Aircraft fuel oil ground full-model test system and hot return oil flow measurement test method thereof

Abstract

The invention relates to an aircraft fuel oil ground full-model test system and a hot return oil flow measurement test method thereof, and the aircraft fuel oil ground full-model test system comprises a tested system and a hot return oil flow measurement system. The tested system comprises a fuel tank, a fuel feed pump and a fuel heat exchanger; the oil supply pump is arranged in the fuel tank, and an outlet of the oil supply pump is connected with the oil delivery header pipe. An outlet of the oil supply pipeline is connected with the engine and the APU; an outlet of the hot oil return pipeline is connected with the fuel tank and is sequentially provided with a fuel heat exchanger, a hot oil return flow regulating valve and a test state switching valve; 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 oil return 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 measuring pipeline, and a servo adjusting valve and a turbine flowmeter are sequentially arranged on the hot return oil flow measuring pipeline.

Description

TECHNICAL FIELD

[0001] The application belongs to the technical field of aircraft fuel system ground full-scale test, and particularly relates to an aircraft fuel ground full-scale test system and a hot oil return flow measurement test method thereof. BACKGROUND

[0002] The aircraft fuel system needs to have the ability to cool the hot oil return while meeting the oil supply flow demand of the engine or APU, therefore, when the aircraft fuel system is designed, a hot oil return pipeline is usually arranged side by side with the oil supply pipeline, and a hot oil return flow regulating valve is arranged on the hot oil return pipeline to control the oil supply flow.

[0003] When the aircraft fuel system is designed, the performance cannot be comprehensively and truly verified by theoretical calculation and numerical simulation, therefore, the aircraft fuel system ground full-scale test is designed to comprehensively verify the aircraft fuel system in all aspects. The hot oil return flow is crucial to the design of the aircraft fuel system, and the hot oil return flow measurement test is one of the projects of the aircraft fuel system ground full-scale test.

[0004] Currently, the aircraft fuel ground full-scale test system measures the hot oil return flow by arranging a turbine flowmeter on the hot oil return pipeline, however, the turbine flowmeter has a great influence on the flow resistance of the hot oil in the hot oil return pipeline, and a large pressure difference is generated before and after the measurement position, which seriously affects the hot oil fluid pressure, and further causes the change of the pressure in the oil supply pipeline, affects the outlet pressure of the oil supply pipeline, and affects other projects of the aircraft fuel system ground full-scale test, which is easy to cause misjudgment of the performance of the aircraft fuel system.

[0005] In some aircraft fuel ground full-scale test systems, an external clamping ultrasonic flowmeter is arranged on the periphery of the hot oil return pipeline to measure the hot oil return flow, this kind of hot oil return flow measurement method does not have an influence on the flow resistance of the hot oil in the hot oil return pipeline, but the measurement accuracy is not high, and it is difficult to meet the accuracy requirement of the hot oil return flow measurement.

[0006] The present application is proposed in view of the existence of the above technical defects. SUMMARY

[0007] The purpose of the present application is to provide an aircraft fuel ground full-scale test system and a hot oil return flow measurement test method thereof, which can accurately measure the hot oil return flow while not affecting the test of other projects after completing the hot oil return flow measurement test, and ensure the effectiveness of the aircraft fuel ground full-scale test.

[0008] The technical scheme of the present application is:

[0009] An aircraft fuel ground full-scale test system, comprising a tested system and a hot oil return flow metering system.

[0010] The test system comprises a fuel tank, a fuel supply pump, and a fuel heat exchanger.

[0011] The fuel supply pump is arranged in the fuel tank, and an outlet of the fuel supply pump is connected to a fuel supply pipeline.

[0012] The fuel supply pipeline is connected to an engine and an APU.

[0013] The heat return oil pipeline is connected to the fuel tank, and a fuel heat exchanger, a heat return oil flow regulating valve, and a test state switching valve are sequentially arranged on the heat return oil pipeline.

[0014] The heat return oil flow measurement system comprises an oil collecting tank, a transfer pump, and an oil storage tank.

[0015] The oil collecting tank is connected to the heat return oil pipeline through a drainage pipeline, and a drainage control valve is arranged on the connection node of the drainage pipeline on the heat return oil pipeline.

[0016] The transfer pump is arranged in the oil collecting tank, and an outlet of the transfer pump is connected to the oil storage tank through a heat return oil flow measurement pipeline.

[0017] According to at least one of the embodiments of the present application, a fireproof hose is arranged on the fuel supply pipeline in the aircraft fuel ground full-mode test system.

[0018] According to at least one of the embodiments of the present application, a liquid level meter is arranged on the oil collecting tank in the aircraft fuel ground full-mode test system.

[0019] According to at least one of the embodiments of the present application, a safety valve is arranged on the oil collecting tank in the aircraft fuel ground full-mode test system.

[0020] According to at least one of the embodiments of the present application, a cooler is arranged on the oil collecting tank in the aircraft fuel ground full-mode test system.

[0021] According to at least one of the embodiments of the present application, the fuel supply pump is arranged at the bottom of the fuel tank in the aircraft fuel ground full-mode test system.

[0022] According to at least one of the embodiments of the present application, the transfer pump is arranged at the bottom of the oil collecting tank in the aircraft fuel ground full-mode test system.

[0023] According to at least one of the embodiments of the present application, the test state switching valve is a hand valve in the aircraft fuel ground full-mode test system.

[0024] According to at least one of the embodiments of the present application, the drainage control valve is a hand valve in the aircraft fuel ground full-mode test system.

[0025] A method for measuring the flow of hot return oil of an aircraft fuel system, which is implemented based on the aircraft fuel ground full-scale test system, comprising:

[0026] Close the test state switching valve, open the flow control valve, connect the hot return oil flow measurement system to the test system, and guide the hot return oil to the oil collecting tank. When the liquid level meter reaches the upper limit, start the transfer pump, and open the servo regulating valve to transfer the oil in the oil collecting tank to the oil storage tank.

[0027] When the hot return oil flow measurement test is stopped, the remaining oil in the oil collecting tank is transferred to the oil storage tank by the transfer pump.

[0028] The amount of oil transferred by the oil collecting tank to the oil storage tank is measured by the turbine flow meter to obtain the hot return oil flow, thereby realizing the measurement of the hot return oil flow.

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

[0030] The aircraft fuel ground full-scale test system and the method for measuring the flow of hot return oil thereof can complete the hot return oil flow measurement test, accurately measure the hot return oil flow, and ensure the effectiveness of the aircraft fuel ground full-scale test without affecting the test of other items. BRIEF DESCRIPTION OF DRAWINGS

[0031] Figure 1 is a schematic diagram of the aircraft fuel ground full-scale test system provided by the present application;

[0032] Among them:

[0033] 1 - fuel tank; 2 - fuel supply pump; 3 - fuel heat exchanger; 4 - hot return oil flow regulating valve; 5 - test state switching valve; 6 - oil collecting tank; 7 - transfer pump; 8 - oil storage tank; 9 - flow control valve; 10 - liquid level meter; 11 - safety valve; 12 - cooler; 13 - servo regulating valve; 14 - turbine flow meter.

[0034] In order to better illustrate the present application, some contents in the drawings may be omitted, enlarged or reduced, and are only used for exemplary description, and cannot be understood as a limitation of the present application. DETAILED DESCRIPTION

[0035] In order to make the technical solutions of the present application and its advantages clearer, the technical solutions of the present application will be further described in detail below with reference to the drawings, and it should be understood that the specific embodiments described herein are only part of the embodiments of the present application, and are only used to explain the present application, but not to limit the present application. It should be noted that, in order to facilitate description, only parts related to the present application are shown in the drawings, and other related parts can be referred to the usual design.

[0036] In addition, unless otherwise defined, technical terms or scientific terms used in the description of the present application shall be understood as the general meaning understood by those of ordinary skill in the art to which the present application belongs. "Include" used in the description of the present application indicates that the concept appearing before the word covers the concepts listed after the word and its equivalents, and does not exclude other associated concepts.

[0037] In addition, the words used to indicate the position in the description of the present application are only used to indicate the relative direction or positional relationship, and when the absolute position of the described object changes, the relative positional relationship may also change accordingly. It should be noted that, unless otherwise specified and limited, "installation", "connection" and similar words used in the description of the present application should be understood in a broad sense, for example, the connection can be fixed connection or detachable connection; can be mechanical connection or electrical connection; can be directly connected or indirectly connected through intermediate medium, and those skilled in the art can understand the specific meaning of the present application according to the specific situation.

[0038] When conducting hot oil return flow measurement test, only the measurement of hot oil return flow is concerned, and the working condition of the rear end of the hot oil return pipeline is not concerned. Based on this, the present application provides an aircraft fuel ground full mode test system, which comprises a test system and a hot oil return flow measurement system, as shown in Figure 1

[0039] The test system is the engine / APU oil supply part in the ground 1:1 simulation aircraft fuel system, which comprises a fuel tank 1, an oil supply pump 2, a fuel heat exchanger 3 and the like.

[0040] The oil supply pump 2 is arranged in the fuel tank 1 and is located at the bottom of the fuel tank 1. The outlet of the oil supply pump 2 is connected to the oil supply pipeline, and the outlet of the oil supply pipeline is divided into the oil supply pipeline and the hot oil return pipeline.

[0041] A fireproof hose is arranged on the oil supply pipeline, and the outlet of the fireproof hose is connected to the engine and the APU, so as to supply oil to the engine and the APU.

[0042] The outlet of the hot oil return pipeline 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 arranged on the hot oil return pipeline in sequence. The test state switching valve 5 is a hand valve.

[0043] The hot oil return flow measurement system comprises an oil collecting tank 6, a transfer pump 7 and an oil storage tank 8.

[0044] The oil collecting tank 6 is connected to the hot oil return pipeline through a drainage pipeline. The connection node of the drainage pipeline on the hot oil return pipeline is between the hot oil return flow regulating valve 4 and the test state switching valve 5. A drainage control valve 9 is arranged on the drainage pipeline, and the drainage control valve 9 is a hand valve.

[0045] A liquid level meter 10 and a safety valve 11 are arranged on the oil collecting tank 6, and a cooler 12 can be arranged in the oil collecting tank 6.​

[0046] The transfer pump 7 is arranged in the oil collecting tank 6 at the bottom of the oil collecting tank 6, is a high-power pump, and the outlet is connected to the oil storage tank 8 through a hot oil flow measuring pipeline, on which a servo adjusting valve 13 and a turbine flowmeter 14 are arranged in sequence.

[0047] When other test items are carried out in the hot oil flow measurement test using the aircraft fuel ground full-mode test system disclosed in the above embodiment, the test state switching valve 5 is opened, the flow control valve 9 is closed, the hot oil flow measurement system is cut off from the tested system, the hot oil flow measurement system does not affect the tested system, and the tested system can be used to well verify the performance of the aircraft fuel system.

[0048] When the hot oil flow measurement test is carried out, the test state switching valve 5 is closed, the flow control valve 9 is opened, the hot oil flow measurement system is connected to the tested system, the hot oil is introduced into the oil collecting tank 6, when the liquid level meter 10 reaches the upper limit, the transfer pump 7 is started, and the servo adjusting valve 13 is opened, the oil in the oil collecting tank 6 is transferred to the oil storage tank 8, when the hot oil flow measurement test is stopped, the remaining oil in the oil collecting tank 6 is transferred to the oil storage tank 8 by the transfer pump 7, the oil volume transferred from the oil collecting tank 6 to the oil storage tank 8 is measured by the turbine flowmeter 14, the hot oil flow is obtained, and the hot oil flow is accurately measured.

[0049] So far, the technical solution of the present application has been described in combination with the preferred embodiments shown in the drawings, and those skilled in the art should understand that the protection scope of the present application is obviously not limited to these specific embodiments, and those skilled in the art can make equivalent changes or replacements to related technical features without deviating from the principles of the present application, and the technical solutions after the changes or replacements will fall within the protection scope of the present 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.

Images