252 results about "Engine knocking" patented technology

The invention discloses a high-horsepower fuel oil dune buggy gas supply assembly, and belongs to the technical field of internal combustion engine gas inlet systems, the high-horsepower fuel oil dune buggy gas supply assembly comprises an outer cover, a sealed space is limited in the outer cover, and the outer cover is provided with a gas inlet head and a gas exhaust head; the inner container is arranged in the sealed space of the outer cover, and the inner container comprises a first inner shell and a second inner shell; and the pumping piece is arranged in the first inner shell and used for pressurizing air and pumping the air to the second inner shell. Through optimization of the overall structure, high-pressure airflow is generated through the pumping piece, air is physically separated into cold air and hot air in the vortex chamber, and cold air far lower than the environment temperature can be actively provided for an engine without any refrigerant and a complex compressor; the problems that the fuel oil dune buggy is low in inflation efficiency and high in detonation risk in a high-temperature environment are solved, strong, stable and continuous power is output, and power attenuation of the high-horsepower fuel oil dune buggy caused by high-temperature protection of an engine is relieved.

The invention relates to a control method based on low-temperature cold start of a heuristic integrated heavy oil engine, and relates to the field of heuristic integrated heavy oil engines. According to the technical scheme, the preheating plug in the cylinder is combined with the air inlet heating grid, synchronous control is achieved through the same relay, the electric energy requirements of synchronous work and dragging and preheating are met by means of sufficient battery capacity, and the device can be adapted to the ultra-low temperature of-40 DEG C or below and the plateau environment of 4700 m or above; three starting attempts are supported by single-time power-on through intelligent preheating control logic, the pre-preheating and heating-while-dragging processes are executed each time, fault information is automatically uploaded after starting fails, frequent power-off is not needed, and the starting efficiency is improved. And moreover, through an intermittent post-preheating and intake synchronous heating strategy, the combustion stability in the cylinder is effectively improved, the rotating speed fluctuation time is shortened, and mechanical damage caused by flameout and unstable idling after starting is avoided. In addition, the dragging rotating speed control based on the torque can prevent the problem of engine damage caused by accidental detonation after multiple starting failures.

The invention discloses a rotating detonation afterburner based on centrifugal nozzle discrete injection, and belongs to the technical field of detonation propulsion. The combustion chamber comprises a gas collecting cavity, an injection unit, a centrifugal nozzle, an outer ring and an inner column, wherein an annular detonation combustion chamber is formed between the inner wall surface of the outer ring and the outer wall surface of the inner column. The centrifugal nozzles are uniformly arranged at the intersection of the gas collection cavity and the injection unit in the circumferential direction to realize primary atomization of the fuel oil; the air is accelerated by the injection unit from the air collection cavity and then is mixed with the atomized fuel oil, secondary atomization is achieved, the particle size of liquid drops is remarkably reduced, and the fuel activity and mixing uniformity are improved. The injection unit adopts a Laval nozzle profile, air is accelerated to supersonic speed in the injection unit, and pressure of a combustion chamber is prevented from being transmitted forwards. The rotary detonation engine is suitable for the high-temperature low-oxygen environment, supports the annular combustion chamber configuration and the empty cylinder combustion chamber configuration, can achieve stable rotary detonation detonation and propagation of liquid fuel and air, and provides technical support for engineering application of the rotary detonation engine.

The invention discloses an ignition angle control method and device of an extended range engine, a vehicle and a storage medium, and the method comprises the steps that for each air cylinder of the extended range engine, the target correction amplitude corresponding to a current knock signal of the air cylinder is obtained, the absolute value of the target correction amplitude is not larger than the ideal correction amplitude, and the target knock signal of the air cylinder is obtained; the ideal correction amplitude is used for correcting an ignition angle and is a preset correction amplitude threshold value corresponding to a target interval to which current working condition parameters of the extended-range engine belong; according to a preset basic ignition angle of the extended-range engine and the target correction amplitude corresponding to the air cylinder, the target ignition angle of the air cylinder is obtained; ignition angle control is achieved through separate cylinders, each cylinder is combined with a current knock signal, a target ignition angle in a better state is obtained under different working condition parameters, oil consumption is reduced, and the performance of an engine is improved.

This can suppress the occurrence of water hammer within the cylinder. [Solution] The control device 90 of the internal combustion engine 1 controls the internal combustion engine 1, which includes a fuel pump 16 that pressurizes fuel and an injector 15 that supplies fuel into the cylinder 4 by injecting the fuel pressurized from the fuel pump 16. The control device 90 is configured to stop the operation of the fuel pump 16 when the degree of discrepancy between the output timing of a signal output from a knocking sensor 48, which is a sensor that detects the vibration state of the internal combustion engine 1, and the output timing of an injection command signal that drives the injector 15, is greater than a predetermined degree.

The application discloses an ammonia-hydrogen internal combustion engine knock suppression system and a knock suppression method, and belongs to the technical field of internal combustion engine combustion control. The suppression system comprises an ammonia gas supply unit, a hydrogen gas supply unit, a cylinder pressure sensor, a pressure sensor and an electronic control unit. The ammonia gas supply unit realizes ammonia gas supply in a cylinder. The hydrogen gas supply unit realizes hydrogen gas supply in the cylinder. The cylinder pressure sensor is used for monitoring the pressure in the cylinder in real time and calculating CA50. The pressure sensor is used for monitoring the knock intensity of the cylinder. The electronic control unit is electrically connected with the ammonia gas supply unit, the hydrogen gas supply unit, the cylinder pressure sensor and the pressure sensor respectively, is used for receiving sensor signals, calculating ammonia energy (AER) and knock intensity (KI), controlling the ignition time and dynamically adjusting the ammonia mixing ratio, realizing the collaborative optimization of knock suppression and thermal efficiency, and achieving the win-win effect of "knock suppression" and "efficiency increase".

The invention discloses a multi-wave rotary detonation engine isolation section analog calculation method based on a rotary heat source, which comprises the following steps: step 1, carrying out three-dimensional modeling on an isolation section to obtain an isolation section digital model; the isolation section digital model is at least provided with two heat sources, and the heat sources are used for simulating detonation waves rotating in the same direction or opposite directions; step 2, performing grid division on the isolation section digital model by using grid drawing software, and inputting the isolation section digital model after grid division into fluid simulation software; 3, giving a flow field control equation; and 4, giving boundary conditions, initial conditions, heat source motion conditions and heat source heat release conditions, and performing calculation simulation on the isolation section of the rotary detonation engine to obtain a simulation calculation result. Motion shock wave development and evolution structures in an isolation section under various combustion conditions of the multi-wave rotary detonation engine can be simulated, the applicable working conditions are rich, the simulation calculation method is simple in condition setting, the calculation stability is high, and high-precision calculation is adapted.

A method of fuel injector management based on cylinder knock detection includes: receiving an individual cylinder knock count from a first cylinder; determining whether a knock metric is initialized for the first cylinder, whether the knock metric deviates from an established baseline knock metric after multiple cycles when the knock metric is initialized for the first cylinder, whether the knock metric is decreasing with respect to the established baseline knock metric when the knock metric deviates from the established baseline knock metric, whether a fuel system memory indicates rich, lean or healthy when that the knock metric is decreasing with respect to the established baseline knock metric, whether a knock adaptation control indicates a reduction of knock for the first cylinder, and updating a health status of a fuel injector based on the indication of rich, lean, or healthy.

This application provides an engine combustion control method and apparatus, relating to the field of automotive engine technology. The method includes: responding to an engine start command issued by a hybrid vehicle, setting the engine control mode to a high-efficiency combustion control mode; calculating the intake air volume in the engine cylinders based on the vehicle's required torque; calculating the final boost pressure based on the intake air volume; controlling the speed of the electric supercharger based on the final boost pressure; determining the optimal injection frequency and fuel injection parameters for each engine operating condition based on the engine's full-map operating conditions and the intake air volume; and performing fuel injection and engine knock linkage control based on the optimal injection frequency and fuel injection parameters for each operating condition. The engine combustion control method and apparatus provided in this application can achieve efficient combustion of the hybrid engine in the vehicle, achieve optimal thermal efficiency, and enable smooth charging and driving of the vehicle.

The application relates to the field of aeroengines, in particular to a rotating detonation combustion chamber with a pressure regulating structure and an injection channel, comprising a duct shell, a combustion chamber body arranged in the duct shell and a Tesla valve arranged at the inlet of the combustion chamber body, the combustion chamber body being provided with an annular channel, the Tesla valve comprising a shell and a flow channel, one end of the shell being fixedly connected with one end of the duct shell, the other end of the shell being coaxially connected with the combustion chamber body, the flow channel being coaxially arranged in the shell, the inlet end of the flow channel being used for air inlet, and the outlet end of the flow channel being communicated with the annular channel in the combustion chamber body; the injection channel is formed between the duct shell, the shell and the combustion chamber body, the inlet end and the outlet end of the flow channel are both provided with a pressure regulating structure, the pressure regulating structure comprises a gas collection cavity and an air inlet hole used for connecting the gas collection cavity with the flow channel, and the injection channel is communicated with the gas collection cavity. The application has the effect of improving the problem that the pressure backflow causes the total pressure loss of the combustion chamber to be large.

Title: Control Unit and Method for Determining Backfire in the Intake Manifold of a Hydrogen Engine. The control unit 118 determines backfire in the intake manifold 110 of the vehicle's hydrogen engine. The intake manifold includes the hydrogen injector 112 and a pressure sensor 114. The hydrogen engine includes the knock sensor 106. Gaseous hydrogen is injected through the hydrogen injector 112 and sent to the engine cylinder. The control unit 118 is configured to detect the first signal indicating a hydrogen flame in the intake manifold 110 via the flame sensor 116. The control unit 118 measures the second and third signals via the pressure sensor 114 and the knock sensor 106, respectively.Control unit 118 validates and determines the presence of backfire based on the correlation of the first signal with the second and third signals. After determining backfire, control unit 118 takes control measures that reduce its occurrence. Figure 1 for the summary.

The application relates to the technical field of aero-engines, and provides a rotating detonation combustion chamber detonation wave propagation direction induced air intake pre-rotation structure which comprises an air intake shell, an air intake flow channel is arranged in the air intake shell, the air intake flow channel comprises an air intake passage, a connecting passage, an expansion passage and a backflow passage, one end of the air intake passage is used for introducing air and fuel, the other end is communicated with the connecting passage, the small end of the expansion passage is communicated with one end of the connecting passage away from the air intake passage, and the large end of the expansion passage is communicated with a combustion chamber; the inlet end of the backflow passage is communicated with one end of the connecting passage away from the expansion passage, and the outlet end of the backflow passage is communicated with the air intake passage; a plurality of guide vanes are arranged in the expansion passage and are arranged in a circumferential interval, and a pre-rotation passage for pre-rotating gas is formed between two adjacent guide vanes. The rotating detonation combustion chamber detonation wave propagation direction induced air intake pre-rotation structure can improve the control accuracy of the detonation wave mode in the combustion chamber.

The invention discloses an air film cooling structure and a rotary detonation engine, and relates to the technical field of rotary detonation engine thermal protection, the air film cooling structure comprises a cold air cavity and a Tesla valve type air film pipe, the Tesla valve type air film pipe comprises a main flow pipe, a flow dividing pipe and a collecting pipe, and an inlet of the flow dividing pipe is connected and communicated with the side portion of the main flow pipe; an outlet of the flow dividing pipe is connected and communicated with an inlet of the collecting pipe, an outlet of the main flow pipe is connected and communicated with the side portion of the collecting pipe, the main flow pipe and the collecting pipe are linear, the flow dividing pipe is an arc-shaped pipe and protrudes upwards relative to the collecting pipe, and an inlet of the main flow pipe is connected and communicated with the cold air cavity. And an outlet of the collecting pipe is connected and communicated with a combustion chamber of the rotary detonation engine. The rotary detonation engine comprises a combustion chamber and the air film cooling structure, and the combustion chamber is provided with a combustion inlet and a combustion outlet. According to the invention, high-temperature fuel gas anti-invasion can be inhibited when detonation waves pass through, the influence of high-temperature fuel gas on the cold air cavity is reduced, and the cooling efficiency is improved.

Method for preventing or reducing knock in a hydrogen fueled combustion engine is described. The steps of the method include lubricating the crankcase of the engine with a lubricating oil composition that includes from about 500 to about 2000 ppm of calcium from one or more phenolic-based calcium detergent, based on total weight of the lubricating oil composition.

This invention discloses a device and control method for maintaining uniform pressure and temperature in the engine intake chamber. The device includes a circulation pipe, with its two ends fixedly connected to the flywheel end and free end of the intake chamber, respectively. The intake passages of the first and last cylinders are connected to the intake chamber. Temperature and pressure detection devices are installed on both the first and last cylinder intake passages. A regulating valve is installed on the circulation pipe to adjust the flow rate of the boosted intercooled air in the circulation pipe. The detection devices are connected to the ECU, and the regulating valve is controlled by the ECU. The regulating valve is configured as an electronic throttle. The ECU monitors the intake pressure and temperature signals of each cylinder in real time, obtains a preset electronic throttle opening angle based on the temperature and pressure differences, and controls the opening angle of the electronic throttle according to the preset angle. This precisely controls and adjusts the flow rate of the boosted intercooled air in the circulation pipe, ensuring uniform intake pressure and temperature in each cylinder, improving engine knock pressure uniformity, exhaust temperature uniformity, and reducing vibration.

The application provides a rotating detonation combustion chamber inner cylinder end face pressure testing device under axial air inlet and radial air inlet conditions, which comprises an end cover (1), an inner cylinder (2), an axial air inlet outer cylinder (3), a connecting sheet (4), an adapter section (5), a pressure measuring tube (6), a blind plate (7) and a radial air inlet outer cylinder (8); the end cover (1), the inner cylinder (2) and the stainless steel pressure measuring tube (6) are common structures, the axial air inlet outer cylinder (3), the connecting sheet (4) and the adapter section (5) are structures used under axial air inlet conditions, and the blind plate (7) and the radial air inlet outer cylinder (8) are structures used under radial air inlet conditions. The end cover is provided with a static pressure measuring point, and the pressure is led out through the stainless steel pressure measuring tube (6) for measurement. The end face static pressure value can be obtained under the condition of not affecting the tail flow field, and the bottom resistance is calculated.

Systems and methods are provided herein useful to thrust augmentation in a gas turbine engine. In some embodiments, the systems include augmentors that incorporate a rotating detonation architecture. An exhaust system of a gas turbine engine includes an augmentor and a peripheral wall surrounding an exhaust system core. The augmentor comprises a detonation chamber disposed within the exhaust system core. The detonation chamber includes a channel formed in the peripheral wall. A core inlet path delivers a core air-fuel mixture and a pilot inlet path delivers a pilot air-fuel mixture to the detonation chamber. The core air-fuel mixture combusts in the detonation chamber along the midline the detonation chamber. The pilot air-fuel mixture detonates in the detonation chamber adjacent the peripheral wall to create a rotating detonation wave that supports the combustion reaction occurring along the midline of the detonation chamber.

The invention provides an air inlet method, a detonation engine using the method and a rotary detonation engine, and the air inlet method comprises the steps that fuel is injected to the downstream area of a combustion device through a fuel nozzle to form a jet flow curtain, and the jet flow curtain and the combustion device are enclosed to form a closed space or a semi-closed space; the closed space or the semi-closed space is injected through the jet flow curtain, so that the closed space or the semi-closed space circularly reciprocates to form a low-pressure state to realize high-frequency air inlet; according to the detonation engine and the rotary detonation engine using the air inlet method, fuel is injected through the fuel nozzle to form a jet flow curtain, the jet flow curtain, the combustion chamber and the reflector define a closed space or a semi-closed space, and injection is conducted on the closed space or the semi-closed space through the jet flow curtain; and the closed space or the semi-closed space circularly reciprocates to form a low-pressure state so as to realize high-frequency air intake. The invention can be applied to the fields of power propulsion and rotation torque generation.

The invention relates to the technical field of vehicles, and provides an engine control device and a humidity measuring method. The method comprises the following steps: detecting the actual pump current of the wide-range front oxygen sensor in the current state; obtaining the theoretical pump current of the wide-area front oxygen sensor; comparing a current difference value Dip between the actual pump current and the theoretical pump current with a set threshold value, and if the current difference value is greater than the set threshold value, entering the next step; when the engine is in the humidity detection working condition, a natural gas injection quantity coefficient and a knock intensity indication coefficient are collected and are subtracted from corresponding preset standard values, and a knock difference value and a natural gas injection quantity difference value are obtained; calculating the relative humidity of the intake air of the engine; and by searching a preset conversion table of the relative humidity and the absolute humidity, obtaining the target humidity of the intake air of the engine. The technical problems that an intake oxygen sensor and an air mass flow sensor need to be additionally installed in traditional engine humidity measurement, the structure is complex, cost is high, and reliability is insufficient are solved.

The invention discloses a camshaft deviation determination method and device, a vehicle, a medium and a product. The method comprises the steps that multiple sets of actually-measured seating knock data are obtained, and the seating knock data are data collected when an engine is in a reverse towing state and an ignition signal is shielded; according to vibration amplitude difference characteristics of the engine between each group of actually measured seating knock data and standard seating knock data, a plurality of correlation coefficients of each group of actually measured seating knock data and a crank angle corresponding to each correlation coefficient are determined, and the standard seating knock data are seating knock data when no camshaft deviation exists; and determining the camshaft deviation according to the plurality of correlation coefficients of each group of actually measured seating knock data and the crank angle corresponding to each correlation coefficient. According to the technical scheme, the camshaft deviation can be determined more accurately.

The invention relates to the technical field of aerospace engines, in particular to an axial expansion combustion chamber and a rotary detonation engine, which comprise a base, a gas distribution assembly and an axial expansion combustion chamber which are coaxially and sequentially arranged along the axial direction, the axial expansion combustion chamber is improved aiming at the technical defect that the flow speed of supersonic airflow in an existing uniform-section combustion chamber is reduced due to the gas dynamic effect and the wall surface heat sink effect, so that the inner wall of the axial expansion combustion chamber expands outwards in the axial direction of the airflow; therefore, the sectional area of an inner channel of the axial expansion combustion chamber is gradually expanded in the axial direction, and an expansion type flow channel is formed. Compared with the prior art, the inner channel has the beneficial effects that through the physical geometric structure change of axial expansion of the inner channel, the total pressure loss and speed attenuation of airflow in the flowing process are successfully compensated, the energy release efficiency in the combustion chamber is remarkably improved, and the self-sustaining capacity of an engine in the combustion process is effectively enhanced.

The controller (118) determines backfire in the intake manifold (110) of the hydrogen engine of the vehicle. The intake manifold (110) comprises the hydrogen injector (112) and a pressure sensor 114. The hydrogen engine comprise the knock sensor (106). The hydrogen gas is injected via the hydrogen injector (112) and supplied to the engine cylinder of the engine and the controller (118) is configured to detects the first signal which indicates the hydrogen flame in the intake manifold (110) through the flame sensor (116). The controller (118) measures the second signal and the third signal through the pressure sensor (114) and the knock sensor (106), respectively. The controller (118) validates and determines presence of the backfire based on correlation of the first signal with the second signal and the third signal. Upon backfire determination, the controller (118) takes control measures which mitigates the backfire occurrence.

In one instance, disclosed herein is an engine system, comprising: an engine comprising a plurality of engine cylinders; and a controller operative to: control a respective ignition timing for each engine cylinder of the plurality of engine cylinders; detect an increase of a knock intensity of the engine; after detecting the increase of the knock intensity of the engine, compare the knock intensity of the engine to a threshold knock intensity; if the knock intensity of the engine is greater than the threshold knock intensity, retard the respective ignition timing for each engine cylinder of the plurality of engine cylinders by the same amount; and if the knock intensity of the engine is less than the threshold knock intensity, retard a first ignition timing of a first engine cylinder by a first amount independently of a second ignition timing of a second engine cylinder.

A rotating detonation engine having a non-circular cross-sectional shape provided by the present invention may comprise: a housing; an ethylene plenum provided in the housing; an oxygen plenum surrounding the ethylene plenum; a channel-shaped combustion chamber connected to the ethylene plenum and the oxygen plenum and having a non-circular cross-section; a pre-ignition device for igniting a compound present in the combustion chamber; an oxygen plenum static pressure sensor for measuring the static pressure in the oxygen plenum; a supply port for supplying oxygen to the oxygen plenum; a static pressure sensor for measuring the static pressure in the combustion chamber; and a dynamic pressure sensor for measuring the dynamic pressure in the combustion chamber.

The application discloses a lean-burn engine control method, device and engine system. The lean-burn engine control method comprises the following steps: obtaining a current torque and a target torque; when the current torque is less than the target torque, obtaining an average effective pressure and an excess air coefficient; when the average effective pressure is in a first pressure range and the excess air coefficient is in a first coefficient range, adjusting an ignition angle, increasing air content and combustible content in a cylinder, and increasing the current torque to the target torque. By using the above technical scheme, the current torque can be increased, the thermal efficiency can be ensured to be high, and the combustion center can be prevented from changing, the ignition angle can be prevented from being large, and the lean-burn engine can be prevented from being damaged by knocking.

The embodiment of the invention provides a vehicle fault processing method and device, equipment, a storage medium and a program product. The method comprises the steps that when a vehicle is in a running state, whether knocking abnormity exists in an engine or not is determined according to target knocking parameters of the engine of the vehicle, and the target knocking parameters comprise at least one of a knocking learning value, a knocking fast learning value and knocking signal intensity. And if the engine has the knock abnormity, the knock abnormity processing operation is executed, and the knock abnormity processing operation comprises at least one of limiting the torque of the engine and outputting abnormity prompt information. The method is used for achieving the effects of reducing the knocking condition of the vehicle engine, improving the operation stability of the engine and prolonging the service life of the engine.

The present invention provides a vehicle control device that can suppress vibrations of the vehicle body when the internal combustion engine restarts, even if a restart request occurs before the engine speed of the internal combustion engine reaches "0". [Solution] The control device is applied to a vehicle that transmits torque output from an internal combustion engine to the drive wheels. The control device includes a processing circuit that controls the internal combustion engine. The processing circuit performs ignition timing control, automatic stop control, and automatic start control. Ignition timing control is a control that starts from the initial ignition timing when the engine starts and repeatedly adjusts the ignition timing according to the knock detection result. The processing circuit terminates the ignition timing control (step S13) when the engine rotational speed NE becomes less than or equal to a first rotational speed NE1 which is greater than "0" (step S12: YES).

According to the three-rotor high-speed turbofan engine and the control method thereof, the three-rotor overall layout is adopted for the three-rotor high-speed turbofan engine, a rotor system is decoupled into three independent rotors, the component system efficiency of the engine in the low-speed state, the medium-speed state and the high-speed state is greatly improved, and the overall circulation efficiency of the engine is improved; a novel variable circulation structure is adopted, under the condition that the circulation capacity of a core engine in the high-speed state is limited, part of airflow can bypass the core engine to be combusted in an outer culvert, then a turbine is driven to do work, the rotating speed of a low-pressure compressor is increased, the fan flow and efficiency of the engine are improved, and then the overall thrust of the engine in the high-speed state is improved; the rotating detonation combustion chamber is additionally arranged, under the condition that the flow capacity of the core engine in the high-speed state is limited, energy can be injected into the main flow through the rotating detonation combustion chamber, a turbine is driven to do work, the overall thrust of the engine is improved, meanwhile, nitrogen oxide combustion improvers are avoided, and the safety of the engine can be improved.

Method for a power machine (10), comprising: to deactivate individual cylinder valve mechanisms according to a cylinder pattern chosen based on a knock value of each cylinder (14) of the power engine (10), wherein the selection involves selecting a first cylinder (14) which has a knock value above a threshold for deactivation, while a second cylinder (14) with a knock value below a threshold remains active during deactivation, characterized by the fact that the first cylinder (14) remains deactivated for a number of power engine cycles, the number being based on the temperature of the first cylinder (14), the number of power engine cycles being increased if the temperature of the first cylinder (14) rises above a threshold, the temperature of the cylinder (14) including a measured or derived cylinder internal temperature.

The application relates to the technical field of engines and discloses a turbine-based combined cycle engine operation method and a turbine-based combined cycle engine. The turbine-based combined cycle engine operation method comprises the following steps: adopting a pulse detonation combustion mode in a pure turbine mode; adopting a rotating detonation combustion mode in a pure ram mode; and adopting the pulse detonation combustion mode and the rotating detonation combustion mode simultaneously in a transition mode. The application utilizes the advantages of the pulse detonation combustion, such as self-pressurization and high unit thrust, to improve high-speed performance and widen the upper limit of the working Mach number of the pure turbine mode; the advantages of the rotating detonation combustion, such as fast combustion speed, high combustion efficiency, simple structure and short length, are utilized to widen the lower limit of the working Mach number of the pure ram mode. In the transition mode, the turbine-based combined cycle engine simultaneously has the characteristics of the pure turbine mode and the pure ram mode, so that sufficient thrust can be provided for an aircraft.