CN210037462U - Aviation high pressure fuel pipe high temperature pulse test device - Google Patents
Aviation high pressure fuel pipe high temperature pulse test device Download PDFInfo
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- CN210037462U CN210037462U CN201920305673.6U CN201920305673U CN210037462U CN 210037462 U CN210037462 U CN 210037462U CN 201920305673 U CN201920305673 U CN 201920305673U CN 210037462 U CN210037462 U CN 210037462U
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Abstract
A high-temperature pulse test device for an aviation high-pressure oil pipe comprises a hydraulic power system, a pressure control system, a pressure pipeline, a high-temperature test box and a cooling system, the actual use working condition of the aviation high-pressure oil pipe is simulated, the test pressure, the test temperature and the test frequency can be adjusted according to different use working conditions, and the device is relatively simple to operate; multiple groups of samples can be tested simultaneously, so that the working efficiency is greatly improved, and energy conservation and emission reduction can be realized.
Description
Technical Field
The utility model relates to an aviation high pressure fuel pipe performance check out test set field, concretely relates to aviation high pressure fuel pipe high temperature pulse test device.
Background
The high-pressure oil pipe is widely applied in various industries and is an important part in hydraulic transmission products, and the hydraulic transmission products are more important in aviation industry application. The high-pressure oil pipe detected at this time is in a high-temperature environment in actual use, and the pressure in the pipe is continuously changed, so that the oil pipe is continuously subjected to pulse vibration to greatly damage the oil pipe and a joint, and once the oil pipe is broken or the joint is loosened, an oil leakage phenomenon occurs, which may cause serious faults to equipment.
At present, the national military standard has definite requirements on tests, but no standard regulation is provided for experimental equipment, and the equipment has larger difference. In order to ensure the use reliability of the high-pressure oil pipe, experimental equipment needs to simulate the working condition of the high-pressure oil pipe in the use process and perform high-temperature pulse tests on the high-pressure oil pipe for specified times, so that the safety of the equipment and personnel is guaranteed.
Disclosure of Invention
For solving the problem of above-mentioned prior art, the utility model provides an aviation high pressure fuel pipe high temperature pulse test device, simulation aviation high pressure fuel pipe's the in-service use operating mode test pressure, test temperature and experimental frequency can all adjust according to the use operating mode of difference.
In order to achieve the above purpose, the utility model adopts the following technical scheme: a high-temperature pulse test device for an aviation high-pressure oil pipe comprises a hydraulic power system, a pressure control system, a pressure pipeline, a high-temperature test box and a cooling system, wherein the pressure control system is a main component for controlling pulse test conditions and is arranged on the pressure pipeline; the hydraulic power system is connected with the high-temperature test box through a pressure pipeline, so that pulse energy of the hydraulic power system is transmitted into the high-temperature test box through the pressure pipeline; the cooling system comprises two parts, one part is arranged in the hydraulic power system and is responsible for cooling the temperature of a hydraulic medium in the hydraulic power system, and the other part is arranged on the pressure pipeline and is close to one side of the high-temperature test box and is responsible for cooling the heat transferred by the high-temperature test box in the pressure pipeline; the high-temperature test chamber is provided with a transparent window so that the test state can be observed, a pipeline mounting hole is reserved, the pressure pipeline extends into the high-temperature test chamber and is divided into a plurality of joints, and the end parts of the joints are provided with threads to be connected with an oil pipe to be tested.
Furthermore, the hydraulic power system adopts a hydraulic fitting with rated pressure not less than 33MPa and suitable for high-temperature heat conduction oil.
Furthermore, the high-temperature test chamber adopts a test chamber with the highest temperature reaching 300 ℃.
Furthermore, the pressure control system comprises a pressure regulating valve, a pressure sensor, a frequency controller and an electromagnetic valve, wherein the pressure sensor is arranged on the pressure pipeline, detects the pressure of the pressure pipeline and is connected with the frequency controller; the pressure regulating valve is arranged on the pressure pipeline, is connected with the pressure sensor and regulates the pressure of the pressure pipeline according to the pressure fed back by the pressure sensor; the electromagnetic valve is installed on the pressure pipeline, the frequency controller is connected with the electromagnetic valve, and the pulse frequency of the pressure pipeline is controlled through the frequency controller.
Furthermore, the number of the joints in the high-temperature test box is an even number which is more than or equal to 2, the corresponding number of the joints can be selected according to the experiment requirement, and the rest of the joints are sealed by hydraulic plugs.
Compared with the prior art, the beneficial effects of the utility model are that:
1) the device more closely simulates the actual use working condition of the aviation high-pressure oil pipe, the test pressure, the test temperature and the test frequency can be adjusted according to different use working conditions, and the device is relatively simple to operate;
2) the number of the oil pipes to be tested in the test can be adjusted according to different requirements, namely, a plurality of groups of samples can be tested simultaneously, so that the working efficiency is greatly improved, and the energy conservation and emission reduction can be realized;
3) the cooling system comprises two parts, and can cool heat generated by a hydraulic oil pump in a hydraulic power system under a high-pressure state and heat transferred along a pressure pipeline and a medium in a high-temperature test box.
Drawings
In order to illustrate the embodiments of the present invention or the technical solutions in the prior art more clearly, the drawings needed to be used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and those skilled in the art can also obtain other drawings according to the drawings without any inventive work.
Fig. 1 is a schematic structural view of the present invention;
the device comprises a hydraulic power system 1, a pressure control system 2, a pressure pipeline 3, a high-temperature test box 4, a cooling system 5, an oil pipe 6 to be tested, a pressure regulating valve 21, a pressure sensor 22, a frequency controller 23, an electromagnetic valve 24, a pipeline mounting hole 41 and a joint 42.
Detailed Description
In order to make the objects, technical solutions and advantages of the embodiments of the present invention clearer, the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention, and it is obvious that the described embodiments are some, but not all, embodiments of the present invention. Based on the embodiments in the present invention, all other embodiments obtained by a person skilled in the art without creative efforts belong to the protection scope of the present invention.
Example 1:
as shown in the figure:
a high-temperature pulse test device for an aviation high-pressure oil pipe comprises a hydraulic power system 1, a pressure control system 2, a pressure pipeline 3, a high-temperature test box 4 and a cooling system 5, wherein the pressure control system 2 is a main component for controlling pulse test conditions and is arranged on the pressure pipeline 3; the hydraulic power system 1 is connected with the high-temperature test box 4 through a pressure pipeline 3, so that the pulse energy of the hydraulic power system 1 is transmitted into the high-temperature test box 4 through the pressure pipeline 3; the cooling system 5 comprises two parts, one part is arranged in the hydraulic power system 1 and is responsible for cooling the temperature of the hydraulic medium in the hydraulic power system 1, and the other part is arranged on the pressure pipeline 3 and is close to one side of the high-temperature test box 4 and is responsible for cooling the heat transferred by the high-temperature test box 4 in the pressure pipeline 3; the high-temperature test chamber 4 is provided with a transparent window so that the test state can be observed, a pipeline mounting hole 41 is reserved, the pressure pipeline 3 extends into the high-temperature test chamber 4 and is divided into a plurality of joints 42, and the end parts of the joints 42 are provided with threads to be connected with an oil pipe 6 to be tested.
The hydraulic power system 1 adopts hydraulic fittings with rated pressure not less than 33MPa and suitable for high-temperature heat conduction oil.
The high-temperature test chamber 4 adopts a test chamber with the highest temperature reaching 300 ℃.
The pressure control system 2 comprises a pressure regulating valve 21, a pressure sensor 22, a frequency controller 23 and an electromagnetic valve 24, wherein the pressure sensor 22 is installed on the pressure pipeline 3, detects the pressure of the pressure pipeline 3 and is connected with the frequency controller 23; the pressure regulating valve 21 is installed on the pressure pipeline 3, is connected with the pressure sensor 22, and regulates the pressure of the pressure pipeline 3 according to the pressure fed back by the pressure sensor 22; the electromagnetic valve 24 is installed on the pressure pipeline 3, the frequency controller 23 is connected with the electromagnetic valve 24, and the pulse frequency of the pressure pipeline 3 is controlled through the frequency controller 23.
The number of the joints 42 in the high-temperature test box 4 is an even number greater than or equal to 2, the corresponding number of the joints 42 can be selected according to the experiment requirement, and the rest of the joints are sealed by hydraulic plugs.
When the device is used, one end of the pressure pipeline 3 is connected with an oil outlet of the hydraulic power system 1, the other end of the pressure pipeline is installed in the high-temperature test box 4 and fixed, four joints 42 connected with an oil pipe 6 to be tested are reserved, other joints 42 are sealed by hydraulic plugs, and the middle part of the pressure pipeline 3 passes through the cooling system 5 to prevent heat from being transmitted back to the hydraulic power system 1; adding high-temperature heat conduction oil into the hydraulic power system 1, installing an oil pipe 6 to be tested on a pressure pipeline joint 42 reserved in the high-temperature test box 4, starting the hydraulic power system 1 after opening the cooling system 5, adjusting a pressure regulating valve on the hydraulic power system 1, adjusting the pressure to required test pressure, setting parameters of the frequency controller 23 on the pressure control system 2 according to test requirements, setting a temperature value of the high-temperature test box 4 according to the test requirements, and starting a test after the temperature reaches the set temperature.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit it; although the present invention has been described in detail with reference to the foregoing embodiments, it should be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention in its corresponding aspects.
Claims (5)
1. The utility model provides an aviation high pressure fuel pipe high temperature pulse test device which characterized in that: the device comprises a hydraulic power system, a pressure control system, a pressure pipeline, a high-temperature test box and a cooling system, wherein the pressure control system is a main part for controlling pulse test conditions and is arranged on the pressure pipeline; the hydraulic power system is connected with the high-temperature test box through a pressure pipeline, so that pulse energy of the hydraulic power system is transmitted into the high-temperature test box through the pressure pipeline; the cooling system comprises two parts, one part is arranged in the hydraulic power system and is responsible for cooling the temperature of a hydraulic medium in the hydraulic power system, and the other part is arranged on the pressure pipeline and is close to one side of the high-temperature test box and is responsible for cooling the heat transferred by the high-temperature test box in the pressure pipeline; the high-temperature test chamber is provided with a transparent window so that the test state can be observed, a pipeline mounting hole is reserved, the pressure pipeline extends into the high-temperature test chamber and is divided into a plurality of joints, and the end parts of the joints are provided with threads to be connected with an oil pipe to be tested.
2. The high-temperature pulse testing device for the aviation high-pressure oil pipe according to claim 1, characterized in that: the hydraulic power system adopts hydraulic fittings with rated pressure not less than 33MPa and suitable for high-temperature heat conduction oil.
3. The high-temperature pulse testing device for the aviation high-pressure oil pipe according to claim 1, characterized in that: the high-temperature test chamber adopts a test chamber with the highest temperature reaching 300 ℃.
4. The high-temperature pulse testing device for the aviation high-pressure oil pipe according to claim 1, characterized in that: the pressure control system comprises a pressure regulating valve, a pressure sensor, a frequency controller and an electromagnetic valve, wherein the pressure sensor is arranged on a pressure pipeline, detects the pressure of the pressure pipeline and is connected with the frequency controller; the pressure regulating valve is arranged on the pressure pipeline, is connected with the pressure sensor and regulates the pressure of the pressure pipeline according to the pressure fed back by the pressure sensor; the electromagnetic valve is installed on the pressure pipeline, the frequency controller is connected with the electromagnetic valve, and the pulse frequency of the pressure pipeline is controlled through the frequency controller.
5. The high-temperature pulse testing device for the aviation high-pressure oil pipe according to claim 1, characterized in that: the number of the joints in the high-temperature test box is an even number which is more than or equal to 2, the joints with the corresponding number can be selected according to the experiment requirement, and the rest joints are sealed by hydraulic plugs.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920305673.6U CN210037462U (en) | 2019-03-12 | 2019-03-12 | Aviation high pressure fuel pipe high temperature pulse test device |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920305673.6U CN210037462U (en) | 2019-03-12 | 2019-03-12 | Aviation high pressure fuel pipe high temperature pulse test device |
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| CN210037462U true CN210037462U (en) | 2020-02-07 |
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| CN201920305673.6U Active CN210037462U (en) | 2019-03-12 | 2019-03-12 | Aviation high pressure fuel pipe high temperature pulse test device |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114720114A (en) * | 2022-06-10 | 2022-07-08 | 沈阳美茵联合检测有限公司 | Aviation hydraulic conduit test sample piece and sine wave pulse fatigue test method thereof |
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2019
- 2019-03-12 CN CN201920305673.6U patent/CN210037462U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN114720114A (en) * | 2022-06-10 | 2022-07-08 | 沈阳美茵联合检测有限公司 | Aviation hydraulic conduit test sample piece and sine wave pulse fatigue test method thereof |
| CN114720114B (en) * | 2022-06-10 | 2022-08-12 | 沈阳美茵联合检测有限公司 | Aviation hydraulic conduit test sample piece and sine wave pulse fatigue test method thereof |
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