Abstract: An inlet assembly for a high-mach engine includes a gas turbine core, an inlet turbine, and a core-flow director. When in a closed position, the core-flow director forces air to interact with the inlet turbine before entering the gas turbine core.

Abstract: A gas turbine engine includes a fan, a compressor, a combustor, a turbine, a bypass duct, and a bearing compartment assembly. The bearing compartment assembly includes a fluid pump, a compartment, a fluid line between the fluid pump and the compartment, and a damper check valve located in the fluid line. The damper check valve is a unitary, monolithic component that is configured to restrict a reverse flow from the compartment to the fluid pump substantially more than the damper check valve restricts a standard flow from the fluid pump to the compartment.

Abstract: The present disclosure relates generally to a manifold including a plurality of manifold channels disposed therethrough, each manifold channel including a manifold channel opening, and a seal plate, including a plurality of seal plate apertures disposed thereon, operably coupled to the manifold, wherein the seal plate includes at least one seal plate channel extending between at least two of the plurality of seal plate apertures.

Abstract: The present invention discloses a novel apparatus and methods for controlling an air injection system for augmenting the power of a gas turbine engine, improving gas turbine engine operation, and reducing the response time necessary to meet changing demands of a power plant. Improvements in control of the air injection system include ways directed towards preheating the air injection system, including using an gas turbine components, such as an inlet bleed heat system to aid in the preheating process.

Abstract: A method of modulating cooling flow to an engine component based on a health of the component is provided. The method includes determining a cooling flow requirement of the engine component for each of a plurality of operating conditions and channeling the determined required flow to the engine component during each respective operating condition of the plurality of operating conditions. The method also includes assessing a health of the engine component. The method further includes modifying the determined cooling flow requirement based on the assessed health of the engine component, and supplying the modified cooling flow requirement to the engine component during each subsequent respective operating condition of the plurality of operating conditions.

Abstract: A modular gas turbine system is disclosed. The system includes a base plate and a gas turbine engine mounted on the base plate. The gas turbine engine has a rotation axis, a first air compressor section and a second air compressor section. A rotating load is mechanically coupled to the gas turbine engine and mounted on the base plate. A supporting frame extends above the base plate and supports a plurality of secondary coolers, which are fluid exchange relationship with an intercooler of the gas turbine engine.

Abstract: An exemplary gas turbine engine includes a fan bypass duct defined between a fan nacelle and core cowl of an engine core. The engine core includes a cooled cooling air system configured to receive cooling air from a primary flowpath bleed at a diffuser within the engine core and configured to provide cooled cooling air to at least one component within the engine core. The cooled cooling air system including an air-air heat exchanger.

Abstract: Features and methods for modulating a flow of cooling fluid to gas turbine engine components are provided. In one embodiment, an airfoil is provided having a flow modulation insert for modulating a flow of cooling fluid received in a cavity of a body of the airfoil. In another embodiment, a shroud is provided comprising a cooling channel for a flow of cooling fluid and an insert that varies in position to modulate the flow of cooling fluid through the cooling channel. In yet another embodiment, a method for operating a gas turbine engine having a cooling circuit for cooling one or more components of the gas turbine engine comprises increasing power provided to the engine and decreasing power provided to the engine to modulate a position of a flow modulation insert located in the cooling circuit and thereby modulate the flow of cooling fluid through the cooling circuit.

Abstract: A first cooling stage is fluidly coupled to a bleed port of a compressor to receive and cool bleed air with the air stream to produce a cool bleed air. A cooling pump receives and increases a pressure of the cool bleed air to produce a pressurized cool bleed air. A second cooling stage is fluidly coupled to the pump to receive and cool the pressurized cool bleed air to produce an intercooled cooling air. A valve is downstream of the first cooling stage, the valve selectively delivering air into a mixing chamber where it is mixed with air from a tap that is compressed to a higher pressure than the air from the bleed port, and the valve also selectively supplying air from the first cooling stage to a use on an aircraft associated with the gas turbine engine. A method is also disclosed.

Abstract: A gas turbine engine according to an example of the present disclosure includes, among other things, a fan situated at an inlet of a bypass passage, and a core engine configured to drive the fan. The core engine includes a low pressure compressor section driven by a low pressure turbine section, and a high pressure compressor section driven by a high pressure turbine section. The fan has a fan diameter, Dfan, and the high pressure compressor section has a compressor diameter, Dcomp. The fan diameter Dfan and the compressor diameter Dcomp have an interdependence represented by a scalable ratio Dfan/Dcomp that is greater than about 4.5.

Abstract: A gas turbine engine typically includes a fan section, a compressor section, a combustor section and a turbine section. A speed reduction device such as an epicyclical gear assembly may be utilized to drive the fan section such that the fan section may rotate at a speed different than the turbine section so as to increase the overall propulsive efficiency of the engine. In such engine architectures, a shaft driven by one of the turbine sections provides an input to the epicyclical gear assembly that drives the fan section at a speed different than the turbine section such that both the turbine section and the fan section can rotate at closer to optimal speeds providing increased performance attributes and performance by desirable combinations of the disclosed features of the various components of the described and disclosed gas turbine engine.

Abstract: A turbofan engine according to an example of the present disclosure includes, among other things, an engine case and a gaspath through the engine case. A fan has a circumferential array of fan blades. The engine further has a compressor, a combustor, a gas generating turbine, and a low pressure turbine section. A speed reduction mechanism couples the low pressure turbine section to the fan. A bypass area ratio is greater than about 6.0. The low pressure turbine section airfoil count to bypass area ratio is below about 170.

Abstract: A gas turbine engine includes: an engine core, compressor system, and core shaft. A compressor exit pressure is defined as an average airflow pressure at the exit of the highest pressure compressor at cruise conditions. The core has an annular splitter and bypass flow. Stagnation streamlines around the engine circumference form a streamsurface. A fan is upstream the core with blades having leading and trailing edges, and a radially inner portion within the streamtube. A fan root entry pressure is an average airflow pressure across the radially inner portion leading edge of each fan blade at cruise conditions. An overall pressure ratio, OPR, is defined as the compressor exit pressure divided by the fan root entry pressure. A bypass jet velocity is defined as the jet velocity of air flow exiting the bypass exhaust nozzle at cruise conditions. A jet velocity to OPR ratio is in a range between 4.7 m/s and 7.7 m/s.

Abstract: An engine bleed control system for a gas turbine engine of an aircraft is provided. The engine bleed control system includes a multi-tap bleed array including engine bleed taps coupled to a compressor source of a lower pressure compressor section before a highest pressure compressor section of the gas turbine engine. A highest stage of the engine bleed taps has a maximum bleed temperature below an auto-ignition point of a fuel-air mixture of the aircraft at idle engine power at a maximum aircraft altitude and a pressure suitable for pressurizing the aircraft at the maximum aircraft altitude. The engine bleed control system also includes a plurality of valves operable to extract bleed air from each of the engine bleed taps. A controller is operable to selectively open and close each of the valves based on a bleed air demand and control delivery of the bleed air to an aircraft use.

Abstract: The gas turbine combustor and the operation method thereof are designed to minimize visualization of exhaust gas from the gas turbine upon switching of the gas turbine fuel from the oil fuel to the gas fuel. Upon switching of the combustion by the pilot burner from the oil burning to the gas burning, the gas fuel is supplied to the main burners so as to start the gas burning. Then the gas fuel is supplied to the pilot burner to start the gas burning.

Abstract: A method for operating a gas turbine installation with a measured compressor inlet temperature (Ti-actual) and a virtually constant turbine inlet temperature (TiTiso), wherein to provide safe operation of the gas turbine installation, an increase in a calculated exhaust gas temperature (ATK) is compensated by a reduced mass flow (m) of a flow medium flowing through a compressor of the gas turbine installation. An arrangement for operating the gas turbine installation includes a functional unit and a gas turbine installation with a compressor, a turbine, a control system for operating the method.

Abstract: An engine promoting activation of a catalyst is provided, including an exhaust manifold, an exhaust lead-out path led out from a manifold exit of the exhaust manifold, a catalyst case provided on the exhaust lead-out path, and a catalyst housed in the catalyst case. The exhaust manifold and the catalyst case are extended in the front-back direction of crankshaft extension and disposed side by side orthogonally to the front-back direction. The engine may further include a supercharger attached to the exit of the exhaust manifold, and the catalyst case is attached to a turbine exit of the supercharger. The engine may further include an exhaust relay pipe attached to the exit of the exhaust manifold, and the catalyst case is attached to a relay pipe exit of the exhaust relay pipe. The engine may further include an exhaust throttle device provided on an exhaust downstream side of the catalyst.

Abstract: A variable exhaust valve assembly for a vehicle includes an exhaust housing, a power transmission device that transmits rotational power, a shaft that extends through the exhaust housing and is coupled with a valve so as to open and close the exhaust housing, and a heat shielding unit to reduce heat transfer between the power transmission device and the exhaust housing. The power transmission device is configured to regulate an opening degree of the valve. The variable exhaust valve assembly is improved in durability by minimizing damage to power transmission caused by high-temperature heat of exhaust gas, and reducing vibration transmitted to the power transmission device.

Abstract: Methods and systems are provided for maintaining a compression ratio of an engine via a brake and while disabling an electric current applied to an actuator of the associated variable compression ratio mechanism. A braking force applied via the brake on a compression ratio control shaft is varied before and during a compression ratio transition to move the control shaft at a desired velocity. Brake torque application is coordinated with motor torque from a VCR actuator and engine torque applied on the control shaft to enable a smooth CR transition.

Abstract: Methods and systems are provided for a fuel supply system for an internal combustion engine system, in particular of a motor vehicle, having at least one liquefied petroleum gas (LPG) tank for storing an LPG fuel and at least one direct injection unit, which has a direct injection fuel distributor and direct injection valves that can be supplied with fuel via said distributor. In order to improve supply of the internal combustion engine system with LPG fuel, the fuel supply system includes a booster pump inserted between the LPG tank and the direct injection fuel distributor. A discharge side of the booster pump is connected directly to the direct injection fuel distributor by at least one line, and the direct injection valves each have a closure part that rises outward from a valve seat to open the respective direct injection valve.

Abstract: A method for a knock control for an internal combustion engine with at least one cylinder, which is assigned to at least one intake valve, when knocking occurs in at least one cylinder by actuation of the intake valve associated with the cylinder detected as knocking, in such a way that the temperature of the charge of the cylinder detected as knocking is reduced, the knocking in the cylinder is reduced, on actuating the intake valve associated with the cylinder detected as knocking, a cylinder-specific and/or a global measure for power compensation of the internal combustion engine is performed.

Abstract: A method for establishing a permitted maximum differential pressure of an air filter arranged in an intake tract of an internal combustion engine is provided. The method includes determining a control reserve of the internal combustion engine and establishing the maximum permissible differential pressure of the air filter as a function of the determined control reserve.

Abstract: Various methods and systems are provided for estimating fresh intake air flow. In one example, a system comprises an engine having an intake manifold to receive fresh intake air and an exhaust gas recirculation (EGR) system to supply EGR to the intake manifold, where flow of EGR through the EGR system is controlled by one or more exhaust valves. The system further includes a controller configured to adjust a position of the one or more exhaust valves based on an estimated fresh intake air flow rate, where during a first set of operating conditions, the fresh intake air flow rate is estimated based on a total gas flow rate into the engine and further based on a current position of the one or more exhaust valves, intake manifold pressure, air-fuel ratio, and fuel flow to one or more cylinders of the engine.

Abstract: An exhaust gas recirculation (EGR) control method includes a valve duty differentiated control including: detecting, by a controller, an engine operation region, a mixer region, and an external factor region as a valve control condition for an EGR valve duty correction variable for controlling an EGR system; applying, by the controller, the EGR valve duty correction variable to an EGR valve duty, which is set by a target air amount to an intake air amount, to calculate a minimum EGR valve duty; and outputting, by the controller, the calculated minimum EGR valve duty to an EGR valve as the EGR valve duty.

Abstract: A power system is disclosed. The power system may include one or more memories and a controller. The controller may determine an exhaust temperature of an engine associated with a continuously variable transmission or a hybrid transmission. The controller may determine a target increase to the exhaust temperature based on the exhaust temperature failing to satisfy a threshold. The controller may determine, based on a lookup table, a target increase to a torque output of the engine based on the target increase to the exhaust temperature. The controller may cause a parasitic torque of the engine to be increased based on the target increase to the torque output.

Abstract: An engine control system and method of controlling an engine system are provided. The engine control system includes at least one sensor module configured to generate an exhaust condition signal based on a determined condition in an exhaust component and a cylinder bank control module communicatively coupled to the at least one sensor module. The cylinder bank control module is configured to cause transmission of a first bank control signal to cause a first bank of cylinders of an engine to deactivate at least in part in response to a determination based on the exhaust condition signal that a hydrocarbon mass quantity is above a pre-determined hydrocarbon mass quantity threshold.

Abstract: An apparatus and method for controlling deactivation of cylinders in an engine may include a sensor that measures pressure inside an intake manifold of the engine, an oil control valve (OCV) that deactivates the cylinders in the engine, and a controller that is configured to control the OCV to deactivate a specific cylinder in the engine, based on the pressure inside the intake manifold.

Abstract: Methods and systems are provided for a particulate filter comprising a pretreatment. In one example, a method may include applying a pretreatment to an unused particulate filter, wherein the particulate filter is subjected to incomplete oxidation conditions following application of the pretreatment.

Abstract: In some examples, a system including one or more processors may receive sensor data from one or more sensors indicating one or more engine parameters of an engine including a combustion chamber. Based on the sensor data, the system may determine a homogeneity index indicative of a homogeneity of an air-fuel mixture within the combustion chamber. Furthermore, the system may determine an estimated amount of NOx in the exhaust gas based at least in part on the homogeneity index. In addition, based at least partially on the estimated amount of NOx in the exhaust gas, the system may send an instruction to control an engine component.

Abstract: The invention relates to a method for adjusting a fuel/air ratio of an internal combustion engine (10), comprising a catalyst volume (26) with a first catalyst partial volume (26.1) and a second catalyst partial volume (26.2). The second catalyst partial volume (26.2) is arranged downstream from the first catalyst partial volume (26.1). An actual filling level of an exhaust gas constituent in the catalyst volume (26) is calculated from operating parameters of the internal combustion engine (10) and the exhaust system (14) using a computing model, and is adjusted to a nominal value by modifying the fuel/air ratio. The adjustment is carried out first for the second catalyst partial volume (26.2) and only later for the first catalyst partial volume (26.1).

Abstract: Methods and systems are provided for increasing an efficiency of a purging operation of a fuel vapor storage canister of a vehicle, the fuel vapor storage canister configured to capture and store fuel vapors stemming from a fuel tank of the vehicle. As one example, a method comprises reactivating one or more cylinders of an engine during a purging operation, in response to an indication that the purging of stored fuel vapors from the fuel vapor storage canister is compromised as a result of fuel vaporization stemming from the fuel tank. In this way, the canister may be effectively cleaned even under high fuel vaporization circumstances, which may improve fuel economy and may reduce release of undesired evaporative emissions to atmosphere.

Abstract: An integrated ignition and electronic auto-choke module for an internal combustion engine and an internal combustion engine including the same. In one aspect, the module includes a housing that is configured to be mounted to an engine block of an internal combustion engine. The housing may contain at least a portion of a first temperature sensor that measures a first temperature indicative of an engine temperature. The housing may also contain a controller and at least a portion of an ignition circuit. The controller may be coupled to the first temperature sensor and configured to determine a starting position of a choke valve based on the first temperature and operate an actuator to move the choke valve into the starting position accordingly.

Abstract: An unequal-interval combustion engine misfire-determination device determines whether a misfire has occurred in an unequal-interval combustion engine including a plurality of cylinders in which combustion occurs at unequal intervals.

Abstract: A method for diagnosing the operation of an injector of a diesel engine of a vehicle, controlled by a plurality of control laws on the basis of at least one operating parameter of the injector for each control law. The method includes a step of measuring an operating parameter value during use of the injector, a step of determining an efficiency value of each control law on the basis of the measured value of the parameter and of a predetermined reference curve representing the efficiency of the parameter in its interval of operating values, and a step of determining an efficiency value of the injector on the basis of the efficiency value of each of the control laws.

Abstract: A control system for a compression ignition engine is provided, which includes a combustion chamber, a throttle valve, an injector, an ignition, a swirl control valve, a sensor and a controller. The controller is configured to execute a first mode module, a second mode module, and a changing module to change an engine mode from a first mode to a second mode in response to a change demand. The changing module outputs signals to the throttle valve and the injector in response to the demand so that an air-fuel ratio of mixture gas becomes a stoichiometric air-fuel ratio, and outputs a signal to the swirl control valve so that an EGR gas amount decreases more than before the demand, and when the EGR gas amount is determined to be decreased to a given amount, the changing module causes the second mode module to start the second mode.

Abstract: A control device for a compression-ignition engine in which partial compression-ignition combustion including spark ignition (SI) combustion performed by combusting a portion of a mixture gas inside a cylinder by spark-ignition followed by compression ignition (CI) combustion performed by causing the remaining mixture gas to self-ignite is executed at least within a part of an engine operating range is provided, which includes a detector configured to detect a given parameter that changes as combustion progresses inside the cylinder, an A/F (air-fuel ratio) controller configured to change an air-fuel ratio of air to fuel introduced into the cylinder, and a combustion controller configured to determine combustion stability based on the detected parameter of the detector and control the A/F controller to reduce the air-fuel ratio when it is confirmed that during the partial compression-ignition combustion the combustion stability is low.

Abstract: A method for operating an electronically commutated fuel pump with an upstream fuel pump electronics unit of a motor vehicle, wherein the fuel pump is operated at a predefined speed, the method includes detecting a speed irregularity of the electronically commutated fuel pump, the speed irregularity being determined by examining the synchronicity between rotary field and rotor of the fuel pump, and switching over the speed of the electronically commutated fuel pump to a higher speed value than the predefined speed until a stable operation of the fuel pump without loss of synchronicity between rotary field and rotor of the fuel pump is achieved, the switchover of the fuel pump to the higher speed is performed by a predefined speed jump or is performed at predefined speed steps, the speed being increased until stable operation of the fuel pump is achieved.

Abstract: A method for operating an internal combustion engine, in which fuel is supplied to the internal combustion engine by a rotary pump, and the speed of the pump and/or the electrical current for feeding the pump (pump current) is controlled in accordance with a requirement variable, taking into account a determination specification. When in an overrun mode, a calibration is carried out and the speed of the pump is detected and is maintained during the calibration step. Once the triggering pressure for a calibration valve, arranged on the high-pressure side of the pump, has been reached, the pump current is detected and the determined speed and the determined pump current are used to calibrate the determination specification. A calibration in the overrun mode is performed without alteration to the speed of the fuel pump. This prevents a variable behaviour of the fuel pump which might produce undesired operating conditions.

Abstract: Methods and systems for simultaneously operating port fuel injectors and direct fuel injectors of an internal combustion engine are described. In one example, port fuel injection timing is adjusted to reduce particulate matter formation in the engine so that particulate filter loading may be reduced until a time when the particulate filter may be purged.

Abstract: An estimation device is applicable to a combustion system including an internal combustion engine and includes a mixing acquisition unit, a main region estimation unit, and an after region estimation unit. The mixing acquisition unit acquires a mixing ratio of various components contained in the fuel used for combustion in the internal combustion engine. The main region estimation unit estimates a combustion region of the fuel as a main combustion region for a main combustion produced by injecting the fuel into a combustion chamber of the internal combustion engine by main injection, based on the mixing ratio acquired by the mixing acquisition unit. The after region estimation unit estimates an injection region of the fuel as the after combustion region based on the mixing ratio, for an after combustion produced by injecting the fuel into the combustion chamber by an after injection, after the main injection in one combustion cycle.

Abstract: Various embodiments include a method for operating an internal combustion engine comprising: determining a torque output of each cylinder resulting from a fuel injection; determining a difference in the respective torque output; comparing the difference with a predetermined threshold; determining a respective injection mass; determining a difference in the respective injection masses; comparing the difference with a threshold; if the differences exceed the threshold, determining whether the respective torque outputs correspond to the associated injection mass; and if the respective torque outputs lie outside a predetermined tolerance range for a respective corresponding injection mass, changing an injection time in at least one of the at least two cylinders.

Abstract: A compression-ignition engine control system is provided, which includes an intake phase-variable mechanism and a controller. The controller controls the intake phase-variable mechanism to form a gas-fuel ratio (G/F) lean environment in which burnt gas remains inside a cylinder and an air-fuel ratio is near a stoichiometric air-fuel ratio, and controls the spark plug to spark-ignite the mixture gas to combust in a partial compression-ignition combustion. The controller controls the intake phase-variable mechanism to retard, as an engine speed increases at a constant engine load, an intake valve close timing on a retarding side of BDC of intake stroke and an intake valve open timing on an advancing side of TDC of exhaust stroke, and controls the intake phase-variable mechanism so that a change rate in the intake valve open timing according to the engine speed becomes larger in a high engine speed range.

Abstract: Provided is a spacer configured such that a protruding portion remaining after removal of a portion unnecessary after molding does not contact an inner wall of a coolant water flow path and therefore, even a portion of the spacer in the vicinity of the remaining portion can be positioned close to the cylinder bore side inner wall. The spacer of this embodiment is a spacer (4) formed of a resin molded body and inserted, in use, into a coolant water flow path (3) through an opening (30) of the coolant water flow path (3) that is formed around a plurality of cylinder bores (2) formed adjacent to each other in a cylinder block (1) of an internal combustion engine. The spacer (4) includes a spacer body (40) formed in a cylindrical shape to surround the cylinder bores (2), and a protruding remaining portion (5) remaining after removal of a portion (6ba) necessary in molding and unnecessary after molding.

Abstract: A heat engine with a dynamically controllable hydraulic outlet driven by a high-pressure pump and a gas turbine that include a pressure vessel (1), a lid (1.1), a movable partition (2), a gas working space (4), a liquid working space (5), and a recuperator (7), wherein a sealing (1.4) is disposed between the pressure vessel (1) and the lid (1.1), wherein in the inner space of the pressure vessel (1) the partition (2) is movably attached to a folded membrane (3) which is attached to the lid (1.1), wherein the partition (2) divides the inner space of the pressure vessel (1) into the gas working space (4) and the liquid working space (5), and shaped parts (1.8) are arranged within the pressure vessel, which define an external gas channel (10) which is led between a shell of the pressure vessel (1) and the shaped parts.

Abstract: A blocker door assembly for use in a gas turbine engine includes a facesheet including a plurality of openings to facilitate noise attenuation and a body portion coupled to the facesheet. The body portion includes a backsheet integrally formed with a honeycomb core, wherein the body portion is molded from a thermoplastic material.

Abstract: A thrust reverser system for a gas turbine engine includes a transcowl movable between a stowed position, a deployed position and a partially deployed position between the stowed position and the deployed position by at least one actuator. The system includes a temperature sensor and at least one resistance sensor. The thrust reverser system includes a controller, having a processor, that: outputs one or more control signals to move the transcowl to the partially deployed position; determines whether a temperature associated with the transcowl exceeds a temperature threshold; outputs one or more control signals to move the transcowl from the partially deployed position to the stowed position; determines whether the transcowl has encountered resistance; and based on the determination, outputs one or more control signals to stop a movement of the transcowl and outputs the one or more control signals to move the transcowl to the partially deployed position.

Abstract: An assembly is provided for an aircraft propulsion system. This assembly includes a fixed structure, a translating structure, a blocker door and a folding linkage. The translating structure is configured to move between a stowed position and a deployed position. The blocker door is pivotally attached to the translating structure at a first pivot joint. The folding linkage links the blocker door to the fixed structure. The folding linkage includes a member pivotally attached to the blocker door at a second pivot joint that is radially outboard of a skin of the blocker door when the translating structure is in the stowed position. The second pivot joint is radially outboard of the first pivot joint when the translating structure is in the stowed position.

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

Abstract: A gas turbine engine may include a high pressure compressor coupled to a high pressure turbine by a high pressure shaft, a core combustor located downstream of the high pressure compressor and upstream of the high pressure turbine, and a low pressure compressor provided upstream of the high pressure compressor. The low pressure compressor may be configured to direct core airflow to the high pressure compressor and first bypass airflow which bypasses the high pressure compressor, core combustor and high pressure turbine through a first bypass duct. The engine may further include a mixer downstream of the high pressure turbine and low pressure compressor, the mixer being configured to mix the core and first bypass airflows. The engine also may include a re-heat combustor configured to combust fuel with both core airflow and first bypass airflow.

Abstract: A scramjet includes a converging inlet, a combustor configured to introduce a fuel stream into an air stream in a combustion chamber and to combust the fuel air mixture stream to create an exhaust stream, and a diverging exit nozzle configured to accelerate the exhaust stream. The combustor includes a fuel injection system including at least one arcjet. A method of creating thrust for an aircraft includes compressing a supersonic incoming air stream in a converging inlet, injecting a fuel stream into the air stream in a combustion chamber to create a fuel air mixture stream, igniting the fuel air mixture stream to create an exhaust stream, and exhausting the exhaust stream from a diverging exit nozzle. The injecting the fuel stream into the air stream includes injecting the fuel stream at a fuel speed sufficient to create shear between the fuel stream and the air stream.