CN211784284U - Test run training device for aircraft engine - Google Patents
Test run training device for aircraft engine Download PDFInfo
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- CN211784284U CN211784284U CN202020556254.2U CN202020556254U CN211784284U CN 211784284 U CN211784284 U CN 211784284U CN 202020556254 U CN202020556254 U CN 202020556254U CN 211784284 U CN211784284 U CN 211784284U
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Abstract
The utility model discloses an aircraft engine test training device, which comprises an engine and a safety protection cover, wherein a fuel supply mechanism is arranged in a working rack, the upper part of the working rack is provided with the engine, the safety protection cover and a thrust test mechanism, the safety protection cover covers the engine, the thrust test mechanism comprises a fixed support and a thrust sensor, the engine is fixed on the fixed support arranged on a slide rail, the fixed support is connected with the thrust sensor, the slide rail is arranged on the upper part of the working rack, the engine is connected with an engine controller, the engine controller is connected with a display screen, a rotating speed sensor, a temperature sensor and the thrust sensor, one end of an oil pipeline is connected with an oil tank, the other end of the oil pipeline is connected with the engine, the oil pipeline between the oil tank and the engine is provided with an oil pump, a shut-off valve and an oil filter pump, the shut, the controller is connected with a handle switch. The utility model discloses safe and reliable does not receive weather and guarantee equipment restriction.
Description
Technical Field
The utility model relates to a trainer, concretely relates to aircraft engine training device that tries on a trial run.
Background
The engine test run is an important and frequent means for detecting the performance of the aircraft engine, is a skill which must be mastered by professional trainees of aviation maintenance machinery, and has the defects of high danger, high consumption, complex guarantee, weather restriction and the like if the practical aircraft is used for the engine test run in the teaching implementation process; if the engine test training is carried out by using the simulation test training exerciser, the problems of low simulation degree, high equipment failure rate and the like exist.
SUMMERY OF THE UTILITY MODEL
The utility model discloses the technical problem that will solve is: the defects of the prior art are overcome, and the aircraft engine test run training device based on the small turbojet engine and used for performing transition training between simulation training and actual loading test run is provided.
The utility model discloses a technical scheme who solves technical problem and take is:
an aircraft engine test run training device comprises a working bench, an engine, a thrust testing mechanism, a fuel supply mechanism and a safety protection cover, wherein the fuel supply mechanism is arranged inside the working bench, the upper part of the working bench is provided with the engine, the safety protection cover and the thrust testing mechanism, the safety protection cover covers the engine, the thrust testing mechanism comprises a fixed support and a thrust sensor, the engine is fixed on the fixed support, the fixed support is arranged on a sliding rail, the fixed support is connected with the thrust sensor, the sliding rail is arranged on the upper part of the working bench, the engine is connected with an engine controller through a two-way signal communication link, the engine controller is connected with a display screen, a rotating speed sensor, a temperature sensor and the thrust sensor, revolution speed sensor with the rotation axis connection of engine, temperature sensor sets up the gas vent department of engine, fuel supply mechanism includes defeated oil pipe way, oil tank, oil pump, shutoff valve and oil and strains, defeated oil pipe way one end with the oil tank is connected, the other end with the engine is connected, the oil tank with between the engine defeated oil pipe is provided with on the road oil pump, shutoff valve with oil strains, the oil pump with the shutoff valve with engine controller connects, be connected with control on the controller the handle switch of throttle lever on the engine.
The safety protection cover adopts transparent organic glass to make, the safety protection cover is detachable safety protection cover, the engine will when out of work the safety protection cover pull down and place in inside the work bench frame, the engine during operation uses the safety protection cover covers the engine.
The engine is a turbojet engine, and an AT89C52 chip is adopted in the controller; the model of the rotating speed sensor is CS-1, the model of the temperature sensor is TR02005, and the model of the thrust sensor is QLW-20. The oil is strained and is passed through defeated oil pipe way with the engine is connected, the oil pump passes through defeated oil pipe way with the oil tank is connected, the oil pump with be provided with between the oil is strained the shutoff valve.
The device has the main functions of realizing the starting and stopping of the small turbojet engine and enabling the engine to be in different working states, and can measure engine performance parameters such as the starting temperature, the starting time, the stopping time, the rotating speed, the exhaust temperature, the thrust and the like of the engine in each state.
The turbojet engine in the device is a small turbojet engine, the small turbojet engine is the core of a training device and is also an operation object of test run, and the small turbojet engine for the test run training is manufactured by using an original parameter sensor or adding a corresponding parameter sensor and an interface circuit on the basis of the turbojet engine for the model airplane with moderate thrust and reliable performance.
The core components of the engine controller are a single chip microcomputer and a control program, when the engine controller works, the engine rotating speed, the exhaust temperature and the throttle lever position data are collected, the oil supply amount of the engine is controlled after calculation according to the control program, and the collected data are displayed on a display.
The handle switch actuates the throttle lever to start the engine and control the operating state of the engine, and the communication link communicates throttle position data to the engine control unit.
The display can monitor the engine speed, the exhaust temperature and the engine thrust, so that a test person can observe various performance parameters of the engine in real time through the monitor, including the engine speed, the engine thrust, the temperature at an exhaust pipe of the engine and the oil supply quantity.
The thrust measuring mechanism is composed of a fixed support and a thrust sensor, the engine is fixed on the fixed support, the fixed support is placed on the slide rail and connected with the thrust sensor, the engine pushes the fixed support to generate displacement in the direction of the slide rail in proportion to the thrust when working, and the displacement is measured by the thrust sensor to obtain the thrust of the engine.
The fuel oil supply mechanism consists of an oil tank, an oil pump, an oil pipeline, an oil filter and a shutoff valve, and stably and reliably supplies aviation kerosene for work to the engine; the function of the fuel tank is to store fuel; the oil pump is used for pressurizing fuel and supplying the pressurized fuel to the engine, so that the engine is ensured to work reliably; the oil delivery pipeline has the function of providing a fuel flow channel, a shut-off valve on the oil delivery pipeline is connected to an engine controller, the opening of the shut-off valve is adjusted by the engine controller to adjust the oil supply amount, and the oil supply amount is adjusted and then supplied to the engine; the function of the oil filter is to ensure that the fuel supplied to the engine is free of impurities.
The working bench is a mounting container and a platform of other components; an oil tank, an oil pump, an oil filter, a shut-off valve, a part of oil conveying pipelines and a safety protection cover of the fuel oil supply mechanism when the engine does not work are arranged in the working rack; the engine, the engine controller, and various sensors are disposed on the upper portion of the stand.
The safety protection cover is made by transparent organic glass for the operating condition of engine can be observed to the personnel of taking a trial run when receiving the protection, and the engine is covered to engine during operation use safety protection cover, prevents that compressor and turbine blade from throwing away and causes the incident, and the intensity of safety protection cover should satisfy under the highest rotational speed state blade and not punctureed when throwing away, and safety protection cover is detachable design, and the engine is pulled down and is placed inside the rack when out of work.
The utility model discloses an actively beneficial effect is:
1. the device can check the main performance parameters of the engine, has the functions of enabling a student to understand the performance measurement standard of the engine and detecting and teaching targets of the parameters, and simultaneously has the function which is not provided by the practical airplane test under the outfield condition, namely, the thrust of the engine can be measured, and the rotating speed characteristic curve of the engine can be drawn, so that the understanding of the student on the working characteristics of the engine can be deepened.
2. The device can be functionally expanded according to needs, and the speed characteristic curve of the engine can be further obtained after expansion; the expansion idea is to change the air inlet condition of the engine, namely adding an air inlet channel and fan-type power equipment at the air inlet of the small turbojet engine and changing the Mach number, total temperature and total pressure of the inlet airflow, thereby simulating the flight condition and verifying the speed characteristic of the engine.
3. The device has the advantages of low consumption, relative safety, indoor implementation and the like from the teaching effect, and can deepen the understanding and mastering of students on the working principle of the engine and the basic performance detection method; from the perspective of saving expenditure, when the device is used in test run, the consumption of service life loss, fuel consumption and the like of the engine can be obviously reduced compared with the use of a solid engine.
Description of the drawings fig. 1 is a schematic diagram of the aircraft engine test run training device of the present invention.
Detailed Description
The invention will be further explained and explained with reference to the drawings and the embodiments:
referring to fig. 1, in the figure: 1-a working table frame, 2-an engine, 3-a safety protection cover, 4-a fixed support, 5-a thrust sensor, 6-a slide rail, 7-an engine controller, 8-a display screen, 9-a rotating speed sensor, 10-a temperature sensor, 11-an oil conveying pipeline, 12-an oil tank, 13-an oil pump, 14-a shutoff valve, 15-an oil filter and 16-a handle switch.
Example (b): a test run training device of an aircraft engine 2 comprises a workbench frame 1, an engine 2, a thrust testing mechanism, a fuel supply mechanism and a safety protection cover 3, wherein the fuel supply mechanism is arranged in the workbench frame 1, the engine 2, the safety protection cover 3 and the thrust testing mechanism are arranged on the upper portion of the workbench frame 1, the safety protection cover 3 covers the engine 2, the thrust testing mechanism comprises a fixed support 4 and a thrust sensor 5, the engine 2 is fixed on the fixed support 4, the fixed support 4 is arranged on a sliding rail 6, the fixed support 4 is connected with the thrust sensor 5, the sliding rail 6 is arranged on the upper portion of the workbench frame 1, the engine 2 is connected with an engine controller 7 through a bidirectional signal communication link, the engine controller 7 is connected with a display screen 8, a rotating speed sensor 9, a temperature sensor 10 and the thrust sensor 5, and the rotating speed sensor 9 is connected with a rotating shaft of the engine, the temperature sensor 10 is arranged at an exhaust port of the engine 2, the fuel supply mechanism comprises a fuel conveying pipeline 11, a fuel tank 12, a fuel pump 13, a shut-off valve 14 and a fuel filter 15, one end of the fuel conveying pipeline 11 is connected with the fuel tank 12, the other end of the fuel conveying pipeline is connected with the engine 2, the fuel pump 13, the shut-off valve 14 and the fuel filter 15 are arranged on the fuel conveying pipeline 11 between the fuel tank 12 and the engine 2, the fuel pump 13 and the shut-off valve 14 are connected with an engine controller 7, and a handle switch 16 for controlling a throttle lever on the engine 2 is connected onto the controller.
Safety protection cover 3 adopts transparent organic glass preparation, and safety protection cover 3 is detachable safety protection cover 3, and engine 2 is out of work and pulls down safety protection cover 3 and place inside work rack 1, and engine 2 during operation uses safety protection cover to cover engine 2.
The engine 2 is a turbojet engine, and an AT89C52 chip is adopted in the controller; the model of the rotating speed sensor 9 is CS-1, the model of the temperature sensor 10 is TR02005, and the model of the thrust sensor 5 is QLW-20. The oil filter 15 is connected with the engine 2 through an oil pipeline 11, the oil pump 13 is connected with the oil tank 12 through the oil pipeline 11, and a shut-off valve 14 is arranged between the oil pump 13 and the oil filter 15.
The main function of the device is to realize the starting and stopping of the small turbojet engine and to enable the engine 2 to be in different working states, and to measure the performance parameters of the engine 2, such as the starting temperature, the starting time, the stopping time, the rotating speed, the exhaust temperature, the thrust and the like of the engine 2 in each state.
The turbojet engine 2 in the device is a small turbojet engine, the small turbojet engine is the core of a training device and is also an operation object of test run, and the small turbojet engine 2 for the test run training is manufactured by using an original parameter sensor or adding a corresponding parameter sensor and an interface circuit on the basis of the turbojet engine 2 for the model airplane with moderate thrust and reliable performance.
The core components of the engine controller 7 are a single chip microcomputer and a control program, and when the engine controller works, the rotating speed, the exhaust temperature and the throttle lever position data of the engine 2 are acquired, the oil supply amount of the engine 2 is controlled after calculation according to the control program, and the acquired data are displayed on a display.
The handle switch 16 activates the throttle lever to start the engine 2 and control the operating state of the engine 2, and the communication link communicates throttle position data to the engine controller.
The display is capable of monitoring the rotational speed, exhaust temperature and engine thrust of the engine 2 so that a test person can observe various performance parameters of the engine 2 in real time through the monitor, including the rotational speed of the engine 2, the thrust of the engine 2, the temperature at the exhaust pipe of the engine 2 and the amount of oil supply.
The thrust measuring mechanism is composed of a fixed support 4 and a thrust sensor 5, the engine 2 is fixed on the fixed support 4, the fixed support 4 is placed on the slide rail 6 and connected with the thrust sensor 5, the fixed support 4 is pushed to generate displacement in proportion to the thrust in the direction of the slide rail 6 when the engine 2 works, and the displacement is measured by the thrust sensor 5 to obtain the thrust of the engine 2.
The fuel oil supply mechanism consists of an oil tank 12, an oil pump 13, an oil pipeline 11, an oil filter 15 and a shut-off valve 14, and stably and reliably supplies the aviation kerosene for work to the engine 2; the function of the tank 12 is to store fuel; the oil pump 13 is used for pressurizing fuel and supplying the pressurized fuel to the engine 2, so that the engine 2 is ensured to work reliably; the oil delivery pipeline has the function of providing a fuel flow channel, a shut-off valve 14 on the oil delivery pipeline is connected to the engine controller 7, the opening degree of the shut-off valve 14 is adjusted through the engine controller 7 to adjust the oil supply quantity, and the oil supply quantity is adjusted and then supplied to the engine 2; the function of the oil filter 15 is to ensure that the fuel supplied to the engine 2 is free of impurities.
The work bench 1 is provided with a mounting container and a platform of other components; an oil tank 12, an oil pump 13, an oil filter 15, a shut-off valve 14, a part of an oil pipeline 11 and a safety protection cover 3 of the engine 2 when the engine does not work are arranged inside the working rack 1; the engine 2, the engine controller 7, and various sensors are disposed on the upper portion of the stand.
Safety protection cover 3 is made by transparent organic glass for the operating condition of engine 2 can be observed when the personnel of taking a trial run receives the protection, engine 2 during operation uses safety protection cover 3 to cover engine 2, prevent that compressor machine and turbine blade from throwing away and causing the incident in engine 2, the intensity of safety protection cover 3 should satisfy under the highest rotational speed state blade and not punctures when throwing away, safety protection cover 3 is detachable design, pull down and place inside the rack when engine 2 is out of work.
When the device is used, the method comprises the following steps of preparation, starting of the engine 2, detection of parameters of the engine 2, stopping of the engine 2, recovery and data processing:
(1) preparation and safety precautions:
before the test run training, whether the rack is clean or not needs to be checked, and sundries possibly sucked into an air inlet of the engine 2 need to be cleaned; the accessories of each part of the training device are firmly fixed, so that the problems of part loosening, oil leakage and the like in the working process of the engine 2 are prevented; when the engine 2 starts to work and in the working process, people are ensured to be beyond the safe distance, namely beyond 2m in front of the engine 2, 1m at two sides and 5m behind the engine 2, so as to avoid the suction airflow at the inlet of the engine 2 and the high-temperature and high-speed airflow at the nozzle of the engine 2; in order to prevent accidental fire, the fire-extinguishing bottle must be ready at any time during the operation of the engine 2; the engine 2 is covered with the protective cover 3 during operation, and small articles such as tools and stationery are prevented from being sucked into the engine 2.
(2) Starting of the engine 2
Turning on the control handle switch 16; pushing the throttle lever on the control handle to the maximum and then pulling the throttle lever to the minimum, sending a starting signal to the engine controller 7 at the moment, starting the motor to start driving under the control of the engine controller 7, starting the ignition rod to heat, starting the oil supply pump 13 to supply oil, and starting the engine 2; when the engine 2 reaches the idling rotation speed, the start is finished under the control of the control unit of the engine 2.
(3) Engine 2 parameter detection
Slightly pushing the throttle lever to increase the rotation speed of the engine 2 to warm up the engine 2; the throttle valve retracting rod reduces the rotating speed of the engine 2 to the slow vehicle rotating speed; the throttle lever is pushed to increase the rotating speed of the engine 2, the rotating speed, the exhaust temperature and the thrust of the engine 2 are recorded after the rotating speed is stabilized, the process is repeated for several times until the rotating speed of the engine 2 reaches the maximum rotating speed, the throttle lever is received to reduce the rotating speed of the engine 2 to the slow rotating speed, and the engine 2 is cooled.
(4) Engine 2 stop
The power supply of the operating handle is turned off, a stop signal is sent to the engine controller 7, and the engine 2 is driven to work for a period of time under the control of the engine controller 7 so as to further cool the engine 2, and then the vehicle is stopped.
(5) Recovery work and data processing
After the vehicle is stopped, the power is cut off, the oil is cut off, and the test run training device is cleaned; recording data and carrying out corresponding calculation to obtain performance parameters of the engine 2, wherein the performance parameters comprise the rotating speed, the thrust, the exhaust temperature, the oil consumption and the oil consumption rate of the engine 2; drawing a rotating speed characteristic curve of the engine 2, namely a variation curve of thrust and fuel consumption of the engine 2 along with rotating speed; and drawing a change curve of the exhaust temperature along with the rotating speed.
The above description is only a preferred embodiment of the present invention, and the protection scope of the present invention is not limited to the above embodiment, but all equivalent modifications or changes made by those skilled in the art according to the present invention should be included in the protection scope of the claims.
Claims (4)
1. The utility model provides an aircraft engine training device that tries on a trial run, includes work bench, engine, thrust accredited testing organization, fuel supply mechanism and safety protection cover, characterized by: the fuel oil supply mechanism is arranged in the work bench, the engine, the safety protection cover and the thrust testing mechanism are arranged on the upper portion of the work bench, the safety protection cover covers the engine, the thrust testing mechanism comprises a fixed support and a thrust sensor, the engine is fixed on the fixed support, the fixed support is arranged on a sliding rail, the fixed support is connected with the thrust sensor, the sliding rail is arranged on the upper portion of the work bench, the engine is connected with an engine controller through a bidirectional signal communication link, the engine controller is connected with a display screen, a rotating speed sensor, a temperature sensor and the thrust sensor, the rotating speed sensor is connected with a rotating shaft of the engine, the temperature sensor is arranged at an exhaust port of the engine, the fuel feed mechanism includes defeated oil pipe way, oil tank, oil pump, shut-off valve and oil strain, defeated oil pipe way one end with the oil tank is connected, the other end with the engine is connected, the oil tank with be provided with on the defeated oil pipe way between the engine oil pump, shut-off valve with oil strain, the oil pump with the shut-off valve with engine controller connects, be connected with control on the controller the handle switch of throttle lever on the engine.
2. An aircraft engine test run training device as defined in claim 1, wherein: the safety protection cover adopts transparent organic glass to make, the safety protection cover is detachable safety protection cover, the engine will when out of work the safety protection cover pull down and place in inside the work bench frame, the engine during operation uses the safety protection cover covers the engine.
3. An aircraft engine test run training device as defined in claim 1, wherein: the engine is a turbojet engine, and an AT89C52 chip is adopted in the controller; the model of the rotating speed sensor is CS-1, the model of the temperature sensor is TR02005, and the model of the thrust sensor is QLW-20.
4. An aircraft engine test run training device as defined in claim 1, wherein: the oil is strained and is passed through defeated oil pipe way with the engine is connected, the oil pump passes through defeated oil pipe way with the oil tank is connected, the oil pump with be provided with between the oil is strained the shutoff valve.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020556254.2U CN211784284U (en) | 2020-04-15 | 2020-04-15 | Test run training device for aircraft engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202020556254.2U CN211784284U (en) | 2020-04-15 | 2020-04-15 | Test run training device for aircraft engine |
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| Publication Number | Publication Date |
|---|---|
| CN211784284U true CN211784284U (en) | 2020-10-27 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202020556254.2U Expired - Fee Related CN211784284U (en) | 2020-04-15 | 2020-04-15 | Test run training device for aircraft engine |
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| CN (1) | CN211784284U (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114151208A (en) * | 2020-11-30 | 2022-03-08 | 西安交通大学 | Real-time aerial parking monitoring method for aircraft engine |
| CN115014790A (en) * | 2022-06-14 | 2022-09-06 | 南京航空航天大学 | Turbojet engine testing device and method for assembling ceramic matrix composite blades |
-
2020
- 2020-04-15 CN CN202020556254.2U patent/CN211784284U/en not_active Expired - Fee Related
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114151208A (en) * | 2020-11-30 | 2022-03-08 | 西安交通大学 | Real-time aerial parking monitoring method for aircraft engine |
| CN114151208B (en) * | 2020-11-30 | 2023-10-27 | 西安交通大学 | Aerial engine air parking real-time monitoring method |
| CN115014790A (en) * | 2022-06-14 | 2022-09-06 | 南京航空航天大学 | Turbojet engine testing device and method for assembling ceramic matrix composite blades |
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| GR01 | Patent grant | ||
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| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20201027 Termination date: 20210415 |
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| CF01 | Termination of patent right due to non-payment of annual fee |