CN115683637A - Pulse jet device for simulating surge working condition of miniature turbojet engine - Google Patents
Pulse jet device for simulating surge working condition of miniature turbojet engine Download PDFInfo
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- CN115683637A CN115683637A CN202211285266.6A CN202211285266A CN115683637A CN 115683637 A CN115683637 A CN 115683637A CN 202211285266 A CN202211285266 A CN 202211285266A CN 115683637 A CN115683637 A CN 115683637A
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Abstract
The invention relates to a pulse jet device for simulating the surge working condition of a miniature turbojet engine, wherein a jet unit and an air entraining unit are both arranged on a test bed, and the environmental simulation of the miniature turbojet engine under the surge working condition during test is realized through the combined action; the air-entraining unit uses an external fan to supply stable high-pressure airflow to the jet unit through an air-entraining pipeline; the jet unit is positioned in the gas collection cavity, the phase of the pulsating jet in the segmented gas collection cavity is adjusted by adjusting the pulsating jet angle through the hydraulic unit and adjusting the servo valve, and the two together act to simulate the surge working condition of the engine. The invention realizes the change of the pulsating jet flow by changing the direction and the phase of the jet flow on the basis of the test bed of the micro turbojet engine, and can complete the simulation of the surge working condition of the micro turbojet engine caused by different influencing factors.
Description
Technical Field
The invention belongs to the technical field of aero-engines, and particularly relates to a pulse jet device for simulating the surge condition of a miniature turbojet engine.
Background
In recent years, along with the continuous development and progress of science and technology, the unmanned aerial vehicle is widely used, and the application in military and civil aspects is gradually increased. For a specific unmanned aerial vehicle aircraft, the working performance of the whole aircraft is determined by the quality of the used micro turbojet engine, and the corresponding research on the whole aircraft is of practical significance.
Different from large-scale aviation aircrafts, the ground test run of the miniature turbojet engine of the small unmanned aerial vehicle focuses more on the embodiment of the thrust performance of the engine, but the test run simulation under different working conditions is few, the working environment of the unmanned aerial vehicle becomes very complicated in future due to the continuous expansion of the use range of the unmanned aerial vehicle, and the simulation of the surge working condition of the engine in advance has very important significance in order to prolong the service life of the unmanned aerial vehicle and reduce the adverse effect of the environment on the unmanned aerial vehicle.
To date, experimental research on micro turbojet engines has focused primarily on measuring the thrust performance of the engine. In the prior art, a six-degree-of-freedom thrust measurement rack is built by people, and simulation analysis is carried out on the whole engine starting process; a variable-size universal miniature turbine engine test bed is also designed; however, the micro-turbojet engine has been rarely studied for surge failure and the like.
At present, the main method for carrying out the surge test on the engine is fuel oil step, and the method has the disadvantages of complex operation, high risk and easy occurrence of safety accidents; the Kung Guilan team of Nanjing aerospace university blocks a flow path by introducing high-pressure gas to the back of a gas compressor, so that surge of an engine is avoided, but the method introduces the high-pressure gas through an existing gas-introducing port on a diffuser box, the failure rate of the scheme is high, the scheme can only be applied to single type machines, and the universality is poor.
In summary, the existing micro turbojet engine test bed lacks the capability of performing a surge test, and cannot be adjusted according to different types of engines, so that the working performance of the engines cannot be comprehensively evaluated and verified.
Disclosure of Invention
The invention aims to overcome the defects of the prior art and provides a pulse jet device for simulating the surge condition of a micro turbojet engine, wherein the surge condition of the micro turbojet engine is simulated by changing different jet phases and jet angles.
The technical problem to be solved by the invention is realized by the following technical scheme:
the utility model provides a pulse fluidic device that is used for miniature turbojet engine surge operating mode to simulate which characterized in that: the test bed comprises a test bed, an air entraining unit, a hydraulic unit and a jet unit, wherein the air entraining unit and the hydraulic unit are installed on the test bed, the jet unit is installed in the air entraining unit, the air entraining unit provides a stable air source for a jet device, and the jet unit is operated under the action of the hydraulic unit.
Moreover, the test bench includes engine, L type support and bottom plate, install 2L type supports on the bottom plate through the bolt, fixed mounting between two L type supports the engine.
And the air-entraining unit comprises a fan, an air-entraining pipeline, a servo valve and a gas-collecting cavity, the fan is fixedly arranged on the bottom plate, the fan is connected to the gas-collecting cavity through the air-entraining pipeline, the servo valve is arranged on the air-entraining pipeline, the gas-collecting cavity is mounted on an outer casing of the engine through a bolt, and the fan is started to enable the gas-collecting cavity to be filled with high-pressure gas and to be discharged through the jet unit.
And the hydraulic unit comprises a linear stepping motor, a force sensor, a hydraulic actuating cylinder and a hydraulic pipeline, the stepping motor is arranged on the bottom plate, the hydraulic actuating cylinder is connected with the bottom plate through a buckle, the force sensor is connected between the linear stepping motor and the hydraulic actuating cylinder, and the end part of the hydraulic actuating cylinder is connected to the jet unit in the gas collecting cavity through the hydraulic pipeline.
The jet unit comprises an annular hydraulic pipeline, a jet actuator cylinder and a jet nozzle, the jet nozzle is connected with the jet actuator cylinder and an outer casing of the engine through hinges, the annular hydraulic pipeline is connected with the jet actuator cylinder through a quick-connect connector, the annular hydraulic pipeline is installed in a gas collection cavity of the gas entraining unit through a buckle, and the annular hydraulic pipeline conveys liquid to enable the jet actuator cylinder to move and drive the jet nozzle to rotate in the circumferential direction.
Moreover, the gas collecting cavity comprises 4 gas collecting cavity monomers, the 4 gas collecting cavity monomers are connected through bolts to form a ring, and the gas guide pipeline is divided into four branch pipelines and corresponds to the four gas collecting cavity monomers.
Moreover, the number of the jet flow nozzles is 8, and the jet flow nozzles are arranged at equal intervals along the circumferential direction of the axis of the engine. .
The invention has the advantages and beneficial effects that:
1. the invention relates to a pulse jet device for simulating the surge working condition of a miniature turbojet engine, which adopts a gas-collecting and flow-guiding unit with adjustable gas-guiding phases, and can realize different pulse jet impacts by adjusting different phases during gas guiding, thereby completing the simulation of the surge working condition of the engine caused by different phase factors.
2. The invention relates to a pulse jet device for simulating the surge working condition of a miniature turbojet engine, which adopts a blade tip jet device with an adjustable jet angle, wherein a jet nozzle can be adjusted within the range of 0-45 degrees, and the simulation of the surge working condition of the miniature turbojet engine under different jet angles can be realized through the angle adjustment.
3. After the engine test is finished, external cooling airflow can be introduced through the air-entraining unit and the jet unit, so that the cooling speed of the engine is accelerated, the service life of the engine is prolonged, the cycle period of the test is reduced, the engine can be assisted in a high-temperature environment to prolong the test time, and the test frequency is increased.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a schematic structural view of a fluidic unit of the present invention;
FIG. 3 is a schematic view of the initial position of the fluidic unit of the present invention;
FIG. 4 is a schematic diagram of the position of the jet unit when the present invention simulates surge;
fig. 5 is a working principle diagram of the angle adjustment of the jet unit of the invention.
Detailed Description
The present invention is further illustrated by the following specific examples, which are intended to be illustrative, not limiting and are not intended to limit the scope of the invention.
As shown in fig. 1 and 2, a pulse jet device for simulating the surge condition of a miniature turbojet engine is characterized in that: including test bench 1, bleed unit 2, hydraulic unit 3 and fluidic unit 4, bleed unit 2 and hydraulic unit 3 install in on the test bench 1, fluidic unit 4 install in bleed unit 2, bleed unit 2 provides stable air supply for fluidic device, fluidic unit 4 realizes the operation through hydraulic unit 3's effect.
The test bed 1 comprises an engine 5, L-shaped supports 6 and a bottom plate 7, wherein the bottom plate 7 is provided with 2L-shaped supports 6 through bolts, and the engine 5 is fixedly arranged between the two L-shaped supports 6.
The air-entraining unit 2 comprises a fan 8, an air-entraining pipeline 9, a servo valve 10 and a gas-collecting cavity 11, the fan 8 is fixedly installed on the bottom plate 7, the fan 8 is connected to the gas-collecting cavity 11 through the air-entraining pipeline 9, the servo valve 10 is installed on the air-entraining pipeline 9, the gas-collecting cavity 11 is installed on an outer casing of the engine 5 through bolts, and the fan 8 is started to enable the gas-collecting cavity 11 to be filled with high-pressure gas and to be discharged through the jet unit 4.
The gas collecting cavity 11 comprises 4 gas collecting cavity monomers, the 4 gas collecting cavity monomers are connected through bolts to form a ring, the gas guiding pipeline 9 is divided into four branch pipelines and corresponds to the four gas collecting cavity monomers, the four gas collecting cavity monomers can be filled with high-pressure gas according to a specific sequence through adjustment of the servo valve (10), and phase change of pulse jet is achieved.
The hydraulic unit 3 comprises a linear stepping motor 12, a force sensor 13, a hydraulic actuating cylinder 14 and a hydraulic pipeline 15, the stepping motor 12 is installed on the bottom plate 7, the hydraulic actuating cylinder 14 is connected with the bottom plate 7 through a buckle, the force sensor 13 is connected between the linear stepping motor 12 and the hydraulic actuating cylinder 14, the end part of the hydraulic actuating cylinder 14 is connected to the jet unit 4 in the gas collecting cavity 11 through the hydraulic pipeline 15, when a signal is received, the linear stepping motor (12) drives the force sensor (13) and the hydraulic actuating cylinder (14) to move along a straight line, and the linear stepping motor stops when a preset jet angle is reached.
The jet flow unit 4 comprises an annular hydraulic pipeline 16, a jet flow actuating cylinder 17 and a jet flow nozzle 18, the jet flow nozzle 18 is connected with the jet flow actuating cylinder 17 and an outer casing of the engine 5 through hinges, the annular hydraulic pipeline 16 is connected with the jet flow actuating cylinder 17 through a quick-connection connector, the annular hydraulic pipeline 16 is installed in a gas collecting cavity 11 of the air entraining unit 2 through a buckle, the annular hydraulic pipeline 16 conveys liquid to enable the jet flow actuating cylinder 17 to move and drive the jet flow nozzle 18 to rotate along the circumferential direction, and therefore airflow flowing at a diffuser (20) of a centrifugal compressor (19) of the micro turbojet engine is changed.
The number of the jet flow nozzles 18 is 8, and the jet flow nozzles are arranged at equal intervals along the circumferential direction of the axis of the engine 5.
The working principle of the invention is as follows:
the working principle of the invention is as follows:
i, before the device is introduced into jet flow: fig. 3 is a schematic diagram of the position of the jet nozzle before the jet flow is introduced, at this time, the jet nozzle 18 is closed with an outer casing of the engine 5, no external jet flow is introduced, the engine 5 operates normally, the hydraulic cylinder 14 is in the initial position, the air pressure in the air collecting cavity 11 is balanced with the air pressure of the engine, and at this time, a test under the normal working state of the engine can be performed;
II, when the device introduces jet flow at different angles to simulate surge: fig. 4 is a schematic diagram of the position of the jet nozzle when surging is simulated through jet flow, at this time, when the hydraulic unit receives a start signal, the linear stepping motor 12 drives the force sensor 13 and the hydraulic actuator cylinder 14 to move along a straight line, so that the jet nozzle 18 rotates along the circumferential direction, after a specified angle is reached, the force sensor 13 feeds back a signal to stop the movement of the hydraulic actuator cylinder 14, high-pressure airflow inside the gas collection cavity 11 is ejected along the jet nozzle 18, and finally, the flow inside the engine is changed, so that the surging condition is simulated;
III, when the device introduces different phase jet flows to simulate surge: high-pressure airflow is introduced through an external fan (8) and is conveyed into a gas collecting cavity (11) through an air guide pipeline (9), a servo valve (10) connected with the gas collecting cavity with a required phase is adjusted according to requirements, and a jet nozzle (18) rotates along the circumferential direction of the engine under the action of a hydraulic unit, so that the high-pressure airflow in the gas collecting cavity (11) with different phases is emitted along the jet nozzle (18), the gas flow of a diffuser (20) part of a centrifugal compressor (19) is changed, and the surge working condition of the engine is simulated.
The simulation of the surge working condition is not only suitable for the single adjustment of the jet angle and the air-entraining phase, but also suitable for the coupling adjustment of the jet angle and the air-entraining phase.
Although the embodiments of the present invention and the accompanying drawings are disclosed for illustrative purposes, those skilled in the art will appreciate that: various substitutions, changes and modifications are possible without departing from the spirit and scope of the invention and the appended claims, and therefore the scope of the invention is not limited to the disclosure of the embodiments and the accompanying drawings.
Claims (7)
1. The utility model provides a pulse fluidic device that is used for miniature turbojet engine surge operating mode to simulate which characterized in that: including test bench (1), bleed unit (2), hydraulic unit (3) and jet unit (4), bleed unit (2) and hydraulic unit (3) install in on test bench (1), jet unit (4) install in bleed unit (2), bleed unit (2) provide stable air supply for fluidic device, jet unit (4) realize the operation through the effect of hydraulic unit (3).
2. The pulsed waterjet apparatus for surge condition simulation of a micro-turbojet engine according to claim 1, wherein: the test bed (1) comprises an engine (5), L-shaped supports (6) and a bottom plate (7), wherein the bottom plate (7) is provided with 2L-shaped supports (6) through bolts, and the engine (5) is fixedly installed between the two L-shaped supports (6).
3. The pulse jet apparatus for the surge condition simulation of a micro turbojet engine according to claim 2, wherein: bleed unit (2) include fan (8), bleed pipeline (9), servo valve (10) and gas collecting cavity (11), fan (8) fixed mounting in on bottom plate (7), fan (8) are connected to through bleed pipeline (9) gas collecting cavity (11), install servo valve (10) on bleed pipeline (9), gas collecting cavity (11) bolt mounting in on the outer machine casket of engine (5), fan (8) start-up make gas collecting cavity (11) in be filled with high-pressure gas to discharge through fluidic unit (4).
4. The pulsed waterjet apparatus for mini-turbojet engine surge condition simulation of claim 2, wherein: the hydraulic unit (3) comprises a linear stepping motor (12), a force sensor (13), a hydraulic actuating cylinder (14) and a hydraulic pipeline (15), the stepping motor (12) is installed on the bottom plate (7), the hydraulic actuating cylinder (14) is connected with the bottom plate (7) through a buckle, the force sensor (13) is connected between the linear stepping motor (12) and the hydraulic actuating cylinder (14), and the end part of the hydraulic actuating cylinder (14) is connected to the jet unit (4) in the gas collecting cavity (11) through the hydraulic pipeline (15).
5. The pulsed waterjet apparatus for mini-turbojet engine surge condition simulation of claim 2, wherein: the jet flow unit (4) comprises an annular hydraulic pipeline (16), a jet flow actuating cylinder (17) and a jet flow nozzle (18), the jet flow nozzle (18) is connected with the jet flow actuating cylinder (17) and an outer box of the engine (5) through hinges, the annular hydraulic pipeline (16) is connected with the jet flow actuating cylinder (17) through a quick-connection connector, the annular hydraulic pipeline (16) is installed in a gas collection cavity (11) of the air entraining unit (2) through a buckle, and the annular hydraulic pipeline (16) conveys liquid to enable the jet flow actuating cylinder (17) to move to drive the jet flow nozzle (18) to rotate along the circumferential direction.
6. The pulse jet apparatus for the surge condition simulation of a micro turbojet engine according to claim 3, wherein: the gas collecting cavity (11) comprises 4 gas collecting cavity monomers, the 4 gas collecting cavity monomers are connected through bolts to form a ring, and the gas guide pipeline (9) is divided into four branch pipelines and corresponds to the four gas collecting cavity monomers.
7. The pulsed waterjet apparatus for surge condition simulation of a micro-turbojet engine according to claim 5, wherein: the number of the jet flow nozzles (18) is 8, and the jet flow nozzles are circumferentially arranged at equal intervals along the axis of the engine (5).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202211285266.6A CN115683637A (en) | 2022-10-20 | 2022-10-20 | Pulse jet device for simulating surge working condition of miniature turbojet engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202211285266.6A CN115683637A (en) | 2022-10-20 | 2022-10-20 | Pulse jet device for simulating surge working condition of miniature turbojet engine |
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| CN115683637A true CN115683637A (en) | 2023-02-03 |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118130026A (en) * | 2024-04-30 | 2024-06-04 | 太原科技大学 | Vibration resistance performance test device for aero-engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN118130026A (en) * | 2024-04-30 | 2024-06-04 | 太原科技大学 | Vibration resistance performance test device for aero-engine |
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