Aircraft fuel ground full-scale test system and its hot oil return flow measurement test method

Abstract

The application relates to an airplane fuel ground full-mode test system and a hot return oil flow measurement test method thereof, wherein the airplane fuel ground full-mode test system comprises a tested system and a hot return oil flow metering system; the tested system comprises a fuel tank, a fuel supply pump and a fuel heat exchanger; the fuel supply pump is arranged in the fuel tank, an outlet of the fuel supply pump is connected with a fuel supply main pipe, and an outlet of the fuel supply main pipe is divided into a fuel supply pipeline and a hot return oil pipeline; an outlet of the fuel supply pipeline is connected with an engine and an APU; an outlet of the hot return oil pipeline is connected with the fuel tank, a fuel heat exchanger, a hot return oil flow regulating valve and a test state switching valve are sequentially arranged on the hot return oil pipeline; the hot return oil flow metering system comprises an oil collecting tank, a transfer pump and an oil storage tank; the oil collecting tank is connected with the hot return oil pipeline through a drainage pipeline, a drainage control valve is arranged on the drainage pipeline; the transfer pump is arranged in the oil collecting tank, an outlet of the transfer pump is connected with the oil storage tank through a hot return oil flow measurement pipeline, and a servo regulating valve and a turbine flowmeter are sequentially arranged on the hot return oil flow measurement pipeline.

Description

Technical Field

[0001] This application belongs to the field of aircraft fuel system ground full-model test technology, specifically relating to an aircraft fuel ground full-model test system and its hot return oil flow measurement test method. Background Technology

[0002] While meeting the fuel supply flow requirements of the engine or APU, the aircraft fuel system needs to have the ability to cool the hot return fuel. Therefore, when designing the aircraft fuel system, a hot return fuel line is usually set up in parallel with the fuel supply line, and a hot return fuel flow regulating valve is installed on the hot return fuel line to control the fuel supply flow.

[0003] When designing aircraft fuel systems, theoretical calculations and numerical simulations alone cannot fully and realistically verify whether their performance meets requirements. Therefore, a full-scale ground-based simulation test of the aircraft fuel system is designed to comprehensively verify all aspects of the system. The magnitude of the hot return fuel flow rate is crucial to the design of the aircraft fuel system, and one of the items in the full-scale ground-based simulation test of the aircraft fuel system is the hot return fuel flow rate measurement test.

[0004] Currently, most aircraft fuel ground full-scale test systems use turbine flow meters installed on the hot return fuel line to measure the hot return fuel flow. However, the turbine flow meter has a significant impact on the hot return fuel flow resistance in the hot return fuel line, creating a large pressure difference before and after the measurement location. This severely affects the hot return fuel fluid pressure, which in turn causes changes in the pressure in the fuel supply line, affecting the fuel supply line outlet pressure and other items in the aircraft fuel system ground full-scale test, easily leading to misjudgments of the aircraft fuel system performance.

[0005] In some aircraft fuel ground full-scale test systems, the hot return oil flow rate is measured by installing an external clamp-on ultrasonic flow meter around the hot return oil pipeline. Although this method of measuring hot return oil flow rate does not affect the hot return oil flow resistance in the hot return oil pipeline, its measurement accuracy is not high and it is difficult to meet the accuracy requirements of hot return oil flow rate measurement.

[0006] This application is made in view of the aforementioned technical deficiencies. Summary of the Invention

[0007] The purpose of this application is to provide an aircraft fuel ground full-scale test system and its hot return oil flow measurement test method, which can accurately measure the hot return oil flow while completing the hot return oil flow measurement test, without affecting the testing of other items, thus ensuring the effectiveness of the aircraft fuel ground full-scale test.

[0008] The technical solution of this application is:

[0009] A ground-based full-scale test system for aircraft fuel includes a test system and a hot return fuel flow metering system;

[0010] The tested system includes a fuel tank, a fuel supply pump, and a fuel heat exchanger;

[0011] The fuel pump is installed inside the fuel tank, and its outlet is connected to the fuel main. The outlet of the fuel main is divided into a fuel supply line and a hot return line.

[0012] The fuel supply line outlet connects to the engine and APU;

[0013] The hot oil return pipeline outlet is connected to the fuel tank, and a fuel heat exchanger, a hot oil return flow regulating valve, and a test state switching valve are installed on it in sequence.

[0014] The hot return oil flow metering system includes an oil collection tank, a transfer pump, and an oil storage tank;

[0015] The oil collection tank is connected to the hot return oil pipeline through a diversion pipeline. The connection point of the diversion pipeline on the hot return oil pipeline is between the hot return oil flow regulating valve and the test state switching valve, and a diversion control valve is installed on it.

[0016] The transfer pump is installed in the oil collection tank, and its outlet is connected to the oil storage tank through the hot return oil flow measurement pipeline. The hot return oil flow measurement pipeline is equipped with a servo regulating valve and a turbine flow meter in sequence.

[0017] According to at least one embodiment of this application, in the above-described aircraft fuel ground full-scale test system, a fireproof hose is installed on the fuel supply line.

[0018] According to at least one embodiment of this application, in the above-described aircraft fuel ground full-scale test system, a level gauge is installed on the fuel collection tank.

[0019] According to at least one embodiment of this application, in the above-described aircraft fuel ground full-scale test system, a safety valve is installed on the fuel collection tank.

[0020] According to at least one embodiment of this application, in the above-described aircraft fuel ground full-scale test system, the fuel collection tank is equipped with a cooler.

[0021] According to at least one embodiment of this application, in the above-described aircraft fuel ground full-scale test system, the fuel supply pump is located at the bottom of the fuel tank.

[0022] According to at least one embodiment of this application, in the above-described aircraft fuel ground full-scale test system, the transfer pump is located at the bottom of the fuel collection tank.

[0023] According to at least one embodiment of this application, in the above-described aircraft fuel ground full-scale test system, the test state switching valve is a manual valve.

[0024] According to at least one embodiment of this application, in the above-described aircraft fuel ground full-scale test system, the drain control valve is a manual valve.

[0025] A test method for measuring the hot return flow rate of an aircraft fuel system, implemented based on the aforementioned aircraft fuel ground full-scale test system, includes:

[0026] Close the test state switching valve, open the diversion control valve, connect the hot return oil flow metering system to the system under test, divert the hot return oil to the oil collection tank, and when the level gauge reaches the upper limit, start the transfer pump and open the servo regulating valve to transfer the oil in the oil collection tank to the oil storage tank.

[0027] When the hot return oil flow measurement test is stopped, the remaining oil in the oil collection tank is transferred to the oil storage tank using a transfer pump;

[0028] The flow rate of hot return oil is obtained by measuring the amount of oil transferred from the oil collection tank and storage tank using a turbine flow meter.

[0029] This application has at least the following beneficial technical effects:

[0030] This invention provides a full-scale ground test system for aircraft fuel and a test method for measuring the hot return oil flow rate. The system can accurately measure the hot return oil flow rate while conducting other tests, thus ensuring the effectiveness of the full-scale ground test for aircraft fuel. Attached Figure Description

[0031] Figure 1 This is a schematic diagram of the aircraft fuel ground full-scale test system provided in the embodiments of this application;

[0032] in:

[0033] 1-Fuel tank; 2-Fuel supply pump; 3-Fuel heat exchanger; 4-Hot oil return flow regulating valve; 5-Test state switching valve; 6-Fuel collection tank; 7-Transfer pump; 8-Fuel reservoir; 9-Drainage control valve; 10-Level gauge; 11-Safety valve; 12-Cooler; 13-Servo regulating valve; 14-Turbine flow meter.

[0034] To better illustrate this embodiment, some content in the accompanying drawings may be omitted, enlarged, or reduced. They are for illustrative purposes only and should not be construed as limiting the scope of this application. Detailed Implementation

[0035] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings, and other related parts can be referred to the general design.

[0036] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The word "comprising" as used in this application description indicates that the concept preceding the word encompasses the concepts listed following the word and their equivalents, without excluding other related concepts.

[0037] Furthermore, the terms indicating location used in the description of this application are only used to indicate relative directions or positional relationships. When the absolute position of the described object changes, its relative positional relationship may also change accordingly. It should also be noted that, unless otherwise explicitly specified and limited, terms such as "installation" and "connection" used in the description of this application should be interpreted broadly. For example, a connection can be a fixed connection or a detachable connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium. Those skilled in the art can understand its specific meaning in this application according to the specific circumstances.

[0038] When conducting hot return oil flow measurement tests, only the measurement of the hot return oil flow needs to be considered, and the operating conditions at the downstream end of the hot return oil pipeline are not important. Based on this, this application provides an aircraft fuel ground full-scale test system, including a test system and a hot return oil flow measurement system, such as... Figure 1 As shown.

[0039] The test system was the engine / APU fuel supply section of a ground-based 1:1 simulated aircraft fuel system, including fuel tank 1, fuel pump 2, fuel heat exchanger 3, etc.

[0040] The fuel pump 2 is installed inside the fuel tank 1 at the bottom of the fuel tank 1. Its outlet is connected to the fuel supply main pipe, and the outlet of the fuel supply main pipe is divided into a fuel supply line and a hot return line.

[0041] Fireproof hoses are installed on the fuel supply line, with the outlets connected to the engine and APU for supplying fuel to the engine and APU.

[0042] The hot return oil pipeline outlet is connected to the fuel tank 1, and a fuel heat exchanger 3, a hot return oil flow regulating valve 4, and a test state switching valve 5 are installed on it in sequence. The test state switching valve 5 is a manual valve.

[0043] The hot return oil flow metering system includes an oil collection tank 6, a transfer pump 7, and an oil storage tank 8.

[0044] The oil collection tank 6 is connected to the hot return oil pipeline through a diversion pipeline. The connection point of the diversion pipeline on the hot return oil pipeline is between the hot return oil flow regulating valve 4 and the test state switching valve 5. A diversion control valve 9 is installed on it, and the diversion control valve 9 is a manual valve.

[0045] The oil collection tank 6 is equipped with a level gauge 10 and a safety valve 11, and a cooler 12 can be installed inside it.

[0046] The transfer pump 7 is installed inside the oil collection tank 6 at the bottom of the oil collection tank 6. It is a high-power pump, and its outlet is connected to the oil storage tank 8 through the hot return oil flow measurement pipeline. The hot return oil flow measurement pipeline is equipped with a servo regulating valve 13 and a turbine flow meter 14 in sequence.

[0047] When conducting tests other than the hot return fuel flow measurement test using the aircraft fuel ground full-model test system disclosed in the above embodiments, the test state switching valve 5 is opened and the flow control valve 9 is closed to disconnect the hot return fuel flow metering system from the test system. The hot return fuel flow metering system will not affect the test system, and the test system can be used to effectively verify the performance of the aircraft fuel system.

[0048] During the hot return oil flow measurement test, the test state switching valve 5 can be closed and the diversion control valve 9 can be opened to connect the hot return oil flow metering system to the system under test. The hot return oil is diverted into the oil collection tank 6. When the level gauge 10 reaches the upper limit, the transfer pump 7 is started and the servo regulating valve 13 is opened to transfer the oil in the oil collection tank 6 to the oil storage tank 8. When the hot return oil flow measurement test is stopped, the transfer pump 7 is used to transfer the remaining oil in the oil collection tank 6 to the oil storage tank 8. The turbine flow meter 14 is used to measure the amount of oil transferred from the oil collection tank 6 to the oil storage tank 8 to obtain the hot return oil flow rate, thereby achieving accurate measurement of the hot return oil flow rate.

[0049] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A ground-based full-scale test system for aircraft fuel, characterized in that, This includes the tested system and the hot return oil flow metering system; The tested system includes a fuel tank (1), a fuel pump (2), and a fuel heat exchanger (3). The fuel pump (2) is installed inside the fuel tank (1), and its outlet is connected to the fuel supply main pipe. The outlet of the fuel supply main pipe is divided into a fuel supply line and a hot return line. The fuel supply line outlet connects to the engine and APU; The hot oil return pipeline outlet is connected to the fuel tank (1), and a fuel heat exchanger (3), a hot oil return flow regulating valve (4), and a test state switching valve (5) are installed on it in sequence. The hot return oil flow metering system includes an oil collection tank (6), a transfer pump (7), and an oil storage tank (8); The oil collection tank (6) is connected to the hot return oil pipeline through the diversion pipeline. The connection point of the diversion pipeline on the hot return oil pipeline is between the hot return oil flow regulating valve (4) and the test state switching valve (5), and a diversion control valve (9) is installed on it. The transfer pump (7) is installed in the oil collection tank (6), and its outlet is connected to the oil storage tank (8) through the hot return oil flow measurement pipeline. The hot return oil flow measurement pipeline is equipped with a servo regulating valve (13) and a turbine flow meter (14) in sequence.

2. The aircraft fuel ground full-scale test system according to claim 1, characterized in that, Fireproof hoses are installed on the oil supply lines.

3. The aircraft fuel ground full-scale test system according to claim 2, characterized in that, A level gauge (10) is installed on the oil collection tank (6).

4. The aircraft fuel ground full-scale test system according to claim 3, characterized in that, A safety valve (11) is installed on the oil collection tank (6).

5. The aircraft fuel ground full-scale test system according to claim 4, characterized in that, The oil collection tank (6) is equipped with a cooler (12).

6. The aircraft fuel ground full-scale test system according to claim 5, characterized in that, The fuel pump (2) is located at the bottom of the fuel tank (1).

7. The aircraft fuel ground full-scale test system according to claim 6, characterized in that, The transfer pump (7) is located at the bottom of the oil collection tank (6).

8. The aircraft fuel ground full-scale test system according to claim 7, characterized in that, The test state switching valve (5) is a manual valve.

9. The aircraft fuel ground full-scale test system according to claim 8, characterized in that, The drainage control valve (9) is a manual valve.

10. A test method for measuring the hot return oil flow rate of an aircraft fuel system, implemented based on the aircraft fuel ground full-scale test system according to claim 9, characterized in that, include: Close the test state switching valve (5), open the diversion control valve (9), connect the hot return oil flow metering system to the test system, divert the hot return oil to the oil collection tank (6), when the level gauge (10) reaches the upper limit, start the transfer pump (7) and open the servo regulating valve (13) to transfer the oil in the oil collection tank (6) to the oil storage tank (8); When the hot return oil flow measurement test is stopped, the remaining oil in the oil collection tank (6) is transferred to the oil storage tank (8) using the transfer pump (7). The flow rate of hot return oil is obtained by measuring the amount of oil transferred from the oil collection tank (6) and the oil storage tank (8) using a turbine flow meter (14), thus realizing the measurement of hot return oil flow rate.

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