A Method for Determining the Fuel Leakage Boundary of an Aeroengine Fuel Accessory

Abstract

This application belongs to the field of aero-engine control systems, and particularly relates to a method for determining the fuel leakage amount boundary of a fuel accessory for an aero-engine. It includes: Step 1, building a test pipeline; Step 2, excessively grinding the F-interface part of the fuel accessory A so that its leakage amount meets the pressure for the complete operation of the fuel accessory B; Step 3, conducting tests. This application can reduce the difficulty of grinding test pieces. After manufacturing leakage by grinding the test piece one to two times, the test requirements can be met, and there is no need for repeated grinding; running the system tester one to two times can achieve the purpose of test verification, saving a large amount of manpower and material resources; only one test part to be ground is required for one test, saving a large number of test parts and reducing the part scrap rate; the fuel discharged during the test process is not contaminated and can be reused, saving costs.

Description

Technical Field

[0001] This application belongs to the field of aero-engine control systems, and particularly relates to a method for determining the fuel leakage boundary of a fuel accessory for an aero-engine. Background Art

[0002] An aero-engine control system mainly consists of a fuel system and an electrical system. The fuel system is composed of various fuel accessories and their related pipelines connected together. There are several fuel accessories in the fuel system. Usually, after establishing pressure through the operation of a certain fuel accessory, it drives the operation of another fuel accessory to meet the overall requirements. Most fuel accessories adopt mechanical structure control or a control method combining mechanical structure and electricity, and there will be a certain amount of fuel leakage at the mating surfaces where mechanical structures are in contact. Therefore, the process from the start of operation to full operation of the fuel accessory is not instantaneous, that is, there is a critical state between working and non-working.

[0003] When designing the fuel system, it is necessary to find the pressure and flow rate that make the fuel accessory in an intermittent working state for the control boundary of the fuel leakage design index. When there is a fault in the fuel system, there is a need to verify whether a certain fuel accessory is in an intermittent working state, or whether the fuel leakage will cause a fault phenomenon. When looking for the working point where a certain accessory in the fuel system is in a critical state, it is often necessary to manually increase the fuel leakage to achieve the goal.

[0004] In the prior art, the method of verifying whether a fuel accessory is in an intermittent working state by grinding the test piece to have a leakage amount has its inherent drawbacks, which are listed as follows: (1) It is very difficult to grind the test piece with an accuracy that exactly meets the test requirements, and the grinding difficulty is extremely high. (2) After each grinding of the test piece, it is necessary to run the system tester for testing to verify whether the grinding amount meets the requirements. If the grinding amount is insufficient, it is necessary to grind repeatedly and run the system tester for testing and verification again, wasting a large amount of manpower and material resources. (3) The test piece for testing needs to be ground on a complete and qualified product. Due to the irreversibility of the grinding work, once the grinding is excessive, it becomes a scrap. If parts that meet the test requirements are ground out, a large number of intact test parts are required.

[0005] Therefore, it is desired to have a technical solution to overcome or at least mitigate at least one of the above-mentioned defects of the prior art. Summary of the Invention

[0006] The purpose of this application is to provide a method for determining the fuel leakage boundary of a fuel accessory for an aero-engine to solve at least one problem existing in the prior art.

[0007] The technical solution of this application is as follows:

[0008] A method for determining the fuel leakage amount boundary of an aero-engine fuel accessory, comprising:

[0009] Step 1: Set up a test pipeline, and the test pipeline includes:

[0010] Fuel accessory A and fuel accessory B. Fuel accessory A includes E interface, F interface, and C interface. Fuel accessory B includes H10 interface, H8 interface, and H2 interface. Among them,

[0011] The F interface is connected to the H8 interface through a first pipeline. A first pressure gauge and a first flowmeter are arranged on the first pipeline. And the first pipeline is connected to a joint pipeline through a three-way joint. A stepless adjustable flow-limiting valve and a second flowmeter are arranged on the joint pipeline;

[0012] The E interface is connected to the H10 interface through a second pipeline;

[0013] The C interface is connected to the H2 interface through a third pipeline;

[0014] Step 2: Excessively grind the F interface part of the fuel accessory A so that its leakage amount meets the pressure when the fuel accessory B is fully in operation;

[0015] Step 3: Conduct a test:

[0016] Check the test pipeline to ensure that when the stepless adjustable flow-limiting valve is adjusted to the most closed state, the fuel accessory B is in the working state, and when the stepless adjustable flow-limiting valve is adjusted to the most open state, the fuel accessory B stops working;

[0017] Gradually adjust the stepless adjustable flow-limiting valve from the most open state to the most closed state. The pressure in the first pipeline gradually increases until the pressure just makes the fuel accessory B in the critical state of working and not working. Record the PH8 pressure, QE flow rate, and QF flow rate at this time. Among them, the PH8 pressure is the measured value of the first pressure gauge, the QE flow rate is the measured value of the first flowmeter, and the QF flow rate is the measured value of the second flowmeter.

[0018] In at least one embodiment of the present application, the joint pipeline is connected to the system return fuel tank.

[0019] In at least one embodiment of the present application, a second pressure gauge is arranged on the second pipeline.

[0020] In at least one embodiment of the present application, a third pressure gauge is arranged on the third pipeline.

[0021] The invention has at least the following beneficial technical effects:

[0022] The method for determining the fuel leakage boundary of the fuel accessories of an aero-engine in this application can reduce the difficulty of grinding test pieces. After grinding the test pieces to cause leakage one to two times, the test requirements can be met, and there is no need for repeated grinding. It only needs to run the system tester one to two times to achieve the purpose of test verification, saving a large amount of manpower and material resources. Only one test part to be ground is required for one test, saving a large number of test parts and reducing the part rejection rate. The fuel discharged during the test process is not contaminated and can be reused, saving costs. BRIEF DESCRIPTION OF THE DRAWINGS

[0023] Figure 1 is a schematic diagram of the test pipeline of an embodiment of this application. DETAILED DESCRIPTION OF THE EMBODIMENTS

[0024] To make the purpose, technical solutions, and advantages of the implementation of this application clearer, the technical solutions in the embodiments of this application will be described in more detail below with reference to the accompanying drawings in the embodiments of this application. In the drawings, the same or similar reference numerals represent the same or similar elements or elements with the same or similar functions from beginning to end. The described embodiments are some, but not all, of the embodiments of this application. The embodiments described below with reference to the accompanying drawings are exemplary and are intended to explain this application and should not be construed as limiting this application. All other embodiments obtained by those of ordinary skill in the art based on the embodiments of this application without creative efforts shall fall within the protection scope of this application. The embodiments of this application will be described in detail below with reference to the accompanying drawings.

[0025] In the description of this application, it should be understood that the terms "center", "longitudinal", "transverse", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. indicate the orientation or positional relationship based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing this 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 should not be construed as limiting the protection scope of this application.

[0026] The following combines the attached Figure 1 to make a further detailed description of this application.

[0027] This application provides a method for determining the fuel leakage boundary of the fuel accessories of an aero-engine, including:

[0028] Step 1: Build a test pipeline, and the test pipeline includes:

[0029] Fuel accessory A and fuel accessory B. Fuel accessory A includes E interface, F interface, and C interface. Fuel accessory B includes H10 interface, H8 interface, and H2 interface. Among them,

[0030] The F interface is connected to the H8 interface through the first pipeline. A first pressure gauge and a first flow meter are provided on the first pipeline. And the first pipeline is connected to the joint pipeline through a tee joint. A stepless regulating flow-limiting valve and a second flow meter are provided on the joint pipeline. The joint pipeline is connected to the system return oil tank;

[0031] The E interface is connected to the H10 interface through the second pipeline. A second pressure gauge is provided on the second pipeline;

[0032] The C interface is connected to the H2 interface through the third pipeline. A third pressure gauge is provided on the third pipeline;

[0033] Step 2: Excessively grind the F interface part of the fuel accessory A so that its leakage meets the pressure for the complete operation of the fuel accessory B;

[0034] Step 3: Conduct a test:

[0035] Check the test pipeline to ensure that when the stepless regulating flow-limiting valve is adjusted to the most closed state, the fuel accessory B is in the working state, and when the stepless regulating flow-limiting valve is adjusted to the most open state, the fuel accessory B stops working;

[0036] Gradually adjust the stepless regulating flow-limiting valve from the most open state to the most closed state. The pressure in the first pipeline gradually increases until the pressure exactly makes the fuel accessory B in the critical state of working and not working. Record the PH8 pressure, QE flow rate, and QF flow rate at this time. Among them, the PH8 pressure is the measured value of the first pressure gauge, the QE flow rate is the measured value of the first flow meter, and the QF flow rate is the measured value of the second flow meter.

[0037] The method for determining the fuel leakage boundary of the aero-engine fuel accessory in this application, as Figure 1 shown, under normal working conditions, in order to make the fuel accessory B work, the F interface in the fuel accessory A is opened, the fuel pressure from the F interface to the H8 interface is established, and the valve in the H8 interface is opened to make the fuel accessory B work; after the fuel accessory B works, the H10 interface and the H2 interface are opened respectively to transfer the fuel pressure to the E interface and the C interface in the fuel accessory A for work; in an abnormal state, when the fuel accessory B does not need to work, the F interface in the fuel accessory A is in the closed state. However, due to fuel leakage inside the F interface, a certain fuel pressure will be established in the pipeline from the F interface to the H8 interface. When the pressure reaches the value required by the fuel accessory B, the fuel accessory B will abnormally start working. When the fuel pressure is exactly in the critical state of making the fuel accessory B in the state of working and not working, that is: it will make the fuel accessory B in an intermittent working state. If it is necessary to verify whether the fuel accessory B has an intermittent working state or to find the flow rate and pressure at which the fuel leakage of the F interface in the fuel accessory A exactly makes the fuel accessory B in an intermittent working state, it is necessary to passFigure 1 The test pipeline in

[0038] In the test pipeline of this application, fuel accessory A has three interfaces, denoted by E, F, and C, and fuel accessory B has three interfaces, denoted by H10, H8, and H2, and are connected in the following manner:

[0039] (1) The F interface is connected to the H8 interface. A first pressure gauge is set on the pipeline to monitor the pressure change, and the monitored pressure is denoted by PH8. A first flowmeter is installed on the pipeline for flow measurement, denoted by QE. At the same time, a tee joint is added to the pipeline between the F interface and the H8 interface. Two joints are used to connect to the original pipeline. An infinitely adjustable flow limiting valve is installed on the newly added joint pipeline, and a second flowmeter is installed on the newly added pipeline for measuring the fuel flow discharged, denoted by QF;

[0040] (2) The E interface is connected to the H10 interface. A pressure gauge 2 is set on the pipeline to monitor the pressure change, and the monitored pressure is denoted by PH10;

[0041] (3) The C interface is connected to the H2 interface. A pressure gauge 3 is set on the pipeline to monitor the pressure change, and the monitored pressure is denoted by PH2;

[0042] (4) Connect the newly added joint pipeline to the system return fuel tank to ensure that the excess fuel discharged is not contaminated and can be reused.

[0043] The method for determining the fuel leakage amount boundary of the fuel accessories of the aero-engine in this application over-grinds the required grinding amount of the parts so that the leakage amount reaches the pressure at which fuel accessory B is put into operation. This can reduce the repeated grinding of the parts to find exactly the pressure point at which the fuel accessory is in intermittent operation. Over-grinding of the parts is relatively easy to meet the test requirements and can easily reach the test requirements at one time. If after verification by the system tester, the leakage amount cannot reach the pressure at which the fuel accessory is fully put into operation, then continue to increase the grinding amount to make the leakage amount continue to increase. If after verification by the system tester, the leakage amount can meet the pressure at which the fuel accessory is fully put into operation, then the test can continue.

[0044] The method for determining the fuel leakage boundary of the fuel accessories of an aero-engine in this application involves checking the test pipeline before the formal test. Adjust the stepless regulating flow-limiting valve to the most closed state. After ensuring the operation of the system tester, the fuel leakage from the F interface in the fuel accessory A can meet the pressure required to open the working valve of the fuel accessory B. After the system tester operates, the fuel accessory B is in the working state. Then adjust the stepless regulating flow-limiting valve to the most open state, that is, the state with the maximum fuel discharge flow rate, and the fuel accessory B will stop working. Finally, conduct the formal test. Gradually adjust the stepless regulating flow-limiting valve from the most open state to the most closed state, that is, the fuel discharge flow rate gradually decreases. On the premise that the fuel leakage from the F interface in the fuel accessory A remains unchanged, the pressure in the pipeline from the F interface to the H8 interface will gradually increase until the pressure just makes the fuel accessory B in the critical state of working and not working. Record the PH8 pressure, QE flow rate, and QF flow rate at this time.

[0045] The method for determining the fuel leakage boundary of the fuel accessories of an aero-engine in this application can reduce the grinding accuracy by over-grinding the required grinding amount of the parts so that the leakage amount reaches the pressure for the fuel accessory to be put into operation. A manual stepless regulating flow-limiting valve is connected in parallel on the pipeline with fuel leakage to release excessive fuel leakage to achieve the fuel pressure for the fuel accessory to work intermittently.

[0046] The method for determining the fuel leakage boundary of the fuel accessories of an aero-engine in this application can achieve the following effects through the method of over-grinding the parts combined with the test method of setting a stepless regulating flow-limiting valve on the newly added drain pipeline: It can verify whether the fuel accessory has an intermittent working state; when the fuel accessory has an intermittent working state, it can explore the required flow rate and pressure and find the boundary of the fuel leakage design index; it can reduce the grinding accuracy of the parts, reduce the grinding difficulty, save test parts and test costs, and more easily achieve the test purpose; the fuel discharged through the drain pipeline will not be contaminated and can be reused. This application can not only more simply achieve the test purpose and find the design index of the fuel leakage boundary, but also save test costs and labor costs, and can be applied in various fuel system tests of aero-engines, with good market application prospects.

[0047] As mentioned above, it is only the specific implementation manner of this application, but the protection scope of this application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the technical field within the technical scope disclosed in this application should be covered by the protection scope of this application. Therefore, the protection scope of this application should be subject to the protection scope of the claimed rights.

Claims

1. A method for determining the fuel leakage amount boundary of an aeroengine fuel accessory, characterized in that Including: Step 1: Set up a test pipeline, and the test pipeline includes: Fuel accessory A and fuel accessory B. Fuel accessory A includes E interface, F interface, and C interface. Fuel accessory B includes H10 interface, H8 interface, and H2 interface. Among them, The F interface is connected to the H8 interface through a first pipeline. A first pressure gauge and a first flowmeter are arranged on the first pipeline. And the first pipeline is connected to a joint pipeline through a tee joint. A stepless adjustable flow-limiting valve and a second flowmeter are arranged on the joint pipeline; The E interface is connected to the H10 interface through a second pipeline; The C interface is connected to the H2 interface through a third pipeline; Step 2: Excessively grind the F interface parts of the fuel accessory A so that its leakage meets the pressure for the full operation of the fuel accessory B; Step 3: Conduct a test: Check the test pipeline to ensure that when the stepless adjustable flow-limiting valve is adjusted to the most closed state, the fuel accessory B is in the working state, and when the stepless adjustable flow-limiting valve is adjusted to the most open state, the fuel accessory B stops working; Gradually adjust the stepless adjustable flow-limiting valve from the most open state to the most closed state. The pressure in the first pipeline gradually increases until the pressure just makes the fuel accessory B in the critical state between working and non-working. Record the PH8 pressure, QE flow rate, and QF flow rate at this time. Among them, the PH8 pressure is the measured value of the first pressure gauge, the QE flow rate is the measured value of the first flowmeter, and the QF flow rate is the measured value of the second flowmeter.

2. The method for determining the fuel leakage amount boundary of an aero-engine fuel accessory according to claim 1, wherein The joint pipeline is connected to the system return oil tank.

3. The method for determining the fuel leakage amount boundary of an aeroengine fuel accessory according to claim 1, characterized in that, A second pressure gauge is arranged on the second pipeline.

4. The method for determining the fuel leakage amount boundary of an aero-engine fuel accessory according to claim 1, wherein, A third pressure gauge is arranged on the third pipeline.

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