152 results about "Turbojet engine" patented technology

The utility model discloses a generator control device, a gas generator system and an aircraft, the generator control device comprises an automatic control unit, a sensing unit and a rectification unit, the generator is connected with a turbine of a turbojet engine through a main shaft, and the generator is connected with electric equipment. The automatic control unit is connected with an oil pump of the turbojet engine, electric equipment, the sensing unit and the rectifying unit, the sensing unit comprises a rotating speed sensor connected with a main shaft, the rectifying unit comprises a diode rectifier bridge and a buck-boost converter, the generator is connected with the diode rectifier bridge, and the diode rectifier bridge is connected with the buck-boost converter. And the buck-boost converter is connected with electric equipment. The power supply can stably output electric energy according to the requirements of electric equipment, ensures that the output voltage is stable, and meets the requirements of the electric equipment.

Hybrid turbomachine comprising: an input shaft (a26) configured to be driven by a low-pressure turbine (102); an output shaft (a64) to drive an electric machine (104) and another output shaft (a64') to drive another electric machine (104'); a speed variator (106) to adjust the speed of each output shaft (a64, a64') according to a speed of the input shaft, comprising: a first planetary gear train (T1) having, at the input, a planet carrier (108) connected to the input shaft, a ring gear (112) and a planet (110); at the output, a first sun gear (130) connected to said output shaft, a second planetary gear train (T2) having, at the input, the ring gear (112) and another planet (120); At the output, a second sun (140) is connected to the other output shaft, and a means (MB) is provided for locking or freeing the crown. Figure for the abbreviation: Fig. 1

This utility model discloses an adjustable two-dimensional tail nozzle, belonging to the field of two-dimensional tail nozzle technology; it includes a connected engine and an adapter casing. A servo is provided on one side of the adapter casing. The output side of the adapter casing consists of a rectangular opening formed by two oppositely arranged fixed plates and two oppositely arranged adjusting plates. A power arm is provided at the output end of the servo. The right end of the power arm is connected to two parallel first connecting rods by a pin shaft. The other ends of the two first connecting rods are respectively connected to two second connecting rods. It can be applied to small afterburning turbojet engines to improve the flight speed of UAVs. Its structure is simple. The synchronous opening and closing movement of the adjusting plates is achieved through a single servo drive source, reducing the control difficulty, realizing engine thrust adjustment, reducing the number of structures, and making it lightweight, highly reliable, and low in cost. By setting a support rod on the outside of the adjusting plate, the adjusting plate can be limited. The structure is simple and the use effect is good.

A rear portion of a turbojet engine with converging-diverging nozzles includes a device for controlling the position of the diverging vane relative to the position of the converging vane, the device including a first link (120) having a first end (120A) hinged to the converging vane (30) and an opposite second end (120B), a second link (122) having a first end (122A) hinged to the diverging vane (32) and an opposite second end (122B), and a third link (124) having a first end (124A) hinged to a synchronization ring (82) and an opposite second end (124B). The second end (120B) of the first link is hinged to the second end (122B) of the second link and / or to the second end (124B) of the third link, and the second end (124B) of the third link (124) is hinged to the second end (122B) of the second link (122).

The invention relates to the technical field of engine recovery, in particular to a turbojet engine ejection recovery system and method in an aircraft fault state, and the system comprises an ejection mechanism which is arranged between a turbojet engine and an aircraft and used for disconnecting the turbojet engine from the aircraft. The turbojet engine is ejected out of the aircraft; the cut-off mechanism is arranged in the aircraft and used for cutting off an oil way and a circuit of the turbojet engine. The protection mechanism comprises a parachute assembly and an air bag assembly, the parachute assembly is connected with the turbojet engine, and a parachute is automatically opened in the landing process of the turbojet engine; the air bag assembly is folded and contracted outside the turbojet engine and automatically expands to wrap the turbojet engine in the landing process. The recycling device is compact in structure and flexible and convenient to use, recycling of the turbojet engine can be efficiently and safely completed when the fixedly-mounted turbojet engine is in an emergency, and the technical requirement for recycling of the turbojet engine in the field is met.

The invention belongs to the technical field of small turbojet engines, and particularly relates to a temperature field and pressure field prediction method and system for a gas compressor of a small turbojet engine. The method comprises the following steps: S1, acquiring data of different working conditions and data corresponding to a temperature field and a pressure field, enabling an acquired time sequence to correspond to the data of the temperature field and the pressure field, and then dividing into a training set and a test set; s2, establishing a neural network prediction model based on a gating circulation unit for the temperature field and the pressure field; s3, training a neural network prediction model based on a gating circulation unit for the temperature field and the pressure field; s4, testing the effect of the neural network prediction model based on the gating circulation unit for the temperature field and the pressure field; and S5, realizing temperature field and pressure field prediction of the small turbojet engine compressor. According to the invention, the problem that the neural network is affected by accumulative errors due to gradient disappearance and long prediction time in the unsteady flow field application is solved.

The invention relates to a whole machine dynamic balance system for a turbojet engine. The detection tool of the dynamic balance system is installed on the top face of a base of a conveying assembly, the number of the roller sets is multiple, each roller set comprises two rollers which are sequentially arranged in the first direction, the rollers are rotationally connected to the bottom face of the base through a roller frame, and a through locking hole is formed in the top of the roller frame; the two pushing pieces are oppositely arranged on the top face of the base in the first direction. The connecting rod is movably connected with the top face of the base in the first direction, and the two ends of the connecting rod are connected with the two pushing pieces through locking mechanisms correspondingly. The two ends of a connecting frame of the locking mechanism are connected with a pushing piece and a connecting rod, a driving pin is connected with the connecting frame, at least part of the driving pin is arranged in the connecting frame, a locking block is arranged in the connecting frame in a sliding mode in the first direction, the side, facing the driving pin, of the locking block is an inclined face, and a locking rod is connected with the top of the locking block and inserted into a locking hole. According to the engine base, the phenomenon that the engine on the base moves and collides with other objects can be avoided.

The utility model discloses a low temperature nozzle belongs to turbojet engine technical field, including the outside shield of fixed connection in the engine tail nozzle, the side of outside shield near engine body is equipped with a plurality of air inlet at interval, and the one end of outside shield near engine tail nozzle spout is equipped with the air outlet. When engine body runs, the spout of engine tail nozzle sprays high temperature high -speed gas, at this moment, utilize siphon principle, will bring out the airflow in outside shield, and cold air keeps on continuously acting between engine tail nozzle and outside shield, and the cooling of engine tail nozzle is given, and outside shield also will break off the heat radiation that inside tail nozzle emits, reaches the effect that reduces engine tail nozzle temperature.

1. Name of the product in this design: Electronic Controller for Turbojet Engine (ECU). 2. Purpose of this design: To control engine starting, acceleration, deceleration, steady state and stopping according to input control commands, as well as to check the function of engine accessories (starter motor, oil pump, solenoid valve, igniter, etc.), store engine data, and cool the engine. 3. The key design features of this product are its overall shape. 4. The image or photograph that best illustrates the design's key features: the front view. 5. This design is a thin product, so the left view is omitted; this design is a thin product, so the right view is omitted; this design is a thin product, so the top view is omitted; this design is a thin product, so the bottom view is omitted; this design is a thin product, so the perspective view is omitted.

PROPULSION ASSEMBLY FOR AN AIRCRAFT COMPRISING A TURBOJET ENGINE, A MAST AND MEANS FOR ATTACHING THE TURBOJET ENGINE TO THE MAST The invention relates to a propulsion assembly (100) of an aircraft having a vertical longitudinal axis (X) and median plane (P) and comprising a front casing (112a) with a rear face (113) perpendicular to the longitudinal axis (X), a primary structure (106) with a front wall (106e), and an engine attachment (150) comprising a female clevis (152a) integral with the front wall (106e), a male clevis (152b) integral with the rear face (113) and articulated in the female clevis (152a), a pin (154a) integral with the primary structure (106) and whose axis is parallel to the longitudinal axis (X) and a housing (154b) of the rear face (113) in which the pin (154a) is housed, and where the clevises (152a-b), the pin (154a) and the housing (154b) are arranged at the level of the median plane (P). Fig. 3

The invention relates to a hydraulic control circuit (11) for an orienting actuator (14) for orienting fan blades of a turbojet engine, the circuit (11) comprising an oil reservoir (17) and an axial piston pump (18) comprising a tiltable plate (23), as well as a control chamber (24) and a compensation chamber (27) for increasing the tilt of the plate (23) when the pressure inside these chambers increases, the pump (18) being supplied by the reservoir (17) and having its outlet configured so as to be able to be connected by a supply line (19) to one of the chambers (12, 13) of the orienting actuator (14), the other chamber of the orienting actuator (14) being connected to the reservoir (17), this control circuit comprising a valve (42) controlled by a computer (FADEC), which valve (42) allows the outlet of the pump (18) to be connected to the reservoir (17) in order to deactivate this pump (18).

The invention discloses a crawler-type remote control camouflage protection smoke screen vehicle and a working method, the crawler-type remote control camouflage protection smoke screen vehicle comprises a chassis, a smoke generating device and a box body, the chassis is a crawler-type mobile vehicle, the smoke generating device and the box body are both arranged on the chassis, and the smoke generating device is arranged in front of the box body; the fuming device is installed on the chassis through a left-right rotating head driving device and an up-down rotating head driving device, a turbojet engine and a spraying pipe are arranged in the fuming device, and the spraying pipe is arranged at the front end of the turbojet engine; a left-right rotating head limiting switch is arranged on the left-right rotating head driving device, and an up-down rotating head limiting switch is arranged on the up-down rotating head driving device; a smoke master control system is arranged in the box body, and the smoke generating device, the moving mechanism, the left-right rotating head driving device and the up-down rotating head driving device are all connected with the smoke master control system. The problems that an existing smoke screen vehicle is low in rapid transfer capacity on complex terrains and cannot rapidly adapt to environmental changes are solved.

The invention relates to a turbojet engine afterbody comprising:-an exhaust casing (9) carrying a manifold plate (11) surrounding a primary air flow and surrounded by a secondary air flow; -an afterburner (12) comprising a casing (13) and a bushing (16) delimiting together with the casing (13) an annular space (17) extending along the axis (AX), the diameter of the bushing (16) being greater than the diameter of the converging plate (11); -a fixed shroud (22) extending from the bus plate (11) to the inner liner (16), the fixed shroud (22) comprising a window (27); -a moving cover (23) extending along the fixed cover (22) and comprising a window (28), the cover (23) being rotatably movable about an axis (AX) between an open position, in which the window (27) in the fixed cover is open, and a closed position, in which the window (27) in the fixed cover (22) is closed by the moving cover (23).

The utility model discloses a heat dissipation structure of a smoke generator of a turbojet engine, which belongs to the technical field of heat dissipation structures and comprises a heat dissipation component, the heat dissipation component comprises a first heat dissipation sleeve and a second heat dissipation sleeve, and the first heat dissipation sleeve and the second heat dissipation sleeve are butted and then wrapped outside a tail spray pipe. Positioning support lugs are arranged on the sides, close to each other, of the first heat dissipation sleeve and the second heat dissipation sleeve; and the liquid flow channel is formed in the first heat dissipation sleeve and the second heat dissipation sleeve, and after the first heat dissipation sleeve and the second heat dissipation sleeve are in sealed butt joint, the liquid flow channel forms a through type net-shaped heat dissipation flow channel. Through the arrangement of a butt-joint structure, the first heat dissipation sleeve and the second heat dissipation sleeve are wrapped on the outer wall of the tail spray pipe, internal liquid circulates through communication of internal heat dissipation flow channels of the first heat dissipation sleeve and the second heat dissipation sleeve, efficient heat dissipation treatment of the tail spray pipe is achieved, and therefore the service life of all parts of the smoke generator is prolonged.

The invention discloses a method for obtaining a control strategy of a turbojet engine and a method for controlling the turbojet engine, the method for obtaining the control strategy of the turbojet engine comprises at least two iterations, and each iteration sequentially comprises a measurement and control stage and an updating stage; the measurement and control stage comprises at least two times of measurement and control and an array set is finally obtained; in the updating stage, the to-be-updated control strategy is updated through a primary function approximation method based on an array set to form a control strategy of the iteration and a control parameter used for representing a mapping rule from an independent variable to a dependent variable in the control strategy of the iteration; the method for controlling the turbojet engine is based on the obtained control strategy, the blade rotating speed is measured every set period, the fuel flow speed is obtained through calculation based on the control strategy, and then the turbojet engine is controlled according to the fuel flow speed obtained through calculation. By the adoption of the technical scheme, under the condition that dynamic parameters in the turbojet engine are unknown, continuous control over the fuel flow speed can be achieved, and the blade rotating speed reaches the target blade rotating speed.

The invention relates to the technical field of micro turbojet engine control, and discloses a control method for solving heat dissipation oil injection recombustion of a micro turbojet engine, which comprises the following steps of: closing fuel supply, establishing rotating speed closed-loop control, and keeping the actual rotating speed of the engine equal to a preset cooling rotating speed under disturbance; under the working condition, the actual cooling rate is obtained, and the reference cooling rate is obtained by inquiring the reference cooling model; comparing the actual cooling rate with a reference cooling rate to determine a rate deviation; according to the method, active rotating speed closed-loop control is established, a constant diagnosis reference working condition is forcibly constructed, and catastrophic interference of external aerodynamic disturbance on diagnosis logic is eliminated, so that the electronic control unit can still reliably sense and actively suppress hidden reburning under the working conditions of shutdown gliding and the like.

AIRCRAFT PROPULSION SYSTEM COMPRISING A TURBOJET ENGINE, A MOUNTING MAST AND MEANS FOR ATTACHING THE TURBOJET ENGINE TO THE MOUNTING MAST The invention relates to an aircraft propulsion system (100) comprising a turbojet engine (102) having a front casing (103) with a rear face (103a) and a rear casing (105), a mooring mast (104) with a front part (106a) and a lower spar to which a rear fitting (108) is attached, a front engine mount (150) fixed between the front casing (103) and the front part (106a), an arch (152) with a base (152a) fixed to the rear fitting (108) and two arms (152b-c), each having a first end integral with the base (152a) and a second end fixed to the rear casing (105), two upper bars (155) hinged to the rear face (103a) and embedded in the arch (152), and two lower bars (157) hinged to the rear face (103a) and to the arch (152). Fig.2.

The application relates to the technical field of aero-engines, in particular to a micro turbojet engine starting control method and system, which comprises the following steps: obtaining initial environment parameters of the micro turbojet engine, generating a clutch action response value according to the initial environment parameters based on a preset starting acceleration model and a clutch action response model; obtaining a current measured rotating speed of the engine, judging whether the clutch is successfully thrown out; if it is judged that the clutch is successfully thrown out, obtaining a rotating speed rising change value of the engine, judging whether the clutch is connected and stably transmits torque; if it is judged that yes, a motor disengagement judgment model is constructed, the motor is controlled to stop rotating based on the motor disengagement judgment model, and a safe disengagement stage is entered. The application improves the adaptability to complex environments and the identification ability to abnormal states in the starting stage, and significantly enhances the starting reliability and use safety of the micro turbojet engine.

The invention relates to a micro turbojet engine oil distribution ring flow testing device. A base of the testing device is provided with a first supporting plate and a second supporting plate, and the second supporting plate is arranged on the first supporting plate; the oil storage tank is connected with the base and arranged below the first supporting plate. The top end of the circulating pipe is arranged on the second supporting plate; the detection assembly comprises a supporting seat, a lifting part and a plurality of detection pipes, the supporting seat is connected with the base and located below the second supporting plate, the lifting part is connected with the supporting seat, the multiple detection pipes are arranged around the peripheral side of the supporting seat at intervals, the multiple detection pipes are connected with the lifting part, and the lifting part drives the multiple detection pipes to be switched between the first state and the second state. According to the method, the consistency of the oil injection quantity of each oil needle of the oil distribution ring can be efficiently and intuitively judged, so that the requirement of balance detection of the oil distribution ring is met.

HIGH-STABILITY, HIGH-AGILITY THREE-SAILING SURFACE AIRCRAFT The three-sail aircraft (1), (2), and (3) is equipped with movable flaps (6), (7), and (8) on each of the lifting surfaces. The flaps of the upstream lifting surface (6) are connected to the flaps of the main wing (7) by a rigid linkage with a deflection angle ratio of 50%. The forces on the downstream lifting surface (horizontal tail) (3) reverse between takeoff (negative lift) and cruise (positive lift). Stabilizing fins (5) are positioned at the rear of the fuselage in the lower section at an angle of 30° to the aircraft's centerline. A weighted control rod (22) located in the vertical tail (4) provides stabilization for the aircraft in the presence of severe turbulence.The propulsion system is located at the rear of the fuselage and consists of either a piston engine driving a multi-bladed propeller, one or two turboshaft engines driving a multi-bladed propeller or two contra-rotating propellers, a turbojet engine, or one or two electric motors driving a multi-bladed propeller or two contra-rotating propellers. This aircraft can be piloted either by a human pilot on board or by an electronic computer controlled from the ground or autonomously.

This utility model relates to the field of turbojet engine technology and discloses a test bench for turbojet engines, comprising a main body of the bench; a placement plate is mounted on the top of the main body of the bench, and four adjustment slots are formed on the top of the placement plate; two fixing rods are fixedly connected inside the adjustment slots; adjustment blocks are slidably connected inside the adjustment slots and on the surfaces of the fixing rods; arc-shaped clamping plates are fixedly connected to the tops of the adjustment blocks; four sets of extension plates are fixedly connected to the top of the placement plate, and multiple limiting slots are formed on the surfaces of the extension plates; and a toggle slot is formed on the top of the adjustment blocks. This test bench for turbojet engines allows for convenient positioning of the turbojet engine. When personnel need to test it, they only need to simply remove, move, and adjust it to achieve convenient positioning, thereby effectively reducing the cumbersome positioning operation during testing and significantly improving testing efficiency.

The utility model provides a kind of smoke generator using two-stage cyclone air atomization nozzle, belong to smoke generator technical field, the smoke generator includes micro turbojet engine nozzle and is arranged at the smoke nozzle of micro turbojet engine nozzle export side, the inside of smoke nozzle is provided with atomizing device, the outlet of atomizing device and the outlet of smoke nozzle are set same direction;When working, micro turbojet engine is used as smoke power source, high temperature high pressure high-speed airflow generated from micro turbojet engine turbine export flows out from micro turbojet engine nozzle and enters from smoke nozzle import, smoke agent enters atomizing device, atomizing device is fully atomized after smoke agent and is discharged into smoke nozzle, and after atomization, smoke agent and airflow are fully mixed and are discharged from smoke nozzle outlet, and large-scale smoke screen is formed in short time, solve the problem that existing high-power smoke generator directly forms smoke screen due to smoke agent not passing through atomization, reduce smoke effect, cause smoke agent waste.

This utility model discloses a coaxiality auxiliary tool for assembling a turbojet engine, belonging to the technical field of turbojet engine technology. It includes a fixed frame, a turbojet engine placement platform fixed to the fixed frame, a connecting seat fixed to the turbojet engine placement platform, a coaxiality fixture inside the connecting seat, and a handle on one side of the connecting seat, which is connected to the coaxiality fixture via a transmission connection. The top surface of the fixed frame has a recessed platform for placing the turbojet engine. The turbojet engine is placed on the turbojet engine placement platform, and the handle is pressed down. The coaxiality fixture passes through the diffuser front cover and shaft tube of the turbojet engine. At this time, the shaft tube and the diffuser front cover are aligned and coaxial by the coaxiality fixture. Then, the screws of the diffuser front cover are glued and tightened. The handle is lifted, and the coaxiality fixture is removed from the turbojet engine. The compressor wheel, main shaft, and air inlet are then installed onto the turbojet engine to complete the assembly. This utility model can save assembly time and improve work efficiency while ensuring coaxiality accuracy.

This invention relates to the field of engine recovery technology, and in particular to a system and method for the ejection and recovery of a turbojet engine in the event of an aircraft malfunction. The system includes an ejection mechanism positioned between the turbojet engine and the aircraft, used to disconnect the turbojet engine from the aircraft and eject the engine outside the aircraft; a cutting mechanism located inside the aircraft, used to cut off the turbojet engine's oil and electrical circuits; and a protective mechanism including a parachute assembly and an airbag assembly. The parachute assembly is connected to the turbojet engine and automatically deploys during the engine's descent; the airbag assembly folds and retracts outside the turbojet engine and automatically expands to enclose the engine during descent. This invention has a compact structure, is flexible and convenient to use, and can efficiently and safely recover a fixed-mounted turbojet engine in an emergency, meeting the technical requirements for turbojet engine recovery in this field.

The utility model provides a high-control-efficiency two-dimensional vector device which comprises a fixing support installed at the tail of a turbojet engine and a connecting sleeve coaxially arranged outside the fixing support in a sleeving mode, a tail nozzle is erected at the tail end of the fixing support, a drainage structure is arranged at the air inlet end of the tail nozzle, and a flow guide plate is embedded in the tail end of the tail nozzle; a vector ring is coaxially and movably connected to the outer side of the tail nozzle, a gap is formed between the vector ring and the tail nozzle, the vector ring is connected with the fixed support through a first rotating shaft, the vector ring is connected with the tail nozzle through a second rotating shaft, and the first rotating shaft and the second rotating shaft are both arranged in the radial direction of the vector ring; a driving mechanism is mounted on the outer wall of the connecting sleeve, is connected with the tail nozzle and is used for driving the tail nozzle to rotate around the first rotating shaft and / or the second rotating shaft. According to the scheme, large deflection torque is provided within a small deflection angle, and the device has the advantages of being small in size, simple in structure, easy to assemble, high in efficiency and the like.

The steam engine and the steam turbine push the machine to run by water vapor evaporated by heat released by fuel combustion absorbed by water; an internal combustion engine, a turbojet engine and a gas turbine are driven to operate by high-temperature and high-pressure waste gas generated by combustion of fuel in a combustion chamber. The composite combustion chamber is provided with the combustion chamber and the water mixing chamber, fuel combustion can be completed in the composite combustion chamber, water is evaporated into water vapor to form mixed gas, a machine is pushed to operate, and the heat efficiency of a heat engine is greatly improved.

A rear section for a turbojet engine includes a variable geometry nozzle in which a converging flap is provided with a lever (80) supporting a support roller (96) axially arranged between an upstream support wall (90) and a downstream support wall (92), the upstream and downstream support walls being rigidly fixed to a movable section capable of axial movement relative to an upstream stator structure (38) upon command, such that the support roller moves freely in the radial direction (R) relative to the upstream and downstream support walls. During downstream movement of the movable section, the upstream support wall pushes the lever to pivot the downstream end (46) of the converging flap toward the longitudinal axis. Therefore, the operation of the drive mechanism for moving the movable section can be optimized while limiting the size and mass of the device used to control the flap.

The invention relates to a hydraulic control circuit (11) for a fan blade pitch control actuator (14) of a turbojet engine, comprising an oil reservoir (17), an axial piston pump (18) having a tilting swashplate (23) and a control chamber (24) and a compensation chamber (27) to increase the tilt of the swashplate (23) when the pressurization of these chambers increases, the pump (18) being supplied by the reservoir (17) and having its outlet configured to be connected by a supply line (19) to one of the chambers (12, 13) of the pitch control actuator (14), the other chamber of the pitch control actuator (14) being connected to the reservoir (17), this control circuit comprising a valve (42) controlled by a computer (FADEC) allowing the outlet of the pump (18) to be connected to the reservoir (17) in order to deactivate this pump (18). Figure for the abbreviation: Figure 2

The invention provides a device for verifying an engine driving exhaust emission system in a laboratory, and belongs to the technical field of exhaust emission. Comprising an experiment bench used for bearing an engine, the engine arranged in the experiment bench, an exhaust pipeline used for collecting engine tail gas and injected air, a spraying cooling system integrated in the exhaust pipeline, and a back pressure control system arranged at the rear end of the exhaust pipeline. The measuring systems are arranged at different parts of the device; and the control system is used for controlling the device to work. The device integrates multivariable adjusting functions such as the shape / size of an exhaust pipeline, the water spraying amount, the back pressure and the engine working condition, and the influences of different parameters on the injection ratio, the temperature field and the pressure distribution can be tested independently or in a combined mode. An economical and efficient solution can be provided for laboratory test run of the small / micro turbojet engine; experimental data can directly guide the design of an actual airplane laboratory exhaust pipeline and an exhaust tower, and the development period is shortened.

The invention provides an automatic test system process for a turbojet engine pedestal, relates to the technical field of new energy engine testing, is suitable for testing power systems of motor vehicles such as electric vehicles carrying turbojet engines, and is also suitable for testing power systems of various unmanned aerial vehicles and patrol bullets. The problems of more manual operation, low efficiency, high energy consumption and insufficient safety of a traditional test are solved, system hardware is divided into an operation room, a rack test room and a gas cylinder storage room, a measurement and control system device serves as a core, and the whole process of safety protection, gas supply, ignition, starting and testing is integrated. The safety protection system realizes abnormal alarm through a propane gas concentration sensor and a pressure / temperature sensor; the gas supply system automatically controls gas on-off and state monitoring; the ignition system is combined with an exhaust temperature sensor to realize automatic reset of the probe; after starting, oil supply and gas cut-off are automatically switched according to a rotating speed threshold value; normally testing editable working conditions, automatically collecting parameters, and stably stopping after the parameters are collected.