CN215811639U - Automatic cycle test system for test run of micro turbojet engine - Google Patents
Automatic cycle test system for test run of micro turbojet engine Download PDFInfo
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- CN215811639U CN215811639U CN202122244470.0U CN202122244470U CN215811639U CN 215811639 U CN215811639 U CN 215811639U CN 202122244470 U CN202122244470 U CN 202122244470U CN 215811639 U CN215811639 U CN 215811639U
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- engine
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- oil
- oil pump
- power supply
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- 238000012360 testing method Methods 0.000 title claims abstract description 68
- 239000003921 oil Substances 0.000 claims abstract description 48
- RZVHIXYEVGDQDX-UHFFFAOYSA-N 9,10-anthraquinone Chemical group C1=CC=C2C(=O)C3=CC=CC=C3C(=O)C2=C1 RZVHIXYEVGDQDX-UHFFFAOYSA-N 0.000 claims abstract description 18
- 238000006243 chemical reaction Methods 0.000 claims abstract description 18
- 239000000295 fuel oil Substances 0.000 claims abstract description 9
- 239000010687 lubricating oil Substances 0.000 claims abstract description 9
- 238000001228 spectrum Methods 0.000 claims abstract description 8
- 230000005540 biological transmission Effects 0.000 claims description 9
- 230000004044 response Effects 0.000 abstract description 2
- 230000006870 function Effects 0.000 description 4
- 238000000034 method Methods 0.000 description 4
- 238000010586 diagram Methods 0.000 description 2
- 239000000446 fuel Substances 0.000 description 2
- 238000011056 performance test Methods 0.000 description 1
- 239000007858 starting material Substances 0.000 description 1
- 238000012795 verification Methods 0.000 description 1
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Abstract
The utility model relates to an automatic cycle test system for test run of a micro turbojet engine, which comprises an engine, an oil supply system, a control system and a power supply system. The oil supply system comprises fuel oil, lubricating oil and an oil pump; the control system comprises an electronic control unit, a signal conversion plate, a ground auxiliary unit, a computer, a flight control signal receiver and a flight controller; the power supply system comprises a power battery and a power supply battery. The utility model has the advantages that: when a large number of test runs with repeatability and complex load spectrum are needed for verifying the service life of engine parts or examining the overall performance of the engine, the test runs can be automatically and circularly carried out by compiling a test sequence through a computer, so that the workload of testers is greatly reduced. When a verified test vehicle with a small number of test times needs to be tested, the engine can be manually and remotely tested through the flight controller, and the test vehicle has the advantages of convenience, high response speed and the like.
Description
Technical Field
The utility model relates to the technical field of test runs of aero-engines, in particular to an automatic cycle test system for test runs of a micro turbojet engine.
Background
The aircraft engine provides flight power for the aircraft, works above the high altitude, and once the engine breaks down in power, the aircraft loses power, and the aircraft can not guarantee normal flight or even crash and other major accidents. Therefore, before any aircraft engine is put into service formally, the performance, function, strength and reliability of the aircraft engine must be tested, wherein ground test of the engine is an important link.
SUMMERY OF THE UTILITY MODEL
The utility model aims to solve a series of problems that in the prior art, a ground test run circulation test of a micro turbojet engine needs personnel to continuously perform starting-slow running-maximum cruising-stopping operations of the engine, the steps are complicated, the energy is consumed, the circulation test is to examine the service life of the engine, the test times are inevitably thousands of times, and once the personnel fails in operation, unnecessary loss is caused, and the like, and provides an automatic circulation test system for the test run of the micro turbojet engine.
The utility model is realized by the following technical scheme.
An automatic cycle test system for test run of a micro turbojet engine comprises the engine, an oil supply system, a control system and a power supply system. The oil supply system comprises fuel oil, lubricating oil and an oil pump, the fuel oil and the lubricating oil can be respectively connected with the oil pump through an oil delivery pipe, and can also be connected with the oil pump through the oil delivery pipe after being mixed, and the oil pump delivers the fuel oil and the lubricating oil into the engine through the oil delivery pipe; the control system comprises an electronic control unit, a signal conversion plate, a ground auxiliary unit, a computer, a flight control signal receiver and a flight controller, wherein the electronic control unit is respectively connected with an oil pump, the signal conversion plate and the flight control signal receiver through data transmission lines and is connected with an engine and a power battery through power lines; the power supply system comprises a power battery and a power supply battery, the power battery is connected with the electronic controller through a power line, and the power supply battery is connected with the flight control signal receiver through the power line.
Compared with the prior art, the utility model has the advantages that: when the test run test of the micro turbojet engine is carried out, the test run test can be carried out automatically and circularly through the test sequence compiled by the computer, and the test run of the engine can be carried out manually and remotely through the flight controller. The automatic cycle test is carried out by the computer-programmed test sequence, so that the consistency of the load spectrum of each operation of the engine can be ensured, the workload of testers can be greatly reduced when a large number of repeated test runs with complex load spectrums are required to be carried out for verifying the service life of engine parts or examining the overall performance of the engine, and unnecessary loss or accidents caused by fatigue of the testers are avoided; the engine can be quickly started and stopped by manually and remotely testing through the flight controller, and the method has the advantages of convenience, quick response and the like when a verified test run with a small number of testing times is required.
Drawings
FIG. 1 is a block diagram illustrating a test architecture of an automatic cycle test system for ground test of a micro turbojet engine in accordance with the present invention;
FIG. 2 is an operational interface diagram showing computer test software programmed with an automatic cycle test system for ground test of a micro turbojet engine according to the present invention.
For clarity, a brief description of the reference numerals is given below:
000: engine
100: oil supply system
101: fuel oil and lubricating oil
102: oil pump
200: control system
201: electronic control unit
202: signal conversion board
203: ground auxiliary unit
204: computer with a memory card
205: flight control signal receiver
206: flight controller
300: power supply system
301: power battery
302: power supply battery
10: actual state display bar
11: engine rotating speed display dial plate
12: engine exhaust temperature display dial
13: throttle ratio and oil pump voltage status bar
14: electronic controller current and power battery voltage display column
15: automatic cycle test load spectrum compilation sequence
16: oscilloscope for engine operation parameters
17: the signal conversion board is connected into the display area
18: remote control and computer control switching and state display area
19: start test task key and software exit key area
Detailed Description
The utility model is further described with reference to the following figures and specific examples. But not as a limitation of the utility model.
As shown in fig. 1, an automatic cycle test system for a test run of a micro turbojet engine includes an engine 000, an oil supply system 100, a control system 200, and a power supply system 300. The oil supply system 100 comprises fuel oil and lubricating oil 101 and an oil pump 102; the control system comprises an electronic control unit 201, a signal conversion board 202, a ground auxiliary unit 203, a computer 204, a flight control signal receiver 205 and a flight controller 206; the power supply system comprises a power battery 301 and a power supply battery 302.
In a preferred embodiment, the engine 000 is provided with a main board for mounting a series of sensors such as a thermocouple, a rotation speed sensor, and an airspeed sensor, and the main board receives signals from the electronic control unit 201, processes, determines, and controls the operation of the engine. The engine 000 can be used as a platform for checking engine parts and can also be used for carrying out performance test on a certain type of engine.
As a further specific embodiment, the engine 000 is connected to the oil pump 102 through an oil pipe and is connected to the electronic control unit 201 through a power supply line.
In a preferred embodiment, the fuel and oil 101 may be connected to the oil pump 102 through a flow line, or may be mixed and connected to the oil pump 102 through a flow line, and the oil pump 102 functions to deliver the fuel and oil into the engine through the flow line.
In a preferred embodiment, the electronic control unit 201 is configured to calculate, process and determine information from the engine 000, the oil pump 102, the data conversion board 202 and the flight control signal receiver 205 according to a program and data stored in a memory, and then output a command to provide a certain signal to the engine 000 to control the operation of the engine, a certain signal to the oil pump 102 to control the oil supply amount, transmit information to the data conversion board 202, and feed back a signal to the flight control signal receiver 205.
As a further specific embodiment, the electronic control unit 201 is connected with the oil pump 102, the signal conversion board 202 and the flight control signal receiver 205 through data transmission lines, and is connected with the engine 000 and the power battery 301 through power lines.
As a preferred embodiment, the signal conversion board 202 is used for converting an analog signal from the electronic control unit 201 into a digital signal that can be recognized by the ground auxiliary unit 203.
As a further specific embodiment, the signal conversion board 202 is connected to the electronic control unit 201 and the ground auxiliary unit 203 through data transmission lines.
As a preferred embodiment, the ground auxiliary unit 203 functions such that information such as an oil pump voltage, an exhaust temperature of the engine, an engine speed, a power battery voltage, an operation state of the engine, etc. can be observed at any time by operating the ground auxiliary unit 203. When the engine is replaced, a "learning" of the engine main board can be performed by the ground auxiliary unit 203 to adapt the electronic control unit 201. Before the ground test of the engine, the motor can be used for driving the rotor of the engine through the ground auxiliary unit 203, whether the rotor scratches a casing or not is checked, and oil discharge of the oil pump can be carried out so as to ensure that no air is reserved in the oil delivery pipe.
As a further specific embodiment, the ground auxiliary unit 203 is connected to the signal conversion board 202 and the computer 204 through data transmission lines.
In a preferred embodiment, the computer 204 is used for loading computer test software programmed by an automatic cycle test system for ground test of the micro turbojet engine.
In a preferred embodiment, the flight control signal receiver 205 is configured to receive the PWM pulse width modulation signal transmitted by the flight controller 206 and transmit the signal to and from the electronic control unit 201.
As a further specific embodiment, the flight control signal receiver 205 is connected to the electronic control unit 201 via a data transmission line and to the power supply battery 302 via a power line.
As a preferred embodiment, the flight controller 206 has the functions of operating the engine for ignition, controlling the throttle, stopping the vehicle and the like by recoding, and provides a technical premise for manually and remotely controlling the engine to test.
As a further specific embodiment, the flight controller 206 and the flight control signal receiver 205 are connected by transmitting PWM pulse width modulation signals.
As a preferred embodiment, the power battery 301 is used to provide power for the engine starting motor.
As a further specific embodiment, the power battery 301 is connected to the electronic control unit 201 via a power cord and delivers current to the engine starter motor.
In a preferred embodiment, the power supply battery 302 is used to power the flight control signal receiver 205.
As a further specific embodiment, the power supply battery 302 is connected to the flight control signal receiver 205 via a power line.
Before the test, the circuit is connected according to the test structure of the automatic cycle test system for the ground test of the micro turbojet engine shown in figure 1. When a large number of test runs with repeatability and complex load spectrum are carried out, the automatic cycle test software of the engine carried by the computer can be used. After the software is turned on, firstly, whether the signal conversion board access display area 17 is a green light is observed; secondly, clicking a start task in a start test task key and software exit key area 19; thirdly, editing the load spectrum to be operated in the automatic cycle test load spectrum compiling sequence 15, and then clicking a storage sequence to start automatic test; fourthly, various parameters in the running process of the engine can be displayed on an actual state display column 10, an engine rotating speed display dial 11, an engine exhaust temperature display dial 12, an accelerator proportion and oil pump voltage state column 13, an electronic controller current and power battery voltage display column 14 and an engine running parameter oscilloscope 16; fifth, if the remote control is to be changed, the operation can be performed in the remote control and computer control switching and status display area 18. When a verification test car with a small number of test times is carried out, the flight controller can be used for carrying out manual and remote test.
While the utility model has been described with reference to a preferred embodiment, it will be understood by those skilled in the art that various changes in form and detail may be made therein without departing from the spirit and scope of the utility model.
Claims (2)
1. An automatic cycle test system for test run of a micro turbojet engine is characterized by comprising an engine (000), an oil supply system (100), a control system (200) and a power supply system (300); the oil supply system (100) comprises fuel oil and lubricating oil (101) and an oil pump (102); the control system (200) comprises an electronic control unit (201), a signal conversion board (202), a ground auxiliary unit (203), a computer (204), a flight control signal receiver (205) and a flight controller (206); the power supply system comprises a power battery (301) and a power supply battery (302); the engine (000) is connected with the oil pump (102) through an oil pipeline and is connected with the electronic control unit (201) through a power line; the fuel oil and the lubricating oil (101) are connected with the oil pump (102) through an oil delivery pipe or are connected with the oil pump (102) through the oil delivery pipe after being mixed, and the oil pump (102) is used for delivering the fuel oil and the lubricating oil into the engine through the oil delivery pipe; the electronic control unit (201) is respectively connected with the oil pump (102), the signal conversion board (202) and the flight control signal receiver (205) through data transmission lines and is connected with the engine (000) and the power battery (301) through power lines; the signal conversion board (202) is connected with the electronic control unit (201) and the ground auxiliary unit (203) through data transmission lines; the ground auxiliary unit (203) is connected with the signal conversion board (202) and the computer (204) through data transmission lines; the flight control signal receiver (205) is connected with the electronic control unit (201) through a data transmission line and is connected with the power supply battery (302) through a power line; the flight controller (206) and the flight control signal receiver (205) are connected through transmitting PWM pulse width modulation signals.
2. The automatic cycle testing system for a micro turbojet engine test run according to claim 1 wherein the computer test software operating interface programmed by the automatic cycle testing system for a micro turbojet engine ground test run comprises: the device comprises an actual state display field (10), an engine rotating speed display dial plate (11), an engine exhaust temperature display dial plate (12), an accelerator proportion and oil pump voltage state field (13), an electronic controller current and power battery voltage display field (14), an automatic cycle test load spectrum compilation sequence (15), an engine operation parameter oscilloscope (16), a signal conversion board access display area (17), a remote control and computer control switching and state display area (18) and a test starting task key and software exit key area (19).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122244470.0U CN215811639U (en) | 2021-09-16 | 2021-09-16 | Automatic cycle test system for test run of micro turbojet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202122244470.0U CN215811639U (en) | 2021-09-16 | 2021-09-16 | Automatic cycle test system for test run of micro turbojet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN215811639U true CN215811639U (en) | 2022-02-11 |
Family
ID=80163263
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202122244470.0U Expired - Fee Related CN215811639U (en) | 2021-09-16 | 2021-09-16 | Automatic cycle test system for test run of micro turbojet engine |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN215811639U (en) |
-
2021
- 2021-09-16 CN CN202122244470.0U patent/CN215811639U/en not_active Expired - Fee Related
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| Date | Code | Title | Description |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20220211 |