a flame path defined by the fin(s). The resonator can be configured to provide a plasma corona when excited by the power source. The plasma-distributing structure can be arranged within the combustor and proximate to the plasma corona, and can include a second concentrator. When the resonator is excited, the plasma corona can be provided proximate to the first concentrator. Further, when the plasma corona is provided proximate to the first concentrator and the plasma-distributing structure is at a predetermined voltage, an additional plasma corona can be established proximate to the second concentrator and at least partly within the flame path.

Abstract: An example system can include a combustor of a power-generation turbine, a radio-frequency power source, a plasma-distributing structure, and a resonator having a first concentrator. The combustor can include one or more fins protruding into a combustion zone and can be configured to guide combustion of fuel along a flame path defined by the fin(s). The resonator can be configured to provide a plasma corona when excited by the power source. The plasma-distributing structure can be arranged within the combustor and proximate to the plasma corona, and can include a second concentrator. When the resonator is excited, the plasma corona can be provided proximate to the first concentrator. Further, when the plasma corona is provided proximate to the first concentrator and the plasma-distributing structure is at a predetermined voltage, an additional plasma corona can be established proximate to the second concentrator and at least partly within the flame path.

Abstract: An example system and corresponding method includes a jet engine combustor and a resonator. The combustor includes (i) a combustion zone, (ii) one or more fuel inlets for introducing fuel into the combustion zone for combustion, and (iii) one or more fins protruding into the combustion zone and configured to guide combustion of the fuel along a flame path. The resonator can have a resonant wavelength and can provide a plasma corona in the combustion zone when excited with a signal having a wavelength proximate to an odd-integer multiple of one-quarter (¼) of the resonant wavelength. A radio-frequency power source can excite the resonator with the signal so as to provide the plasma corona in the combustion zone and cause combustion of the fuel along the flame path.

Abstract: An example system and corresponding method includes a jet engine combustor and a plurality of resonators. The combustor includes (i) a combustion zone, (ii) one or more fuel inlets for introducing fuel into the combustion zone for combustion, and (iii) one or more fins protruding into the combustion zone and configured to guide combustion of the fuel along a flame path. The resonators can each have a respective resonant wavelength and can each provide a respective plasma corona in the combustion zone when excited with a respective signal having a wavelength proximate to an odd-integer multiple of one-quarter (¼) of the respective resonant wavelength. A radio-frequency power source can excite the resonators with the respective signals so as to provide the respective plasma coronas in the combustion zone and cause combustion of the fuel along the flame path.