Pressure correction device, oil delivery system and correction method for pressure test

Abstract

The application discloses a pressure correction device, an oil delivery system and a pressure test correction method. The pressure correction device comprises a correction assembly and a temperature detection assembly. The correction assembly comprises a mounting body, a pressure relief valve and a pressure measurement assembly. When the temperature difference between the underground temperature and the surface temperature is greater than or equal to a preset temperature difference, the fuel pipeline is in a pressure test state. Otherwise, the fuel pipeline is in a non-pressure test state. By switching the pressure relief valve between the open state and the closed state, the pressure value is kept within a preset test pressure range when the fuel pipeline is in the pressure test state. The pressure test correction method in the application is beneficial to achieving pressure correction by pressure relief during the pressure test process, ensuring the accuracy of the pressure test, and further avoiding the risk of damaging the fuel pipeline and improving the stability of the fuel pipeline.

Description

Technical Field

[0001] This application relates to the field of pipeline pressure testing, and more particularly to a pressure correction device, an oil transportation system, and a pressure testing correction method. Background Technology

[0002] In aerospace and aviation fuel fields, aircraft refueling is typically carried out via pipelines located beneath the apron. Generally, aviation fuel apron pipelines are laid beneath airport parking positions and are used to supply fuel to aircraft. According to the "Design Specifications for Fuel Supply Engineering of Civil Transport Airports," regular pressure tests are required for aviation fuel apron pipelines to ensure their stable operation.

[0003] However, the pressure of aviation fuel is greatly affected by temperature, and changes in temperature can easily cause pressure fluctuations, making it difficult to meet actual pressure testing requirements. Especially at higher temperatures, the increased evaporation rate of aviation fuel can lead to excessive pressure in the fuel supply lines, exceeding the pressure range required for testing. This not only reduces the accuracy of the pressure test but also causes irreversible damage to the supply lines, increasing the risk of leaks over time. Summary of the Invention

[0004] This application provides a pressure calibration device, a fuel delivery system, and a calibration method for pressure testing. The calibration device in this application facilitates pressure calibration by depressurization during pressure testing, ensuring the accuracy of the pressure test and further avoiding the risk of damage to the fuel pipeline, thereby improving the stability of the fuel pipeline.

[0005] The technical solution is as follows:

[0006] According to a first aspect of the embodiments of this application, a pressure correction device is provided for use with aviation fuel pipelines, the pressure correction device including a correction component and a temperature detection component.

[0007] The calibration assembly includes a mounting body, a pressure relief valve, and a pressure measuring component. The mounting body is detachably connected to the fuel line, ensuring communication between the mounting body and the fuel line when they are engaged. The pressure relief valve is connected to the mounting body to release pressure from both the mounting body and the fuel line. The pressure measuring component is connected to the mounting body and is used to detect the pressure readings on the mounting body.

[0008] The temperature detection assembly includes a first temperature detector and a second temperature detector. The first temperature detector is used to acquire the surface temperature. The second temperature detector is used to acquire the underground temperature.

[0009] When the temperature difference between the underground temperature and the ground temperature is greater than or equal to the preset temperature difference, the aviation fuel pipeline is in a pressure test state, and the stop valves at the two ends of the aviation fuel pipeline test section are in a closed state. Otherwise, the aviation fuel pipeline is in a non-pressure test state, and the stop valves at the two ends of the aviation fuel pipeline test section are in an open state. Wherein,

[0010] When the pressure relief valve is in an open state, the mounting body and the aviation fuel pipeline are relieved through the pressure relief valve. When the pressure relief valve is in a closed state, the mounting body and the aviation fuel pipeline are not in communication with the pressure relief valve for pressure relief. Through switching of the pressure relief valve between the open state and the closed state, when the aviation fuel pipeline is in a pressure test state, the pressure value is kept within the preset test pressure range.

[0011] The technical scheme provided by the embodiment of the application can include the following beneficial effects:

[0012] Generally, the ground aviation fuel in the aviation fuel pipeline is close to the ground temperature, so by measuring the ground temperature and the underground temperature, it can be judged whether the temperature difference between the ground temperature and the underground temperature can provide sufficient evaporation heat for aviation fuel evaporation using the underground temperature, so that the pressure in the aviation fuel pipeline automatically reaches the pressure of the pressure test, realizes automatic pressure rise, and meets the requirements of the pressure test. When the pressure exceeds the pressure of the pressure test, the pressure relief valve can be opened to appropriately relieve the aviation fuel pipeline, so that it meets the pressure range of the pressure test, and finally corrects and performs pressure test, to ensure the accuracy of the pressure test, and avoid the increase of the pressure bearing burden of the aviation fuel pipeline due to the excessively high pressure.

[0013] The technical scheme is further described as follows:

[0014] In one of the embodiments, the correction assembly further includes a first ball valve and a second ball valve. The mounting body includes a first pipeline, a second pipeline and a third pipeline. The aviation fuel pipeline, the first pipeline and the pressure measurement assembly are sequentially communicated to form a first branch. The pressure relief valve and the first ball valve are sequentially communicated through the second pipeline to form a second branch. The pressure relief valve and the second ball valve are sequentially communicated through the third pipeline to form a third branch. The second branch and the third branch are connected in parallel to the first branch, and the second branch and the third branch are sequentially arranged from top to bottom along the gravity direction. Wherein,

[0015] When the aviation fuel pipeline is in a pressure test state and the pressure relief valve is in a closed state, the first ball valve and the second ball valve are both in a closed state, so that at least part of the second branch and the third branch are not in communication with the first branch.

[0016] When the aviation fuel pipeline is in a pressure test state and the pressure relief valve is in an open state, the first ball valve is in an open state and the second ball valve is in a closed state, so that the second branch is in communication with the first branch, and at least part of the third branch is not in communication with the first branch.

[0017] When the fuel pipeline is in the non-pressure testing state, the pressure relief valve is in the closed state, and the second ball valve is in the open state, so that the first branch and the third branch are communicated to discharge the fluid in the installation body through the third branch.

[0018] In one of the embodiments, the pressure correction device further comprises a recovery barrel. The recovery barrel is in communication with one end of the second branch away from the pressure relief valve and one end of the third branch away from the pressure relief valve to receive the fluid discharged from the second branch and the third branch.

[0019] In one of the embodiments, the pressure measuring assembly is an electronic pressure gauge.

[0020] In one of the embodiments, the pressure measuring assembly comprises a communicating vessel assembly. One end of the communicating vessel assembly is in communication with the atmospheric pressure, and the other end is in communication with the installation body. The communicating vessel assembly is provided with a scale rack. The pressure value is obtained by reading the scale rack.

[0021] In one of the embodiments, the pressure correction device further comprises a controller. The controller is in communication with the pressure measuring assembly, the temperature detecting assembly, and the stop valve to enable the controller to determine the switching of the fuel pipeline between the pressure testing state and the non-pressure testing state and to control the switching of the pressure relief valve between the open state and the closed state.

[0022] According to a second aspect of the embodiments of the present application, an oil delivery system is provided, which comprises an oil storage tank, a fuel pipeline, a plurality of stop valves, and the pressure correction device in the above embodiments.

[0023] The fuel pipeline is in communication between the oil storage tank and the device to be refueled. At least two stop valves are arranged at both ends of the fuel pipeline to enable the oil storage tank to be in communication with the fuel pipeline and the device to be refueled through the stop valves. The stop valves at both ends of the test section of the fuel pipeline are switched between the open state and the closed state according to the ground temperature and the underground temperature. When the stop valves at both ends of the test section of the fuel pipeline are in the open state, the test section of the fuel pipeline is in communication with the oil storage tank and the device to be refueled. When the stop valves at both ends of the test section of the fuel pipeline are in the closed state, the test section of the fuel pipeline is not in communication with the oil storage tank and the device to be refueled.

[0024] The technical solutions provided by the embodiments of the present application can include the following beneficial effects:

[0025] By measuring the ground temperature and the underground temperature, it is determined whether there is enough heat in the underground temperature for the fuel pipeline to automatically boost pressure. Only when automatic pressure boosting can be achieved, the stop valves at both ends of the test section are closed to enter the pressure testing. In this way, the accuracy of triggering pressure detection is improved.

[0026] The technical solutions are further described as follows:

[0027] In one of the embodiments, the fuel oil delivery system comprises at least three shut-off valves. The at least three shut-off valves are arranged in communication with the fuel oil pipeline. The fuel oil pipeline comprises a first fuel oil branch and a second fuel oil branch. The at least three shut-off valves comprise a first shut-off valve, a second shut-off valve and a third shut-off valve. The first shut-off valve is arranged at one end of the first fuel oil branch. The second shut-off valve is arranged between the first fuel oil branch and the second fuel oil branch. The third shut-off valve is arranged at the other end of the second fuel oil branch.

[0028] In one of the embodiments, the fuel oil delivery system further comprises a plurality of first plug devices arranged at intervals, a plurality of second plug devices arranged at intervals and a plurality of communication valves, each of which is installed to the first plug device. An installation body is detachably connected with the communication valve, so that when the installation body is connected with the communication valve, the installation body is in communication with the fuel oil pipeline through the communication valve. The second plug device is arranged in correspondence with the shut-off valve.

[0029] According to a third aspect of the embodiments of the present application, a pressure test correction method is provided, which is applied to the fuel oil delivery system in the above-mentioned embodiments. The pressure test correction method comprises:

[0030] S1, obtaining the ground temperature and the underground temperature, and calculating the temperature difference value between the underground temperature and the ground temperature.

[0031] When the temperature difference value is greater than or equal to a preset temperature difference, the shut-off valves at both ends of the test section of the fuel oil pipeline are closed, and step S2 is entered.

[0032] S2, after a first time, obtaining the pressure value of the fuel oil pipeline.

[0033] When the pressure value is greater than a preset test pressure, the pressure relief valve is opened to release pressure, so that the pressure value is within the range of the preset test pressure. When the pressure value is less than the preset test pressure, the operation is stopped, and the shut-off valves at both ends of the test section of the fuel oil pipeline remain closed. When the pressure value is within the range of the preset test pressure, the fuel oil pipeline pressure test state is entered, and the pressure relief valve is closed. Wherein, the preset temperature difference is greater than 0.

[0034] The technical solutions provided by the embodiments of the present application can include the following beneficial effects:

[0035] The temperature difference between the ground temperature and the underground temperature is measured to determine whether the difference between the underground temperature and the ground temperature can provide sufficient fuel evaporation heat for the underground temperature. When the temperature difference is large enough, it can be considered that the fuel can be evaporated by the underground temperature. Further, the shut-off valves at both ends of the fuel pipeline of the test section are closed. After a first time, the fuel in the fuel pipeline is automatically heated and evaporated by the heat of the underground temperature, and the fuel in the fuel pipeline is converted from a liquid to a saturated vapor, so that the pressure in the fuel pipeline gradually rises. When the pressure rises to a preset test pressure within the first time, it means that the pressure test can be performed. When the pressure does not rise to the preset test pressure within the first time, it means that there may be a leak in the fuel pipeline. Therefore, the shut-off valves are kept closed to avoid continuous fuel supply to the leaking fuel pipeline section and to avoid large-scale spread of the leak. When the pressure exceeds the preset test pressure within the first time, the fuel pipeline can be appropriately relieved by opening the pressure relief valve to make the pressure meet the preset test pressure range, so that the pressure test is finally corrected to ensure the accuracy of the pressure test and avoid excessive pressure increasing the pressure bearing burden of the fuel pipeline.

[0036] The technical solutions are further described below.

[0037] The correction method of the pressure test comprises:

[0038] In S110, the ground temperature and the underground temperature are obtained. The temperature difference between the underground temperature and the ground temperature is calculated. When the temperature difference is greater than or equal to a preset temperature difference, and both the temperature difference and the preset temperature difference are greater than 0, the process proceeds to S120.

[0039] In S120, the test state is determined.

[0040] When the oil delivery system is in the first test state, the first shut-off valve and the second shut-off valve are closed, and the third shut-off valve is opened, so that the first oil delivery branch is not connected to the oil tank and the oil filling device, the second oil delivery branch is connected to the oil tank or the oil filling device, and the mounting body is connected to the first oil delivery branch. The process proceeds to S2.

[0041] When the oil delivery system is in the second test state, the second shut-off valve and the third shut-off valve are closed, so that the second oil delivery branch is not connected to the oil tank and the oil filling device, the first oil delivery branch is connected to the oil tank or the oil filling device, and the mounting body is connected to the second oil delivery branch. The process proceeds to S2.

[0042] In one embodiment, the correction method of the pressure test comprises:

[0043] In S210, after a first time, the first pressure value of the fuel pipeline is obtained.

[0044] When the first pressure value is greater than the preset test pressure, the pressure relief valve is opened to release pressure, so that the first pressure value is within the range of the preset test pressure. When the first pressure value is less than the preset test pressure, step S220 is entered. When the first pressure value is within the range of the preset test pressure, the fuel oil pipeline pressure test state is entered, and the pressure relief valve is in a closed state.

[0045] S220, after a second time, the second pressure value of the fuel oil pipeline is obtained again.

[0046] When the second pressure value is greater than the preset test pressure, the pressure relief valve is opened to release pressure, so that the second pressure value is within the range of the preset test pressure. When the second pressure value is less than the preset test pressure, it is judged that the fuel oil pipeline is in a leakage state, the operation is stopped, the stop valves at both ends of the test section of the fuel oil pipeline are kept closed, and a leakage alarm signal is issued. When the second pressure value is within the range of the preset test pressure, the fuel oil pipeline pressure test state is entered, and the pressure relief valve is in a closed state.

[0047] In one of the embodiments, the preset temperature difference is between 3℃ and 8℃.

[0048] In one of the embodiments, the correction assembly further comprises a first ball valve and a second ball valve. The mounting body comprises a first pipeline, a second pipeline and a third pipeline. The fuel oil pipeline, the first pipeline and the pressure measurement assembly are sequentially communicated to form a first branch. The pressure relief valve and the first ball valve are sequentially communicated through the second pipeline to form a second branch. The pressure relief valve and the second ball valve are sequentially communicated through the third pipeline to form a third branch. The second branch and the third branch are connected in parallel to the first branch, and the second branch and the third branch are sequentially arranged from top to bottom along the direction of gravity.

[0049] The pressure test correction method comprises:

[0050] S101, when the temperature difference value is greater than or equal to the preset temperature difference, the stop valves at both ends of the test section of the fuel oil pipeline are closed, and the first ball valve and the second ball valve are closed, so that the second branch and the third branch are not communicated with the first branch, and step S201 is entered.

[0051] S201, when the pressure value is greater than the preset test pressure, the pressure relief valve and the first ball valve are opened to release pressure, so that the pressure value is within the range of the preset test pressure. When the pressure value is less than the preset test pressure, the operation is stopped. When the pressure value is within the range of the preset test pressure, the pressure relief valve, the first ball valve and the second ball valve are all in a closed state, so that the second branch and the third branch are not communicated with the first branch, so that the fuel oil pipeline is in a pressure test state, and step S202 is entered.

[0052] S202, after the third time, when the aviation fuel pipeline is in the non-pressure test state, the first branch and the test section of the aviation fuel pipeline are in the non-communication state, the pressure relief valve is closed, and the second ball valve is opened, so that at least part of the fluid in the installation body is discharged through the third branch.

[0053] It should be understood that the general description above and the following detailed description are only exemplary and explanatory, and cannot limit the present application. BRIEF DESCRIPTION OF DRAWINGS

[0054] The accompanying drawings, which are incorporated into and form part of the specification, illustrate embodiments consistent with the present application and, together with the description, serve to explain the principles of the application.

[0055] Figure 1 It is a structural schematic diagram of the oil delivery system in an embodiment.

[0056] Figure 2 It is a structural schematic diagram of the first oil delivery branch and the second oil delivery branch in an embodiment.

[0057] Figure 3 It is a structural schematic diagram of the pressure correction device in an embodiment.

[0058] Figure 4 It is Figure 3 It is a flowchart of the correction method of the pressure test performed by the pressure correction device shown.

[0059] Figure 5 It is Figure 4 It is a specific flowchart of step S1 shown in

[0060] Figure 6 It is Figure 4 It is a specific flowchart of step S2 shown in

[0061] Figure 7 It is a flowchart of the correction method of the pressure test shown in another embodiment.

[0062] Figure 8 It is a structural schematic diagram of the cooperation between the controller and other components in the oil delivery system in an embodiment.

[0063] 10, oil delivery system; 100, pressure correction device; 110, correction assembly; 110a, first branch; 110b, second branch; 110c, third branch; 111, mounting body; 1111, first pipeline; 1112, second pipeline; 1113, third pipeline; 1114, fourth pipeline; 1114a, first end; 1114b, second end; 112, pressure relief valve; 113, pressure detection assembly; 114, first ball valve; 115, second ball valve; 120, temperature detection assembly; 121, first temperature detection member; 122, second temperature detection member; 130, controller; 200, oil storage tank; 210, flow guide pipe; 300, fuel pipeline; 310, first oil delivery branch; 320, second oil delivery branch; 400, stop valve; 410, first stop valve; 420, second stop valve; 430, third stop valve; 500, first well device; 600, second well device; 700, communication valve. DETAILED DESCRIPTION

[0064] The exemplary embodiments will be described in detail herein with reference to the accompanying drawings. In the following description, unless otherwise indicated, like numbers in the attached drawings refer to the same or similar elements. The following detailed description includes specific details for the purpose of providing a thorough understanding of the exemplary embodiments. However, it will be apparent to those skilled in the art that the exemplary embodiments can be practiced without these specific details. In some instances, well-known structures and components are not described in detail in order to avoid obscuring the understanding of this description.

[0065] During the process of fuel oil transportation, the pressure of the fuel oil pipeline gradually increases due to the change of temperature or the solidification and accumulation of fuel oil in the pipeline, which gradually affects the pressure resistance performance of the fuel oil pipeline. Therefore, in order to ensure the stability of fuel oil transportation, it is necessary to regularly test the pressure of the fuel oil pipeline. The pressure test is mainly to close the communication between the oil storage tank and the fuel oil pipeline, to pressurize the fuel oil pipeline by filling liquid, and to increase the pressure to a higher level than that in the general transportation process, so as to test the performance of the fuel oil pipeline under the pressure.

[0066] However, due to the blockage inside the pipeline or the influence of temperature, the pressure of the fuel oil pipeline during the pressure test is likely to be higher than expected. If not handled, it will lead to inaccurate pressure test and increase the pressure burden of the fuel oil pipeline.

[0067] Based on this, the present application provides an oil delivery system 10, as shown in the figure, which comprises an oil storage tank 200, a fuel oil pipeline 300, a plurality of stop valves 400 and a pressure correction device 100. Figures 1 to 2 The pressure correction device 100 comprises a correction assembly 110, a pressure detection assembly 113, a temperature detection assembly 120 and a controller 130.

[0068] The aviation fuel pipeline 300 is in communication between the oil storage tank 200 and the device to be refueled. At least two stop valves 400 are arranged at both ends of the aviation fuel pipeline 300, so that the oil storage tank 200 is in communication with the aviation fuel pipeline 300 and the device to be refueled through the stop valves 400. The aviation fuel pipeline 300 is fixedly arranged on the ground.

[0069] As shown in Figure 3 The pressure correction device 100 includes a correction assembly 110 and a temperature detection assembly 120. The correction assembly 110 includes a mounting body 111, a pressure relief valve 112, and a pressure measurement assembly. The mounting body 111 is detachably connected with the aviation fuel pipeline 300, so that when the mounting body 111 is connected with the aviation fuel pipeline 300, the mounting body 111 is in communication with the aviation fuel pipeline 300. The pressure relief valve 112 is in communication with the mounting body 111, so that the mounting body 111 and the aviation fuel pipeline 300 are relieved through the pressure relief valve 112. The pressure measurement assembly is in communication with the mounting body 111, and the pressure measurement assembly is used to detect the pressure value in the mounting body 111. The temperature detection assembly 120 includes a first temperature detection member 121 and a second temperature detection member 122. The first temperature detection member 121 is used to obtain the ground temperature. The second temperature detection member 122 is used to obtain the underground temperature. It should be noted that the first temperature detection member 121 and the second temperature detection member 122 can be different temperature detection members, or can be the same temperature detection member used in different scenes.

[0070] The pressure correction device is matched with the aviation fuel pipeline to perform the pressure test correction method, and the pressure test correction method includes the following steps:

[0071] As shown in Figure 4 The pressure test correction method includes:

[0072] S1, obtaining the ground temperature and the underground temperature. Calculate the temperature difference value between the underground temperature and the ground temperature.

[0073] When the temperature difference value is greater than or equal to the preset temperature difference, the stop valves at both ends of the aviation fuel pipeline are closed, and step S2 is entered. Otherwise, step S1 is repeatedly executed.

[0074] Specifically, the second temperature detecting member can be fixed to the soil layer or the concrete layer for measurement. It can be understood that, generally, in order to test the actual pressure performance of the aviation oil pipeline, the test pressure of the aviation oil pipeline is greater than the pressure in the actual use process, so as to measure the working stability of the aviation oil pipeline in a relatively extreme state. In some scenarios such as winter, due to the difference in heat dissipation rate between the ground and the underground, the temperature of the ground can be lower than that of the underground, and the higher underground temperature can enable the aviation oil to realize automatic evaporation by using the higher underground temperature, so as to improve the pressure of the aviation oil pipeline, and finally reach the test pressure. Based on this, by measuring the temperature difference between the ground temperature and the underground temperature, it is determined whether the temperature difference between the underground temperature and the ground temperature can provide sufficient aviation oil evaporation heat for the underground temperature. When the temperature difference is large enough, it can be considered that the aviation oil can evaporate by using the underground temperature. Further, after the first time, the aviation oil in the aviation oil pipeline can be automatically heated and evaporated by the heat of the underground temperature, and the aviation oil pipeline can be converted from liquid to saturated vapor, so that the pressure in the aviation oil pipeline gradually rises.

[0075] S2, after the first time, obtaining the pressure value of the aviation oil pipeline.

[0076] When the pressure value is within the preset test pressure range, the aviation oil pipeline pressure test state is entered, and the relief valve is in a closed state. When the pressure value is greater than the preset test pressure, the relief valve is opened to release pressure, so that the pressure value is within the preset test pressure range. It can be understood that when the preset test pressure is reached within the first time, it means that the pressure test can be performed. When the preset test pressure is not reached within the first time, the aviation oil pipeline may have a leak, and the closed stop valve is maintained to avoid continuous oil supply to the leaking aviation oil pipeline section and prevent the spread of the leak.

[0077] When the pressure value is less than the preset test pressure, the operation is stopped, and at least part of the stop valve on both sides of the aviation oil pipeline is kept in a closed state. Wherein, the preset temperature difference is greater than 0. When the preset test pressure is exceeded within the first time, the aviation oil pipeline can be appropriately relieved by opening the relief valve, so as to meet the preset test pressure range, and finally correct the pressure test to ensure the accuracy of the pressure test, and avoid the increase of the pressure of the aviation oil pipeline.

[0078] The following will be described in detail with an embodiment:

[0079] Suppose the current pressure in the fuel pipeline under normal use condition is 0.8 MPa, and the preset test pressure is 0.88 MPa. (Generally, the preset test pressure is 1.1-1.5 times of the pressure in the fuel pipeline under normal use condition when pressure test is performed). If the temperature difference between the underground temperature and the ground temperature is 6℃ at this time, the temperature difference of 6℃ is greater than the preset temperature difference (such as 5℃), which meets the evaporation condition of the evaporation of the fuel pipeline, and the fuel pipeline at both ends of the test section is closed. At this time, step S2 can be entered, and after a first time (such as 5 min), the pressure of the fuel pipeline is measured. Suppose the pressure in the test fuel pipeline rises from 0.8 MPa to 0.95 MPa, and the pressure relief valve is opened to reduce the pressure to 0.88 MPa. At the same time, the pressure change is monitored at any time, so that the pressure in the fuel pipeline always maintains the preset test pressure, improving the stability and accuracy of the pressure test.

[0080] It should be noted that the fuel pipeline of the test section can refer to the entire fuel pipeline or a small section of the fuel pipeline, etc., which is not limited here.

[0081] In combination with any embodiment of the above fuel pipeline 300 delivery system, the fuel pipeline 300 delivery system includes at least three stop valves 400; the at least three stop valves 400 are communicatively arranged in the fuel pipeline 300. The fuel pipeline 300 includes a first oil delivery branch 310 and a second oil delivery branch 320. The at least three stop valves 400 include a first stop valve 410, a second stop valve 420, and a third stop valve 430. The first stop valve 410 is arranged at one end of the first oil delivery branch 310. The second stop valve 420 is arranged between the first oil delivery branch 310 and the second oil delivery branch 320. The third stop valve 430 is arranged at the other end of the second oil delivery branch 320.

[0082] It can be understood that generally, the fuel pipeline 300 under the apron is only provided with corresponding stop valves 400 at both ends, so that the oil tank 200, the stop valve 400, the fuel pipeline 300, the stop valve 400, and the device to be refueled are sequentially communicated to form an oil product transportation loop. For pressure detection of such an oil product transportation loop, the entire oil product transportation loop needs to be closed, the oil tank 200 and the device to be refueled are not allowed, and the pressure of the entire oil product transportation loop is increased by external hydraulic pressure to increase the test pressure, and then pressure test is performed. The traditional test method needs to close the entire oil product transportation loop, which reduces the refueling efficiency between the oil tank 200 and the device to be refueled, and for the current 24-hour airport, closing the entire oil product transportation loop will cause the interruption of aircraft refueling at the airport, which brings great inconvenience.

[0083] And through the setting of the stop valve 400, the aviation oil pipeline 300 is divided into several test branches, so that a segmented detection process can be realized, and only a single small section of the aviation oil branch is subjected to pressure testing, and after the risk is eliminated, another section of the aviation oil branch is subjected to pressure correction and pressure testing, so that the entire oil transportation system does not need to be closed, the transportation efficiency is ensured, and the establishment of a 24-hour airport is facilitated.

[0084] As shown in Figure 5 , specifically, the oil delivery system includes a first test state and a second test state. Step S1 includes:

[0085] S110, the ground temperature and the underground temperature are obtained. The temperature difference value between the underground temperature and the ground temperature is calculated. When the temperature difference value is greater than or equal to the preset temperature difference, and both the temperature difference value and the preset temperature difference are greater than 0, then step S120 is entered.

[0086] S120, determine the test state.

[0087] When the oil delivery system is in the first test state, the first stop valve and the second stop valve are closed, and the third stop valve is opened, so that the first oil delivery branch is not in communication with the oil tank and the device to be refueled, the second oil delivery branch is in communication with the oil tank or the device to be refueled, and the mounting body is in communication with the first oil delivery branch. Enter step S2. That is, when the oil delivery system is in the first test state, the first oil delivery branch is subjected to pressure correction and pressure testing at this time, and the second oil delivery branch continues to maintain the transportation state, so that the transportation aviation oil in the oil tank or the aviation oil to the device to be refueled can continue to be received through the second oil delivery branch.

[0088] When the oil delivery system is in the second test state, the second stop valve and the third stop valve are closed, so that the second oil delivery branch is not in communication with the oil tank and the device to be refueled, the first oil delivery branch is in communication with the oil tank or the device to be refueled, and the mounting body is in communication with the second oil delivery branch. Enter step S2. Similarly, when the oil delivery system is in the second test state, the second oil delivery branch is subjected to pressure correction and pressure testing at this time, and the first oil delivery branch continues to maintain the transportation state, so that the transportation aviation oil in the oil tank or the aviation oil to the device to be refueled can continue to be received through the first oil delivery branch.

[0089] It should be noted that the first oil delivery branch and the second oil delivery branch can be connected in parallel between the oil tank and the device to be refueled, or can be connected in series between the oil tank and the device to be refueled, or a combination thereof. In addition, the aviation oil pipeline can include a plurality of first oil delivery branches and a plurality of second oil delivery branches, which are not limited here.

[0090] Among them, for the communication opening and closing control between the plurality of stop valves 400 and the mounting body 111 and the aviation oil pipeline 300 in the above embodiment, in some embodiments,Figure 1 The oil delivery system 10 further comprises a plurality of first manhole devices 500, a plurality of second manhole devices 600, and a plurality of communication valves 700, wherein the communication valves 700 are installed to the first manhole devices 500 one by one. The mounting body 111 is detachably connected to the communication valve 700, so that when the mounting body 111 is connected and matched with the communication valve 700, the mounting body 111 is communicated with the aviation oil pipeline 300 through the communication valve 700. The second manhole devices 600 are arranged in one-to-one correspondence with the stop valves 400. Specifically, the first manhole devices 500 and the second manhole devices 600 can each include a well cylinder and a well cover matched with the well cylinder. The upper surface of the well cover is flush with the ground.

[0091] It can be understood that under normal use conditions, the well cover is arranged on the well cylinder in a closed manner, and at this time the mounting body 111 is not connected and matched with the aviation oil pipeline 300. When pressure correction and pressure testing of the aviation oil pipeline 300 of the test section are needed, the well cover at the corresponding position can be opened, the stop valve 400 is closed and the communication valve 700 is opened, and the valve port of the aviation oil pipeline 300 in the accommodating cavity of the manhole device is opened, so that the mounting body 111 is inserted into the valve port of the aviation oil pipeline 300, so that the mounting body 111 is communicated with the aviation oil pipeline 300. Further, the one-to-one correspondence of the stop valve 400 and the manhole device makes it possible to arbitrarily select any stop valve 400 to be closed through the manhole device, so as to realize the aviation oil pipeline 300 of different test sections or different lengths of test sections, thereby enriching the test scene of pressure testing.

[0092] It should be noted that the first time can be a fixed value or a variable value, which can be selected according to different design requirements.

[0093] In a specific embodiment, the first time is a fixed value, such as 5 min, 8 min or 10 min, etc.

[0094] In another specific embodiment, the first time is related to the temperature difference value and the preset test pressure. According to the ideal gas state equation PV=nRT, the length of time and the change of temperature will cause the size of pressure change. Based on this, a model can be established according to the size of the preset test pressure and the temperature difference value to control the size of the change of the pressure in the aviation oil pipeline. For example, a larger preset test pressure is needed, and at this time the temperature difference is smaller, so the first time needs to be longer, such as 15 min, to reach the preset test pressure. When a smaller preset test pressure is needed, the temperature difference is larger, and the first time can be very short, such as 3 min, to achieve the preset test pressure. After the preset test pressure is reached through the pressure relief valve, the pressure test can be carried out.

[0095] Further, in an embodiment, as shown in FIG. 6, the first time is related to the temperature difference value and the preset test pressure. Figure 6As shown, the correction method of the pressure test further comprises:

[0096] S210, after the first time, acquiring the first pressure value of the aviation fuel pipeline.

[0097] When the first pressure value is greater than the preset test pressure, the pressure relief valve is opened to release pressure, so that the first pressure value is within the range of the preset test pressure.

[0098] When the first pressure value is less than the preset test pressure, step S220 is entered.

[0099] When the first pressure value is within the range of the preset test pressure, the aviation fuel pipeline pressure test state is entered, and the pressure relief valve is in a closed state.

[0100] S220, after the second time, acquiring the second pressure value of the aviation fuel pipeline. It can be understood that if the pressure value is still less than the preset test pressure after the first time, the second time can be continued to wait for the aviation fuel pipeline to continue to evaporate and warm up.

[0101] When the second pressure value is within the range of the preset test pressure, the aviation fuel pipeline pressure test state is entered, and the pressure relief valve is in a closed state.

[0102] When the second pressure value is greater than the preset test pressure, the pressure relief valve is opened to release pressure, so that the second pressure value is within the range of the preset test pressure. When the pressure value at this time is greater than the preset test pressure, the pressure relief valve is released to make the pressure value within the range of the preset test pressure.

[0103] When the second pressure value is less than the preset test pressure, it is judged that the aviation fuel pipeline is in a leakage state, the operation is stopped, the stop valve at both ends of the test section of the aviation fuel pipeline is kept in a closed state, and a leakage alarm signal is issued. When the pressure value at this time is still less than the preset test pressure, it can be judged that the aviation fuel pipeline leaks, a leakage alarm signal is issued to remind the maintenance personnel to carry out maintenance treatment, and the stability of the aviation fuel pipeline transportation is ensured.

[0104] It should be noted that the type of leakage alarm signal can be, but is not limited to, light, sound, electricity or combination.

[0105] Further, in an example, the controller communicates with the pressure detection component to execute the correction method of the pressure test in any of the above embodiments, so that the controller can issue a leakage alarm signal.

[0106] To improve the working stability of the aviation oil pipeline transportation system, in combination with any of the above embodiments of the pressure correction device, the pressure correction device further comprises a recovery bucket. The recovery bucket is configured to communicate with the pressure relief valve. In this way, the setting of the recovery bucket can accommodate the waste oil liquid discharged during pressure relief, so as to avoid pollution to the soil or the mixed layer around the pipeline.

[0107] In some embodiments, the recovery bucket is configured to communicate with the pressure relief valve. Figure 3 The correction assembly 110 further comprises a first ball valve 114 and a second ball valve 115. The mounting body 111 comprises a first pipeline 1111, a second pipeline 1112, and a third pipeline 1113. The aviation oil pipeline 300, the first pipeline 1111, and the pressure measurement assembly are sequentially communicated to form a first branch 110a. The pressure relief valve 112, the first ball valve 114, and the recovery bucket are sequentially communicated through the second pipeline 1112 to form a second branch 110b. The pressure relief valve 112, the second ball valve 115, and the recovery bucket are sequentially communicated through the third pipeline 1113 to form a third branch 110c. The second branch 110b and the third branch 110c are connected in parallel to the first branch 110a, and the second branch 110b and the third branch 110c are sequentially arranged from top to bottom along the direction of gravity.

[0108] As shown in the pressure test correction method, the method further comprises: Figure 7

[0109] S101, when the temperature difference value is greater than or equal to the preset temperature difference, the stop valves at both ends of the test section of the aviation oil pipeline are closed, and the first ball valve and the second ball valve are closed, so that the second branch and the third branch are not communicated with the first branch, and step S2 is entered. It can be understood that when the aviation oil pipeline needs to be pressure tested, when the temperature difference value is greater than or equal to the preset temperature difference, the stop valves at both ends of the corresponding test section are closed to automatically heat by using the underground temperature heat to increase the pipeline pressure of the test section to reach the preset test pressure. At this time, the first ball valve and the second ball valve need to be closed to connect the test section of the aviation oil pipeline and the first branch to jointly increase the pressure to avoid the overall low level of the pipeline pressure of the test section caused by early pressure relief.

[0110] S201, when the pressure value is greater than the preset test pressure, the pressure relief valve and the first ball valve are opened for pressure relief, so that the pressure value is within the range of the preset test pressure. When the pressure value is less than the preset test pressure, the operation is stopped. When the pressure value is within the range of the preset test pressure, the pressure relief valve, the first ball valve, and the second ball valve are all in the closed state, so that the second branch and the third branch are not communicated with the first branch, so that the aviation oil pipeline is in the pressure test state, and step S202 is entered.

[0111] ​When the pressure value is greater than the preset test pressure after the first time, the pressure needs to be released. Since the heat of the underground temperature is still continuously provided to the aviation oil pipeline during the current process, there is a large amount of gas-liquid phase mixed oil in the aviation oil pipeline. At this time, the first ball valve and the pressure relief valve can be opened, so that the gas-liquid phase mixed oil moves to the pressure relief valve at a faster speed due to the difference in gas pressure. A large amount of gas phase mixed oil is discharged out of the oil delivery system through the pressure relief valve, and the remaining liquid phase mixed oil can be stored to the switch valve along the pipeline by the opening of the first ball valve under the action of gravity. At this time, the opening of the first ball valve can play a good gas-liquid separation effect, and the opening of the pressure relief valve can play a good pressure balance effect. Unlike opening the second ball valve, opening the first ball valve can be closer to the pressure relief valve, can provide a larger length of climbing space, so that the aviation oil is fully gas-liquid separated, and the liquid phase mixed oil discharged through the first ball valve can also achieve a certain pressure balance.

[0112] S202, after the third time, when the aviation oil pipeline is in a non-pressure test state, the first branch and the test section of the aviation oil pipeline are in a non-communicating state, the pressure relief valve is closed, and the second ball valve is opened, so that at least part of the fluid in the installation body is discharged into the recovery bucket through the third branch.

[0113] When the pressure value is in the preset test pressure, the pressure test state can be entered, so that the pressure relief valve, the first ball valve, the second ball valve and the switch valve are all in the closed state, so that the pressure of the installation body and the test section of the aviation oil pipeline remains stable to perform pressure test. After the third time, the pressure test of the test section of the aviation oil pipeline is completed, and the non-pressure test stage is entered, so that the first branch and the test section of the aviation oil pipeline are not communicated, that is, the installation body and the aviation oil pipeline are not communicated (which can be achieved by splitting the installation body and the test section of the aviation oil pipeline, or by providing a switch valve in the first branch to close the communication between the first branch, the second branch, the third branch and the test section of the aviation oil pipeline, etc.), and then the second ball valve and the switch valve communicating with the recovery bucket are opened, so that the fluid in the installation body is discharged into the recovery bucket through the second branch. At this time, the opening of the second ball valve can play a good switch-out effect. The fluid in the first branch has been released to the position of the second branch by gravity during the pressure test, so that the first ball valve can be in the open state or the closed state, and both do not affect the discharge of the fluid in the installation body.

[0114] Further, in a specific embodiment, the recovery bucket is provided with a second switch valve, and the second switch valve is connected with the second branch. Figure 3The mounting body 111 further comprises a fourth pipeline 1114. The fourth pipeline 1114 is in communication with the first branch 110a. The fourth pipeline 1114 is provided with a first end 1114a and a second end 1114b in a top-to-bottom direction along the gravity direction. The second branch 110b is in communication between the first end 1114a and the switch valve. The third branch 110c is in communication between the second end 1114b and the switch valve. The pressure relief valve 112 is arranged at the top end of the fourth pipeline 1114. One end of the first branch 110a is in plug-in cooperation with the well device, so that the one end of the first branch 110a is in communication with the test section of the aviation oil pipeline 300.

[0115] In another specific embodiment, the first branch is provided with a third end and a fourth end in a top-to-bottom direction along the gravity direction. The second branch is in communication between the third end and the switch valve. The third branch is in communication between the second end and the switch valve, so that the second branch and the third branch are in parallel communication with the first branch. The pressure relief valve can be arranged at the top side of the first pipeline. One end of the first branch is in plug-in cooperation with the well device, so that the one end of the first branch is in communication with the test section of the aviation oil pipeline.

[0116] It should be noted that the stop valve in the above embodiments can be but is not limited to a switch valve, and can also be a three-way valve to realize the communication of the aviation oil pipeline and the switching between the communication of the aviation oil pipeline and the mounting body.

[0117] In some embodiments, the preset temperature difference is between 3°C and 8°C. In this way, the preset temperature difference is sufficient to provide evaporation heat for the aviation oil while avoiding excessive limitation on triggering the detection condition.

[0118] In an example, the preset temperature difference is between 4°C and 7°C. In this way, the preset temperature difference can provide more evaporation heat for the aviation oil while also reducing the threshold for triggering pressure correction and pressure testing.

[0119] In another example, the preset temperature difference can be but is not limited to 4°C, 5°C, 6°C, or 7°C, etc., which is not limited here. In this way, the preset temperature difference can realize the increase of aviation oil evaporation pressure while also reducing the threshold for triggering pressure correction and pressure testing.

[0120] In combination with any of the above embodiments of the test and correction device of the aviation oil pipeline 300, as shown in Figure 8 The pressure correction device 100 further comprises a controller 130. The controller 130 is in communication connection with the pressure measurement assembly, the temperature detection assembly 120, and the stop valve 400, so that the controller 130 is used to correct the pressure test according to the pressure value and the temperature value. In this way, it is beneficial to improve the intelligent detection degree and reduce manual operation. Specifically, the controller 130 comprises a memory and a computer program. The computer program can be used to execute the correction method of the pressure test in any of the above embodiments.

[0121] The memory is configured to store a plurality of first preset temperatures and a plurality of second preset temperatures. It should be noted that the memory in the above embodiments can include at least one type of storage medium, including a flash memory, a hard disk, a multimedia card, a card-type memory (e.g., an SD or DX memory, etc.), a random access memory (RAM), a static random access memory (SRAM), a read-only memory (ROM), an electrically erasable programmable read-only memory (EEPROM), a programmable read-only memory (PROM), a magnetic memory, a magnetic disk, an optical disk, etc.

[0122] The computer program can be implemented using, for example, a computer readable medium such as computer software, hardware, or any combination thereof. For hardware implementation, the embodiments described herein can be implemented by using at least one of application specific integrated circuits (ASICs), digital signal processors (DSPs), digital signal processing devices (DSPDs), programmable logic devices (PLDs), field programmable gate arrays (FPGAs), processors, controllers 130 170, microcontrollers 130 170, microprocessors, electronic units designed to perform the functions described herein, or a combination thereof. For software implementation, the embodiments such as processes or functions can be implemented by separate software modules that allow at least one function or operation to be performed. The software code can be implemented by a software application (or program) written in any appropriate programming language, which can be stored in a memory and executed by a computer program.

[0123] It should be noted that the pressure detection assembly 113 can be an electronic pressure gauge, a communicating device detection member, etc., which will be described in detail later.

[0124] In an embodiment, the pressure measurement assembly is an electronic pressure gauge. In this way, the setting is simple, and the measurement is accurate. In an example, the electronic pressure gauge can be in communication connection with the controller 130, so that the controller 130 receives the pressure value.

[0125] In another embodiment, the pressure measurement assembly includes a communicating device assembly. One end of the communicating device assembly is in communication with the atmospheric pressure, and the other end is in communication with the mounting body 111.

[0126] In an example, a scale rack is provided on the communicating device assembly. The pressure value is obtained by reading the scale rack. In this way, the circuit is reduced, which is beneficial to improve the working stability of the aviation fuel pipeline 300.

[0127] In another example, the pressure measuring assembly further comprises an optical sensor in communication with the controller 130, the optical sensor is arranged on the communicating assembly to measure the change of liquid level height at one end of the communicating assembly, and the pressure of the current installation body 111 and the test section of the fuel pipeline 300 is calculated by obtaining the change of liquid level height.

[0128] In combination with any of the above embodiments of the fuel delivery system 10, it is found that Figures 1 to 2 The fuel delivery system 10 further comprises a flow guide pipe 210. The flow guide pipe 210 is arranged in the fuel tank 200 to guide the fuel in the fuel tank 200 to the fuel pipeline 300 through the flow guide pipe 210. One end of the flow guide pipe 210 is in communication with the fuel pipeline 300, and the other end is arranged close to the liquid surface of the fuel in the fuel tank 200, so that the flow guide pipe 210 can receive the upper layer of fuel. It can be understood that, since the density of the fuel is greater than that of water, when the fuel stored in the fuel tank 200 contains water, the liquid surface in the fuel tank 200 will be stratified, and the high-purity fuel will be distributed in the upper layer. The flow guide pipe 210 is arranged close to the liquid surface of the fuel, so that the flow guide pipe 210 can always transport the upper layer of high-purity fuel, improving the quality of fuel delivery.

[0129] The above only describes the preferred embodiments of the present application and is not intended to limit the present application. Any modification, equivalent replacement, improvement, etc. made within the spirit and principles of the present application shall be included in the scope of protection of the present application. Any slight modification or modification of the above-mentioned technical content to make equivalent embodiments, but as long as it does not deviate from the technical solution of the present application, any simple modification, equivalent change and modification of the above-mentioned embodiments according to the technical essence of the present application shall still be within the scope of the technical solution of the present application.

Claims

1. A pressure correction device for cooperation with a fuel oil pipeline, characterized in that, The pressure correction device comprises: a correction assembly; the correction assembly comprises a mounting body, a pressure relief valve and a pressure measurement assembly; the mounting body is detachably connected with the fuel pipeline, so that the mounting body is in communication with the fuel pipeline when the mounting body is connected with the fuel pipeline; the pressure relief valve is in communication with the mounting body, so that the mounting body and the fuel pipeline are relieved through the pressure relief valve; the pressure measurement assembly is in communication with the mounting body, and the pressure measurement assembly is used to detect the pressure value of the mounting body; a temperature detection assembly; the temperature detection assembly comprises a first temperature detection member and a second temperature detection member; the first temperature detection member is used to obtain the ground temperature; and the second temperature detection member is used to obtain the underground temperature; when the temperature difference between the underground temperature and the ground temperature is greater than or equal to a preset temperature difference, the fuel pipeline is in a pressure test state, and the stop valves at both ends of the fuel pipeline test section are in a closed state; otherwise, the fuel pipeline is in a non-pressure test state, and the stop valves at both ends of the fuel pipeline test section are in an open state; wherein when the pressure relief valve is in an open state, the mounting body and the fuel pipeline are relieved through the pressure relief valve; when the pressure relief valve is in a closed state, the mounting body and the fuel pipeline are not in communication with the pressure relief valve for relief; through switching of the pressure relief valve between the open state and the closed state, when the fuel pipeline is in the pressure test state, the pressure value is kept within a preset test pressure range; the correction assembly further comprises a first ball valve and a second ball valve; the mounting body comprises a first pipeline, a second pipeline and a third pipeline; the fuel pipeline, the first pipeline and the pressure measurement assembly are in sequence communication to form a first branch; the pressure relief valve and the first ball valve are in sequence communication through the second pipeline to form a second branch; the pressure relief valve and the second ball valve are in sequence communication through the third pipeline to form a third branch; the second branch and the third branch are in parallel communication with the first branch, and the second branch and the third branch are arranged in sequence from top to bottom along the direction of gravity.

2. The pressure correction device according to claim 1, wherein when the fuel pipeline is in the pressure test state and the pressure relief valve is in the closed state, the first ball valve and the second ball valve are both in the closed state, so that at least part of the second branch and the third branch are not in communication with the first branch; when the fuel pipeline is in the pressure test state and the pressure relief valve is in the open state, the first ball valve is in the open state and the second ball valve is in the closed state, so that the second branch is in communication with the first branch, and at least part of the third branch is not in communication with the first branch; when the fuel pipeline is in the non-pressure test state, the pressure relief valve is in the closed state, and the second ball valve is in the open state, so that the first branch is in communication with the third branch, so that the fluid in the mounting body is discharged through the third branch.

3. The pressure correction device of claim 2, wherein, The pressure correction device further comprises a recovery barrel; the recovery barrel is in communication with one end of the second branch away from the pressure relief valve and one end of the third branch away from the pressure relief valve, so as to receive the fluid discharged from the second branch and the third branch.

4. The pressure correction device of claim 1, wherein The pressure measuring assembly is an electronic pressure gauge.

5. The pressure correction device of claim 1, wherein The pressure measuring assembly comprises a communicating vessel assembly; one end of the communicating vessel assembly is in communication with the atmospheric pressure, and the other end is in communication with the mounting body; a scale rack is arranged on the communicating vessel assembly; the pressure value is obtained through the reading on the scale rack.

6. The pressure correction device of claim 1, wherein The pressure correction device further comprises a controller; the controller is in communication connection with the pressure measuring assembly, the temperature detecting assembly and the pressure relief valve, so that the controller judges the switching between the pressure test state and the non-pressure test state of the fuel pipeline, and controls the switching between the open state and the closed state of the pressure relief valve.

7. An oil delivery system characterized by, It comprises: an oil storage tank, a fuel pipeline, a plurality of stop valves and the pressure correction device according to any one of claims 1 to 6; the fuel pipeline is in communication between the oil storage tank and a device to be refueled; at least two stop valves are arranged at both ends of the fuel pipeline, so that the oil storage tank is in communication with the fuel pipeline and the device to be refueled through the stop valves; the stop valves at both ends of the test section of the fuel pipeline are switched between the open state and the closed state according to the ground temperature and the underground temperature; when the stop valves at both ends of the test section of the fuel pipeline are in the open state, the test section of the fuel pipeline is in communication with the oil storage tank and the device to be refueled; when the stop valves at both ends of the test section of the fuel pipeline are in the closed state, the test section of the fuel pipeline is not in communication with the oil storage tank and the device to be refueled.

8. The oil delivery system of claim 7, wherein, The oil delivery system comprises at least three stop valves; the at least three stop valves are in communication with the fuel pipeline; the fuel pipeline comprises a first oil delivery branch and a second oil delivery branch; the at least three stop valves comprise a first stop valve, a second stop valve and a third stop valve; the first stop valve is arranged at one end of the first oil delivery branch; the second stop valve is arranged between the first oil delivery branch and the second oil delivery branch; the third stop valve is arranged at the other end of the second oil delivery branch.

9. The oil delivery system of claim 8, wherein, The oil delivery system further comprises a plurality of first stake well devices arranged at intervals, a plurality of second stake well devices arranged at intervals and a plurality of communication valves; the communication valves are installed one by one to the first stake well devices; a mounting body is detachably connected to the communication valves, so that when the mounting body is connected to the communication valves, the mounting body is in communication with the fuel pipeline through the communication valves; the second stake well devices are arranged one by one corresponding to the stop valves.

10. A method of calibrating a pressure test, characterized by, The pressure test correction method is applied to the oil delivery system according to any one of claims 7 to 9, and comprises: S1, obtaining the ground temperature and the underground temperature; calculating the temperature difference value between the underground temperature and the ground temperature; when the temperature difference value is greater than or equal to a preset temperature difference, the stop valves at both ends of the test section of the fuel pipeline are closed, and step S2 is entered; S2, after a first time, acquiring the pressure value of the fuel pipeline; When the pressure value is greater than the preset test pressure, the pressure relief valve is opened to release pressure, so that the pressure value is within the range of the preset test pressure; when the pressure value is less than the preset test pressure, the operation is stopped, and the stop valve at both ends of the test section of the fuel pipeline is kept in a closed state; when the pressure value is within the range of the preset test pressure, the fuel pipeline pressure test state is entered, and the pressure relief valve is in a closed state; wherein the preset temperature difference is greater than 0.

11. The method of calibration of pressure testing of claim 10, wherein, The oil delivery system comprises at least three stop valves; at least three stop valves are connected and arranged in the fuel pipeline; the fuel pipeline comprises a first oil delivery branch and a second oil delivery branch; at least three stop valves include a first stop valve, a second stop valve and a third stop valve; the first stop valve is arranged at one end of the first oil delivery branch; the second stop valve is arranged between the first oil delivery branch and the second oil delivery branch; The third stop valve is arranged at the other end of the second oil delivery branch; The correction method of the pressure test comprises: The oil delivery system comprises a first test state and a second test state; S110, acquiring the ground temperature and the underground temperature; calculating the temperature difference value between the underground temperature and the ground temperature; when the temperature difference value is greater than or equal to the preset temperature difference, and the temperature difference value and the preset temperature difference are both greater than 0, step S120 is entered; S120, determine the test state; When the oil delivery system is in the first test state, the first stop valve and the second stop valve are closed, and the third stop valve is opened, so that the first oil delivery branch is not connected with the oil tank and the device to be filled, the second oil delivery branch is connected with the oil tank or the device to be filled, and the mounting body is connected with the first oil delivery branch, step S2 is entered; When the oil delivery system is in the second test state, the second stop valve and the third stop valve are closed, so that the second oil delivery branch is not connected with the oil tank and the device to be filled, the first oil delivery branch is connected with the oil tank or the device to be filled, and the mounting body is connected with the second oil delivery branch, step S2 is entered.

12. The method of calibrating a pressure test of claim 10, wherein, The correction method of the pressure test comprises: S210, after a first time, acquiring the first pressure value of the fuel pipeline; When the first pressure value is greater than the preset test pressure, the pressure relief valve is opened to release pressure, so that the first pressure value is within the range of the preset test pressure; when the first pressure value is less than the preset test pressure, step S220 is entered; when the first pressure value is within the range of the preset test pressure, the fuel pipeline pressure test state is entered, and the pressure relief valve is in a closed state; S220, after a second time, acquiring the second pressure value of the fuel pipeline; When the second pressure value is greater than the preset test pressure, the pressure relief valve is opened to release pressure, so that the second pressure value is within the range of the preset test pressure; when the second pressure value is less than the preset test pressure, it is judged that the aviation oil pipeline is in a leakage state, the operation is stopped, the stop valves at both ends of the test section of the aviation oil pipeline are kept in a closed state, and a leakage alarm signal is sent; when the second pressure value is within the range of the preset test pressure, the aviation oil pipeline pressure test state is entered, and the pressure relief valve is in a closed state.

13. The method of calibrating a pressure test of claim 10, wherein, The preset temperature difference is between 3°C and 8°C.

14. The method of calibration of a pressure test according to any one of claims 10 to 13, characterized in that, The correction assembly further comprises a first ball valve and a second ball valve; the mounting body comprises a first pipeline, a second pipeline and a third pipeline; the aviation oil pipeline, the first pipeline and the pressure measuring assembly are sequentially communicated to form a first branch; the pressure relief valve and the first ball valve are sequentially communicated through the second pipeline to form a second branch; the pressure relief valve and the second ball valve are sequentially communicated through the third pipeline to form a third branch; the second branch and the third branch are connected in parallel to the first branch, and the second branch and the third branch are sequentially arranged from top to bottom along the direction of gravity; The pressure test correction method comprises: S101, when the temperature difference value is greater than or equal to the preset temperature difference, the stop valves at both ends of the test section of the aviation oil pipeline are closed, and the first ball valve and the second ball valve are closed, so that at least part of the second branch and the third branch are not communicated with the first branch, and step S201 is entered; S201, when the pressure value is greater than the preset test pressure, the pressure relief valve and the first ball valve are opened to release pressure, so that the pressure value is within the range of the preset test pressure; When the pressure value is less than the preset test pressure, the operation is stopped; when the pressure value is within the range of the preset test pressure, the pressure relief valve, the first ball valve and the second ball valve are all in a closed state, so that the second branch and the third branch are not communicated with the first branch, so that the aviation oil pipeline is in a pressure test state, and step S202 is entered; S202, after a third time, when the aviation oil pipeline is in a non-pressure test state, the first branch and the test section of the aviation oil pipeline are in a non-communication state, the pressure relief valve is closed, and the second ball valve is opened, so that at least part of the fluid in the mounting body is discharged through the third branch.

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