Detection method and detection system for aviation fuel pump

Abstract

The invention provides a detection method and a detection system for an aviation fuel pump, and relates to the technical field of aviation fuel pumps. The detection method for the aviation fuel pump comprises the steps that the pump outlet pressure of the aviation fuel pump is controlled to change; acquiring a first flow at a safety valve of the aviation fuel pump and a second flow at a pump outlet of the aviation fuel pump; and the state of the safety valve is judged according to the first flow or the second flow. According to the detection method and system for the aviation fuel pump, the state of the safety valve can be accurately judged.

Description

Technical Field

[0001] The present application relates to the technical field of aviation fuel pumps, and in particular to a detection method and a detection system for aviation fuel pumps. Background Art

[0002] The aviation fuel pump is the main component of the aircraft fuel system, which is used to provide the engine with fuel at the required flow rate and pressure. The burst point test of the safety valve in the aviation fuel pump can ensure that when the system pressure exceeds the set value, the safety valve can be opened in time to release the pressure, preventing the fuel pump and the entire fuel system from exploding or being damaged due to excessive pressure, thereby ensuring the safety of the aircraft.

[0003] At present, in the process of testing the explosion, high bypass, recovery and other states of the safety valve in the aviation fuel pump, the pressure of the fuel pump is generally adjusted manually, and the state of the safety valve is manually observed and judged according to the data displayed in the program. However, the judgment of the state of the safety valve is relatively vague and it is impossible to judge the state of the safety valve more accurately. Summary of the invention

[0004] The purpose of the present application includes, for example, providing a detection method and a detection system for an aviation fuel pump, which can more accurately determine the state of a safety valve.

[0005] The embodiments of the present application can be implemented as follows:

[0006] In a first aspect, an embodiment of the present application provides a detection method for an aviation fuel pump, which comprises:

[0007] Controlling the change in pump outlet pressure of the aviation fuel pump;

[0008] obtaining a first flow rate at the safety valve and a second flow rate at a pump outlet of the aviation fuel pump;

[0009] The state of the safety valve is determined according to the first flow rate or the second flow rate.

[0010] Optionally, in the process of detecting the explosion state of the safety valve, the aviation fuel pump detection method includes:

[0011] Controlling the pump outlet pressure of the aviation fuel pump to gradually increase;

[0012] Obtaining the first flow rate;

[0013] When the difference between the preset standard flow rate and the first flow rate is a first preset difference value, it is determined that the safety valve has reached an explosion state;

[0014] Wherein, the first flow rate is less than the preset standard flow rate.

[0015] Optionally, the first preset difference is 3.8L / min-5.7L / min.

[0016] Optionally, in the process of detecting that the safety valve is in a fully open state, the aviation fuel pump detection method includes:

[0017] Controlling the pump outlet pressure of the aviation fuel pump to gradually increase;

[0018] obtaining the second flow rate;

[0019] When the second flow rate decreases rapidly, it is determined that the safety valve is in a fully open state.

[0020] Optionally, in the process of detecting the high bypass state of the safety valve, the aviation fuel pump detection method includes:

[0021] Controlling the pump outlet pressure of the aviation fuel pump to increase to a maximum preset pressure value;

[0022] obtaining the first flow rate or the second flow rate;

[0023] When the first flow rate increases to a maximum preset flow rate value or the second flow rate decreases to a minimum preset flow rate value, it is determined that the safety valve reaches a high bypass state.

[0024] Optionally, in the process of detecting the recovery state of the safety valve, the aviation fuel pump detection method includes:

[0025] Controlling the pump outlet pressure of the aviation fuel pump to gradually decrease from a maximum preset pressure value;

[0026] obtaining the second flow rate;

[0027] When the difference between the preset standard flow rate and the second flow rate is a second preset difference value, it is determined that the safety valve has reached a recovery state;

[0028] Wherein, the second flow rate is less than the preset standard flow rate.

[0029] Optionally, the second preset difference is less than or equal to 1.9 L / min.

[0030] Optionally, in the process of detecting the closed state of the safety valve, the aviation fuel pump detection method further includes:

[0031] Controlling the pump outlet pressure of the aviation fuel pump to maintain at a preset pressure value;

[0032] obtaining the second flow rate;

[0033] When the second flow rate remains constant, it is determined that the safety valve reaches a closed state.

[0034] Optionally, the aviation fuel pump detection method further includes:

[0035] The pump outlet pressure of the aviation fuel pump is controlled to be reduced to zero, so that the aviation fuel pump is in a closed state.

[0036] In a second aspect, the present application also provides an aviation fuel pump detection system for implementing the aviation fuel pump detection method, the detection system comprising an aviation fuel pump and a controller, the aviation fuel pump being provided with a safety valve, the safety valve being provided with a first flow sensor, the outlet of the aviation fuel pump being provided with a pressure sensor and a second flow sensor, the pressure sensor, the first flow sensor and the second flow sensor being electrically connected to the controller.

[0037] The beneficial effects of the aviation fuel pump detection method and detection system provided in the embodiments of the present application include, for example: in order to be able to more accurately determine the state of the safety valve, a detection method for an aviation fuel pump is designed and applied to the detection system for an aviation fuel pump. The detection method for an aviation fuel pump includes: controlling the pump outlet pressure of the aviation fuel pump to change, and obtaining in real time a first flow at the safety valve of the aviation fuel pump and a second flow at the pump outlet of the aviation fuel pump. The state of the safety valve can be more accurately determined based on the first flow or the second flow combined with the change trend of the pump outlet pressure. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. It should be understood that the following drawings only show certain embodiments of the present application and therefore should not be regarded as limiting the scope. For ordinary technicians in this field, other related drawings can be obtained based on these drawings without paying creative work.

[0039] Figure 1 A graph showing the change of the pump outlet pressure and the second flow rate over time in the embodiment of the present application;

[0040] Figure 2 This is a flow chart of steps S1-S3 in the aviation fuel pump detection method of an embodiment of the present application;

[0041] Figure 3 This is a flow chart of sub-steps S11-S13 of the aviation fuel pump detection method according to an embodiment of the present application;

[0042] Figure 4 This is a flow chart of sub-steps S21-S23 of the aviation fuel pump detection method according to an embodiment of the present application;

[0043] Figure 5This is a flow chart of sub-steps S31-S33 of the aviation fuel pump detection method according to an embodiment of the present application;

[0044] Figure 6 This is a flow chart of sub-steps S41-S43 of the aviation fuel pump detection method according to an embodiment of the present application;

[0045] Figure 7 This is a flow chart of sub-steps S51-S53 of the aviation fuel pump detection method according to an embodiment of the present application. DETAILED DESCRIPTION

[0046] In order to make the purpose, technical solution and advantages of the embodiments of the present application clearer, the technical solution in the embodiments of the present application will be clearly and completely described below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are part of the embodiments of the present application, rather than all the embodiments. The components of the embodiments of the present application described and shown in the drawings here can be arranged and designed in various different configurations.

[0047] Therefore, the following detailed description of the embodiments of the present application provided in the accompanying drawings is not intended to limit the scope of the present application for which protection is sought, but merely represents selected embodiments of the present application. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without creative work are within the scope of protection of the present application.

[0048] It should be noted that similar reference numerals and letters denote similar items in the following drawings, and therefore, once an item is defined in one drawing, further definition and explanation thereof is not required in subsequent drawings.

[0049] In the description of the present application, it should be noted that if the terms "upper", "lower", "inside", "outside", etc. appear to indicate an orientation or position relationship, it is based on the orientation or position relationship shown in the drawings, or is the orientation or position relationship in which the product of the invention is usually placed when used. It is only for the convenience of describing the present application and simplifying the description, and does not indicate or imply that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation, and therefore cannot be understood as a limitation on the present application.

[0050] In addition, the terms “first”, “second”, etc., if used, are merely used to distinguish between the descriptions and should not be understood as indicating or implying relative importance.

[0051] It should be noted that, in the absence of conflict, the features in the embodiments of the present application may be combined with each other.

[0052] The inventor of the present application has found that, in the current testing process of the explosion, high bypass, recovery and other states of the safety valve in the aviation fuel pump, the fuel pump pressure is generally adjusted manually, and the state of the safety valve is manually observed and judged according to the data displayed in the program, but the judgment of the safety valve state is relatively vague, and the state of the safety valve cannot be judged more accurately. The embodiment of the present application provides a detection method and detection system for aviation fuel pumps, which is at least used to solve the above technical problems.

[0053] An embodiment of the present application provides a detection system for an aviation fuel pump, which includes an aviation fuel pump and a controller. The aviation fuel pump is provided with a safety valve, and a first flow sensor is provided at the safety valve, and the first flow sensor is used to detect a first flow at the safety valve; a pressure sensor and a second flow sensor are provided at the outlet of the aviation fuel pump, and the pressure sensor is used to detect the pump outlet pressure of the aviation fuel pump, and the second flow sensor is used to detect the second flow at the pump outlet of the aviation fuel pump. The pressure sensor, the first flow sensor, and the second flow sensor are all electrically connected to the controller, and the controller can control the change of the pump outlet pressure of the aviation fuel pump.

[0054] Figure 1 , a graph showing changes in the pump outlet pressure p of an aviation fuel pump and a second flow rate Q at the pump outlet of the aviation fuel pump over time is shown. In the figure, curve C1 is a change curve of the second flow rate Q, and curve C2 is a change curve of the pump outlet pressure p, wherein the unit of the pump outlet pressure p is psig, the unit of the second flow rate Q is L / min, and the unit of time is s.

[0055] like Figure 2 As shown, the embodiment of the present application further provides an aviation fuel pump detection method, which is applied to the above-mentioned aviation fuel pump detection system. The aviation fuel pump detection method includes:

[0056] Step S1, controlling the change of the pump outlet pressure of the aviation fuel pump.

[0057] Step S2, obtaining a first flow rate at the safety valve of the aviation fuel pump and a second flow rate at the pump outlet of the aviation fuel pump.

[0058] Step S3: determining the state of the safety valve according to the first flow rate or the second flow rate.

[0059] In the above steps, the controller is used to control the increase or decrease of the pump outlet pressure of the aviation fuel pump. At the same time, the controller obtains the first flow at the safety valve detected in real time by the first flow sensor, the second flow at the pump outlet of the aviation fuel pump detected in real time by the second flow sensor, and the pump outlet pressure of the aviation fuel pump detected in real time by the pressure sensor. In this process, the controller can more accurately determine the state of the safety valve according to the first flow or the second flow combined with the change trend of the pump outlet pressure.

[0060] like Figure 3 As shown, in the process of detecting the explosion state of the safety valve, the detection method for the aviation fuel pump includes:

[0061] Sub-step S11, controlling the pump outlet pressure of the aviation fuel pump to gradually increase.

[0062] Sub-step S12: obtaining a first flow rate.

[0063] Sub-step S13: when the difference between the preset standard flow rate and the first flow rate is the first preset difference value, it is determined that the safety valve reaches a burst state; wherein the first flow rate is less than the preset standard flow rate.

[0064] The preset standard flow is data stored in the controller. In the above steps, the controller is used to control the pump outlet pressure of the aviation fuel pump to gradually increase. At the same time, the controller obtains the first flow at the safety valve detected by the first flow sensor in real time. When the difference between the preset standard flow and the first flow is the first preset difference, that is, Figure 1 At time a, the controller determines that the safety valve has reached the explosion state.

[0065] In this embodiment, the first preset difference is 3.8 L / min-5.7 L / min.

[0066] Exemplarily, the preset standard flow rate is 246L / min. When the first flow rate reaches 242L / min, the difference between the preset standard flow rate and the first flow rate, that is, the first preset difference, is 4L / min, and 4L / min is within the range of 3.8L / min-5.7L / min. At this time, the controller determines that the safety valve has reached a burst state; or, when the first flow rate reaches 241L / min, the difference between the preset standard flow rate and the first flow rate, that is, the first preset difference, is 5L / min, and 5L / min is within the range of 3.8L / min-5.7L / min. At this time, the controller determines that the safety valve has reached a burst state.

[0067] It should be noted that when the pump outlet pressure begins to increase, the second flow rate at the pump outlet of the aviation fuel pump also begins to increase. Before the safety valve reaches the burst state, the controller will control the pump outlet pressure of the aviation fuel pump to increase rapidly. At this time, a small amount of liquid will leak from the safety valve, causing the second flow rate to decrease slightly. After the safety valve reaches the burst state, the first flow rate gradually increases and the second flow rate gradually decreases.

[0068] like Figure 4 As shown, in the process of detecting that the safety valve is in a fully open state, the detection method for the aviation fuel pump includes:

[0069] Sub-step S21, controlling the pump outlet pressure of the aviation fuel pump to gradually increase.

[0070] Sub-step S22: obtaining a second flow rate.

[0071] Sub-step S23: when the second flow rate decreases rapidly, it is determined that the safety valve is in a fully open state.

[0072] In the above steps, the controller is used to control the pump outlet pressure of the aviation fuel pump to gradually increase, and at the same time, the controller obtains the second flow rate at the pump outlet of the aviation fuel pump detected in real time by the second flow sensor. When the second flow rate drops rapidly, that is, Figure 1 At time b, the controller determines that the safety valve is in a fully open state.

[0073] It should be noted that when the safety valve is in a fully open state, most of the liquid is discharged through the safety valve, so that the second flow rate will drop rapidly. Therefore, in the process of gradually increasing pump outlet pressure, once the second flow rate drops rapidly, it indicates that the safety valve is in a fully open state at this time.

[0074] like Figure 5 As shown, in the process of detecting the high bypass state of the safety valve, the detection method for the aviation fuel pump includes:

[0075] Sub-step S31, controlling the pump outlet pressure of the aviation fuel pump to increase to a maximum preset pressure value.

[0076] Sub-step S32: Obtain the first flow rate or the second flow rate.

[0077] Sub-step S33: when the first flow rate increases to a maximum preset flow rate value or the second flow rate decreases to a minimum preset flow rate value, it is determined that the safety valve reaches a high bypass state.

[0078] In the above steps, the controller is used to control the pump outlet pressure of the aviation fuel pump to increase to the maximum preset pressure value, and at the same time, the controller obtains the first flow at the safety valve detected in real time by the first flow sensor and the second flow at the pump outlet of the aviation fuel pump detected in real time by the second flow sensor. When the first flow increases to the maximum preset flow value or the second flow decreases to the minimum preset flow value, that is, Figure 1 At time c, the controller determines that the safety valve reaches a high bypass state, wherein the maximum preset pressure value, the maximum preset flow value, and the minimum preset flow value are all data stored in the controller.

[0079] It should be noted that when the pump outlet pressure of the aviation fuel pump increases to the maximum preset pressure value and the first flow increases to the maximum preset flow value, or when the pump outlet pressure of the aviation fuel pump increases to the maximum preset pressure value and the second flow decreases to the minimum preset flow value, it indicates that the safety valve reaches a high bypass state. When the safety valve reaches a high bypass state, only a small amount of liquid passes through the pump outlet, and the rest of the liquid circulates in the fuel pump through the safety valve.

[0080] like Figure 6 As shown, in the process of detecting the recovery state of the safety valve, the detection method for the aviation fuel pump includes:

[0081] Sub-step S41, controlling the pump outlet pressure of the aviation fuel pump to gradually decrease from the maximum preset pressure value.

[0082] Sub-step S42: obtaining a second flow rate.

[0083] Sub-step S43: when the difference between the preset standard flow rate and the second flow rate is a second preset difference value, it is determined that the safety valve reaches a recovery state; wherein the second flow rate is less than the preset standard flow rate.

[0084] In the above steps, the controller is used to control the pump outlet pressure of the aviation fuel pump to gradually decrease from the maximum preset pressure value, and at the same time, the controller obtains the second flow rate at the pump outlet of the aviation fuel pump detected in real time by the second flow sensor. When the difference between the preset standard flow rate and the second flow rate is the second preset difference value, that is, Figure 1 At time d, the controller determines that the safety valve has reached the recovery state.

[0085] In this embodiment, the second preset difference is less than or equal to 1.9 L / min.

[0086] Exemplarily, the preset standard flow rate is 246 L / min. When the second flow rate is greater than or equal to 244.1 L / min, the difference between the preset standard flow rate and the first flow rate, that is, the second preset difference, is less than or equal to 1.9 L / min. At this time, the controller determines that the safety valve has reached a burst state.

[0087] It should be noted that after the safety valve reaches the high bypass state, the pump outlet pressure begins to decrease, so that the first flow rate begins to decrease and the second flow rate begins to increase until the safety valve reaches the recovery state.

[0088] like Figure 7 As shown, in the process of detecting the closed state of the safety valve, the aviation fuel pump detection method also includes:

[0089] Sub-step S51, controlling the pump outlet pressure of the aviation fuel pump to maintain at a preset pressure value.

[0090] Sub-step S52: obtaining a second flow rate.

[0091] Sub-step S53: when the second flow rate remains constant, determine that the safety valve reaches a closed state.

[0092] In the above steps, the controller is used to control the pump outlet pressure of the aviation fuel pump to maintain at a preset pressure value, which is less than the maximum preset pressure value; at the same time, the controller obtains the second flow rate at the pump outlet of the aviation fuel pump detected in real time by the second flow sensor. When the second flow rate remains constant, that is, Figure 1 Between time d and time e, the controller determines that the safety valve reaches the closed state.

[0093] It should be noted that when the safety valve transitions from the recovery state to the closed state, the pump outlet pressure of the aviation fuel pump will increase instantaneously and then decrease, while the second flow at the pump outlet of the aviation fuel pump remains constant and the pump outlet pressure remains at a preset pressure value.

[0094] In addition, the aviation fuel pump detection method also includes:

[0095] The pump outlet pressure of the aviation fuel pump is controlled to be reduced to zero, so that the aviation fuel pump is in a closed state.

[0096] It should be noted that when the pump outlet pressure of the aviation fuel pump is reduced to zero by the controller, that is, Figure 1 At time e, the second flow rate at the pump outlet of the aviation fuel pump will slowly decrease to zero due to volumetric efficiency.

[0097] In summary, the embodiments of the present application provide a detection method and a detection system for an aviation fuel pump, which uses a controller to control the increase or decrease of the pump outlet pressure of the aviation fuel pump, and at the same time uses the controller to obtain a first flow at the safety valve and a second flow at the pump outlet of the aviation fuel pump. The state of the safety valve is judged according to the first flow or the second flow combined with the change trend of the pump outlet pressure, and the data can be recorded in real time, so the detection result is more accurate, and when the controller makes an incorrect judgment, manual verification can be performed by reviewing the data.

[0098] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A detection method for an aviation fuel pump, characterized in that: Applied to the detection system for aviation fuel pumps, the detection method for aviation fuel pumps includes: Controlling the change in pump outlet pressure of the aviation fuel pump; Acquire a first flow rate at a safety valve of the aviation fuel pump and a second flow rate at a pump outlet of the aviation fuel pump; The state of the safety valve is determined according to the first flow rate or the second flow rate.

2. The aviation fuel pump detection method according to claim 1, characterized in that: In the process of detecting the explosion state of the safety valve, the detection method for the aviation fuel pump includes: Controlling the pump outlet pressure of the aviation fuel pump to gradually increase; Obtaining the first flow rate; When the difference between the preset standard flow rate and the first flow rate is a first preset difference value, it is determined that the safety valve has reached a burst state; Wherein, the first flow rate is less than the preset standard flow rate.

3. The aviation fuel pump detection method according to claim 2, characterized in that: The first preset difference is 3.8L / min-5.7L / min.

4. The method for detecting an aviation fuel pump according to claim 1, characterized in that: In the process of detecting that the safety valve is in a fully open state, the aviation fuel pump detection method includes: Controlling the pump outlet pressure of the aviation fuel pump to gradually increase; obtaining the second flow rate; When the second flow rate decreases rapidly, it is determined that the safety valve is in a fully open state.

5. The method for detecting an aviation fuel pump according to claim 1, characterized in that: In the process of detecting the high bypass state of the safety valve, the detection method for the aviation fuel pump includes: Controlling the pump outlet pressure of the aviation fuel pump to increase to a maximum preset pressure value; obtaining the first flow rate or the second flow rate; When the first flow rate increases to a maximum preset flow rate value or the second flow rate decreases to a minimum preset flow rate value, it is determined that the safety valve reaches a high bypass state.

6. The method for detecting an aviation fuel pump according to claim 1, characterized in that: In the process of detecting the recovery state of the safety valve, the detection method for the aviation fuel pump includes: Controlling the pump outlet pressure of the aviation fuel pump to gradually decrease from a maximum preset pressure value; obtaining the second flow rate; When the difference between the preset standard flow rate and the second flow rate is a second preset difference value, it is determined that the safety valve has reached a recovery state; Wherein, the second flow rate is less than the preset standard flow rate.

7. The aviation fuel pump detection method according to claim 6, characterized in that: The second preset difference is less than or equal to 1.9 L / min.

8. The method for detecting an aviation fuel pump according to claim 1, characterized in that: In the process of detecting the closed state of the safety valve, the aviation fuel pump detection method further includes: Controlling the pump outlet pressure of the aviation fuel pump to maintain at a preset pressure value; obtaining the second flow rate; When the second flow rate remains constant, it is determined that the safety valve reaches a closed state.

9. The aviation fuel pump detection method according to claim 1, characterized in that: The aviation fuel pump detection method also includes: The pump outlet pressure of the aviation fuel pump is controlled to be reduced to zero, so that the aviation fuel pump is in a closed state.

10. A detection system for an aviation fuel pump, characterized in that: Used to implement the aviation fuel pump detection method according to any one of claims 1 to 9, the detection system includes an aviation fuel pump and a controller, the aviation fuel pump is provided with a safety valve, a first flow sensor is provided at the safety valve, a pressure sensor and a second flow sensor are provided at the outlet of the aviation fuel pump, and the pressure sensor, the first flow sensor and the second flow sensor are all electrically connected to the controller.

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