An aero-engine fuel transient icing test oil supply device, test system and test method

Abstract

The present application relates to the technical field of aero-engine fuel transient icing, and particularly relates to a fuel transient icing test oil supply device for aero-engine, a test system and a test method. The fuel transient icing test oil supply device for aero-engine comprises: a test assembly comprising a test oil tank and a test pipeline, the test oil tank containing fuel, and the test oil tank being adapted to be communicated with an engine through the test pipeline; a temperature control assembly comprising a cooling heat exchanger, the cooling heat exchanger being arranged in communication with the test oil tank; and a transient water injection assembly comprising a transient water injection device and a transient water injection pipeline, liquid in the transient water injection device being communicated with the test pipeline through the transient water injection pipeline. The present application provides a fuel transient icing test oil supply device for aero-engine, a test system and a test method, so as to solve the problem that a test device can only meet the steady-state icing test of the fuel system of the aero-engine and cannot meet the transient icing test of the fuel system of the aero-engine.

Description

Technical Field

[0001] This invention relates to the field of transient fuel icing technology for aero-engines, specifically to a fuel supply device, test system, and test method for transient fuel icing testing of aero-engines. Background Technology

[0002] When an aircraft flies in cold environments, the low temperatures can have detrimental effects on its fuel system. This can cause water in the fuel to freeze, clogging fuel filters or screens, leading to reduced or complete interruption of fuel supply to the engine. This can result in engine power loss or stalling, jeopardizing flight safety. During the development of aircraft or engines, fuel icing tests must be conducted strictly according to relevant standards and regulations to verify the system's performance under conditions of water freezing in the fuel at low temperatures.

[0003] Engine fuel system icing tests consist of two parts: steady-state fuel system icing tests and transient fuel system icing tests. Existing fuel supply systems for engine fuel system icing tests typically meet the requirements for conducting steady-state fuel system icing tests. These systems generally consist of a fuel supply system, a storage tank, a test tank, a fuel-water mixing system, a stirring system, and a fuel cooling system. They are capable of preparing saturated and supersaturated water-fuel mixtures, as well as cooling and supplying the prepared water-containing fuel mixture to the engine fuel system.

[0004] The existing test equipment can only meet the requirements for conducting steady-state icing tests of the fuel system of aero engines, but cannot meet the requirements for conducting transient icing tests of the fuel system of aero engines. Summary of the Invention

[0005] This invention provides a fuel supply device, test system, and test method for transient fuel icing test of aero-engines, to solve the problem that existing test devices can only meet the requirements for conducting steady-state fuel system icing tests of aero-engines, but cannot meet the requirements for conducting transient fuel icing tests of aero-engines.

[0006] In a first aspect, the present invention provides a fuel supply device for transient icing test of fuel for aero-engines, comprising: A test assembly, comprising a test fuel tank and a test pipeline, wherein the test fuel tank contains fuel and is adapted to be connected to an engine via the test pipeline; A temperature control component, the temperature control component including a cooling heat exchanger, the cooling heat exchanger being connected to the test oil tank; A transient water injection assembly, comprising a transient water injection device and a transient water injection pipeline, wherein the liquid in the transient water injection device is connected to the test pipeline through the transient water injection pipeline.

[0007] The cooling heat exchanger cools the fuel in the test tank to a preset temperature. The fuel at the preset temperature enters the engine through the test pipeline. The liquid in the transient water injection pipeline mixes with the fuel at the preset temperature in the test pipeline to form a fuel mixture. The water in the fuel mixture freezes to simulate the transient freezing condition of the fuel.

[0008] In one optional embodiment, the temperature control component includes a cold air storage tank, a mixer, a cold air supply pipeline, and a mixed gas supply pipeline. The cold air supply pipeline is provided between the cold air storage tank and the mixer, and the mixed gas supply pipeline is provided between the mixer and the cooling heat exchanger.

[0009] In one optional embodiment, the temperature control component further includes a dry gas storage tank and a dry gas supply pipeline, wherein the dry gas supply pipeline is provided between the dry gas storage tank and the mixer.

[0010] In one optional embodiment, the temperature control component further includes a venting tower, a cold air discharge pipeline, a dry air discharge pipeline, and a mixed gas discharge pipeline. One end of the cold air discharge pipeline is connected to the cold air supply pipeline and the other end is connected to the venting tower. One end of the dry air discharge pipeline is connected to the dry air supply pipeline and the other end is connected to the venting tower. One end of the mixed gas discharge pipeline is connected to the mixer and the other end is connected to the venting tower.

[0011] In one optional embodiment, the temperature control component further includes a temperature regulating heat exchanger, which is connected to the test oil tank and the cooling heat exchanger pipelines respectively.

[0012] In one alternative embodiment, an environmental test chamber is also included, wherein a three-way valve is provided on the test pipeline, and the three-way valve and the engine are located inside the environmental test chamber.

[0013] In one optional embodiment, the test assembly further includes a power pump, a pressure sensor, and a temperature sensor, which are arranged sequentially from the test pipeline toward the three-way valve.

[0014] In one optional embodiment, the system further includes a fuel supply assembly comprising a fuel reservoir and an oil-water separator, wherein the oil-water separator is connected to the test fuel tank and the fuel reservoir, and the fuel reservoir is connected to the engine.

[0015] Secondly, the present invention also provides a test system, including the above-mentioned fuel supply device for transient icing test of fuel for aero-engines.

[0016] Thirdly, the present invention also provides a test method for a fuel supply device for transient icing test of fuel for aircraft engines. A cooling heat exchanger cools the fuel in the test tank to a preset temperature. The fuel at the preset temperature enters the engine through a test pipeline. Liquid in the transient water injection pipeline mixes with the fuel at the preset temperature in the test pipeline to form a fuel mixture. The water in the fuel mixture freezes. Attached Figure Description

[0017] To more clearly illustrate the specific embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of the present invention. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0018] Figure 1 This is a schematic diagram of a fuel supply device for transient icing test of fuel for aircraft engines according to an embodiment of the present invention.

[0019] Explanation of reference numerals in the attached drawings: 1. Test component; 101. Test oil tank; 102. Test pipeline; 103. Antifreeze nozzle; 104. Three-way valve; 105. Power pump; 106. Pressure sensor; 107. Temperature sensor; 108. Return oil pipeline; 2. Engine; 3. Temperature control component; 301. Cooling heat exchanger; 302. Cold air storage tank; 303. Mixer; 304. Cold air supply pipeline; 305. Venting tower; 306. Drying gas storage tank; 307. Drying gas supply pipeline; 308. Drying gas 309. Discharge pipeline; 310. Second regulating control valve; 311. Mixed gas discharge pipeline; 312. Temperature regulating heat exchanger; 313. Second connecting pipeline; 314. Third connecting pipeline; 315. Water supply tank; 316. Water return tank; 317. Water supply pipeline; 318. Mixed gas supply pipeline; 4. Transient water injection assembly; 401. Transient water injection device; 402. Transient water injection pipeline; 5. Environmental test chamber; 6. Oil supply assembly; 601. Oil supply tank; 602. Oil storage tank; 603. Oil-water separator. Detailed Implementation

[0020] To make the objectives, technical solutions, and advantages of the embodiments of the present invention clearer, the technical solutions of the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings. Obviously, the described embodiments are only some embodiments of the present invention, not all embodiments. Based on the embodiments of the present invention, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of the present invention.

[0021] The following is combined Figure 1The following describes embodiments of the present invention.

[0022] According to an embodiment of the present invention, in one aspect, a fuel supply device for a transient icing test of fuel for an aircraft engine 2 is provided, comprising: a test component 1, including a test fuel tank 101 and a test pipeline 102, the test fuel tank 101 containing fuel and adapted to be connected to the engine 2 through the test pipeline 102; a temperature control component 3, including a cooling heat exchanger 301, the cooling heat exchanger 301 being connected to the test fuel tank 101; and a transient water injection component 4, including a transient water injection device 401 and a transient water injection pipeline 402, the transient water injection device 401 being connected to the test pipeline 102 through the transient water injection pipeline 402.

[0023] The cooling heat exchanger 301 cools the fuel in the test fuel tank 101 to a preset temperature. The fuel at the preset temperature enters the engine 2 through the test pipeline 102. The liquid in the transient water injection pipeline 402 mixes with the fuel at the preset temperature in the test pipeline 102 to form a fuel mixture. The water in the fuel mixture freezes to simulate the transient freezing condition of the fuel.

[0024] In one embodiment, such as Figure 1 As shown, the temperature control component 3 includes a cold gas storage tank 302, a mixer 303, a cold gas supply pipeline 304, and a mixed gas supply pipeline 318. The cold gas supply pipeline 304 connects the cold gas storage tank 302 and the mixer 303, while the mixed gas supply pipeline 318 connects the mixer 303 and the cooling heat exchanger 301. The cold gas storage tank 302 stores cooling gas, which is then transported to the mixer 303 via the cold gas supply pipeline 304. The gas in the mixer 303 is then transported to the cooling heat exchanger 301 via the mixed gas supply pipeline 318 for cooling. In this embodiment, the mixed gas supply pipeline 318 is equipped with a pressure sensor 106 and a flow sensor.

[0025] In one embodiment, such as Figure 1As shown, the temperature control component 3 also includes a dry gas storage tank 306 and a dry gas supply pipeline 307. The dry gas supply pipeline 307 is located between the dry gas storage tank 306 and the mixer 303. The dry gas in the dry gas storage tank 306 reaches the mixer 303 via the dryer supply pipeline, allowing the cooling gas and the dryer to mix in the mixer 303 before reaching the cooling heat exchanger 301 for cooling, thereby reducing the preset temperature of the fuel in the test fuel tank 101. It should be noted that the cold gas in the cold gas storage tank 302 and the dry gas in the dry gas storage tank 306 are existing. To control the flow rates of the cold gas supply pipeline 304 and the dry gas supply pipeline 307, a first regulating control valve is installed on the cold gas supply pipeline 304, and a second regulating control valve 309 is installed on the dry gas supply pipeline 307. Specifically, the first regulating control valve and the second regulating control valve 309 are flow control valves.

[0026] In one embodiment, such as Figure 1 As shown, the temperature control component 3 also includes a venting tower 305, a cold air exhaust pipe, a dry air exhaust pipe 308, and a mixed gas exhaust pipe 310. One end of the cold air exhaust pipe is connected to the cold air supply pipe 304, and the other end is connected to the venting tower 305. One end of the dry air exhaust pipe 308 is connected to the dry air supply pipe 307, and the other end is connected to the venting tower 305. One end of the mixed gas exhaust pipe 310 is connected to the mixer 303, and the other end is connected to the venting tower 305. A cold air discharge pipeline is provided to discharge excess cold air from the cold air supply pipeline 304 into the venting tower 305, from which it is released into the air. The connection point between the cold air discharge pipeline and the cold air supply pipeline 304 is located downstream of the first regulating control valve (i.e., the cooling gas first passes through the first regulating control valve before entering the cold air discharge pipeline). A dry gas discharge pipeline 308 is provided to discharge excess dry gas from the dry gas supply pipeline 307 into the venting tower 305, from which it is released into the air. The connection point between the dry gas discharge pipeline 308 and the dry gas supply pipeline 307 is located downstream of the second regulating control valve 309 (i.e., the dry gas first passes through the second regulating control valve 309 before entering the dry gas discharge pipeline 308). A mixed gas discharge pipeline 310 is provided to discharge excess gas from the mixer 303 into the air. It should be noted that the cooling gas and the dry gas in this embodiment are both gases that are harmless to the air environment.

[0027] In this embodiment, as Figure 1 As shown, a third regulating control valve is installed on the cold air discharge pipe, and a fourth regulating control valve is installed on the dry air discharge pipe 308. The third and fourth regulating control valves are flow control valves.

[0028] In one embodiment, such as Figure 1As shown, the temperature control component 3 also includes a temperature-regulating heat exchanger 311, which is connected to the test oil tank 101 and the cooling heat exchanger 301 via pipelines. In this embodiment, as... Figure 1 As shown, a first connecting pipe connects the test fuel tank 101 to the cooling heat exchanger 301, a second connecting pipe 312 connects the cooling heat exchanger 301 to the temperature regulating heat exchanger 311, and a third connecting pipe 313 connects the temperature regulating heat exchanger 311 to the test fuel tank 101. Fuel in the test fuel tank 101 enters the cooling heat exchanger 301 through the first connecting pipe, fuel in the cooling heat exchanger 301 enters the temperature regulating heat exchanger 311 through the second connecting pipe 312, and fuel in the temperature regulating heat exchanger 311 enters the test fuel tank 101 through the third connecting pipe 313. The cooling heat exchanger 301 and the temperature regulating heat exchanger 311 are used to exchange heat with the fuel to reduce the fuel temperature. It should be noted that the cooling heat exchanger 301 and the temperature regulating heat exchanger 311 can independently reduce the fuel in the test tank 101 to the preset temperature required for the test, or they can work together to reduce the fuel in the test tank 101 to the preset temperature required for the test. Figure 1 As shown, a temperature sensor 107 is installed on the first connecting pipe.

[0029] In this embodiment, as Figure 1 As shown, the temperature control component 3 also includes a water supply tank 314, a water return tank 315, a water supply pipe 316, and a water return pipe 317. The water supply pipe 316 connects the water supply tank 314 and the inlet of the temperature regulating heat exchanger 311, and the water return pipe 317 connects the water return tank 315 and the return of the temperature regulating heat exchanger 311 to supply cooling water to the temperature regulating heat exchanger 311.

[0030] In one embodiment, such as Figure 1 As shown, it also includes an environmental test chamber 5. A three-way valve 104 is installed on the test pipeline 102. The three-way valve 104 and the engine 2 are located inside the environmental test chamber 5, which simulates test conditions. It should be noted that a return oil pipeline 108 is provided between the three-way valve 104 and the test oil tank 101 to facilitate the return of a portion of the fuel to the test oil tank 101.

[0031] In one embodiment, such as Figure 1 As shown, the test assembly 1 also includes a power pump 105, a pressure sensor 106, and a temperature sensor 107. The power pump 105, pressure sensor 106, and temperature sensor 107 are arranged sequentially from the test pipeline 102 toward the three-way valve 104. The power pump 105 provides power for the movement of fuel in the test pipeline 102, and the pressure sensor 106 and temperature sensor 107 monitor the movement state of fuel in the test pipeline 102.

[0032] In this embodiment, as Figure 1 As shown, the test pipeline 102 is also equipped with an antifreeze nozzle 103. The antifreeze nozzle 103 is located between the power pump 105 and the pressure sensor 106. The antifreeze nozzle 103 is connected to the transient water supply pipeline 316, so that the pure water or oil-water mixture in the transient water injection device 401 reaches the antifreeze nozzle 103 through the transient water supply pipeline 316 and mixes with the fuel.

[0033] In one embodiment, such as Figure 1 As shown, it also includes a fuel supply assembly 6, which includes a fuel tank 602 and an oil-water separator 603. The oil-water separator 603 is connected to the test fuel tank 101 and the fuel tank 602 respectively. The fuel tank 602 is connected to the engine 2. Excess fuel from the engine 2 will flow into the fuel tank 602. The fuel in the fuel tank 602 will be separated into gas by the oil-water separator 603 and then enter the test fuel tank 101.

[0034] In this embodiment, as Figure 1 As shown, the fuel supply assembly 6 also includes a fuel supply tank 601, which is connected to the fuel storage tank 602 via a pipeline, and the fuel supply tank 601 provides fuel to the fuel storage tank 602.

[0035] According to an embodiment of the present invention, another aspect provides a test system including the above-described fuel supply device for transient icing test of fuel for aircraft engine 2.

[0036] A test method for a fuel supply device for transient icing testing of fuel for an aircraft engine 2 includes the following steps: (1) Before the transient icing test of fuel, the fuel in the test fuel tank 101 enters the cooling heat exchanger 301 through the first connecting pipe. The dry gas in the dry gas storage tank 306 enters the mixer 303 through the dry gas supply pipe 307. The cooling gas in the cold gas storage tank 302 enters the mixer 303 through the cold gas supply pipe 304. The dry gas and cooling gas are mixed in the mixer 303 in a preset ratio and then enter the cooling heat exchanger 301 through the mixed gas supply pipe 318 to exchange heat with the fuel to reduce the temperature of the fuel. The cooled fuel enters the temperature regulating heat exchanger 311 through the second connecting pipe 312. The cooling water in the water supply tank 314 flows into the temperature regulating heat exchanger 311 through the water supply pipe 316. The cooling water exchanges heat with the fuel to further reduce the temperature of the fuel, so that the temperature of the fuel entering the third connecting pipe 313 is the preset test temperature, until the temperature of the fuel in the test fuel tank 101 reaches the preset temperature (the preset temperature is below 0℃). (2) During the transient icing test of fuel, the power pump 105 provides power, and the fuel at the preset temperature in the test fuel tank 101 enters the antifreeze nozzle 103 through the test pipeline 102. At the same time, the pure water or oil-water mixture in the transient water injection device 401 reaches the antifreeze nozzle 103 through the transient water injection pipeline 402 to mix with the fuel to form a fuel mixture. The water in the fuel mixture freezes to simulate the freezing form and effect of water-containing fuel under real working conditions.

[0037] Throughout the test, the flow rate was controlled by the first regulating control valve, the second regulating control valve 309, and the three-way valve 104, while the pressure sensor 106 and the temperature sensor 107 provided real-time feedback of relevant information to ensure that the test parameters met the test requirements.

[0038] The fuel supply device for transient icing test of aero-engine 2 provided by the present invention has the following advantages: (1) The cooling heat exchanger 301 cools the fuel in the test fuel tank 101 to a preset temperature. The fuel at the preset temperature enters the engine 2 through the test pipeline 102. The liquid in the transient water injection pipeline 402 mixes with the fuel at the preset temperature in the test pipeline 102 to form a fuel mixture. The water in the fuel mixture freezes to simulate the transient icing condition of the fuel. (2) The existing dry air source, cold air source and circulating cooling water of the test bench are used to cool and regulate the temperature of the fuel, which improves the efficiency of the existing equipment and energy of the test bench, simplifies the device structure and reduces the system purchase cost. (3) The low-temperature cold air after mixing dry gas and cold air is used to cool the fuel. The temperature and flow rate of the mixed low-temperature cold air can be accurately controlled to perform initial cooling and temperature control of the fuel. The circulating cooling water heat exchange is used to further control the temperature of the fuel. By adjusting the flow rate of the circulating cooling water in real time, the fuel temperature can be accurately controlled. It can cool quickly and has high temperature control accuracy.

[0039] Although embodiments of the invention have been described in conjunction with the accompanying drawings, those skilled in the art can make various modifications and variations without departing from the spirit and scope of the invention, and such modifications and variations all fall within the scope defined by the appended claims.

Claims

1. A fuel supply device for transient icing test of fuel for aero-engines, characterized in that, include: Test assembly (1), the test assembly (1) includes a test fuel tank (101) and a test pipeline (102), the test fuel tank (101) contains fuel, and the test fuel tank (101) is adapted to be connected to the engine (2) through the test pipeline (102); Temperature control component (3), the temperature control component (3) includes a cooling heat exchanger (301), the cooling heat exchanger (301) is connected to the test oil tank (101); Transient water injection assembly (4), the transient water injection assembly (4) includes a transient water injection device (401) and a transient water injection pipeline (402), the liquid in the transient water injection device (401) is connected to the test pipeline (102) through the transient water injection pipeline (402); The temperature control component (3) includes a cold air storage tank (302), a mixer (303), a cold air supply pipeline (304), and a mixed gas supply pipeline (318). The cold air supply pipeline (304) is provided between the cold air storage tank (302) and the mixer (303), and the mixed gas supply pipeline (318) is provided between the mixer (303) and the cooling heat exchanger (301).

2. The fuel supply device for transient icing test of aero-engine fuel according to claim 1, characterized in that, The temperature control component (3) also includes a dry gas storage tank (306) and a dry gas supply pipeline (307), with the dry gas supply pipeline (307) provided between the dry gas storage tank (306) and the mixer (303).

3. The fuel supply device for transient icing test of aero-engine fuel according to claim 2, characterized in that, The temperature control component (3) further includes a venting tower (305), a cold air discharge pipeline, a dry air discharge pipeline (308), and a mixed gas discharge pipeline (310). One end of the cold air discharge pipeline is connected to the cold air supply pipeline (304), and the other end is connected to the venting tower (305). One end of the dry air discharge pipeline (308) is connected to the dry air supply pipeline (307), and the other end is connected to the venting tower (305). One end of the mixed gas discharge pipeline (310) is connected to the mixer (303), and the other end is connected to the venting tower (305).

4. The fuel supply device for transient icing test of aero-engine fuel according to any one of claims 1-3, characterized in that, The temperature control component (3) also includes a temperature regulating heat exchanger (311), which is connected to the test oil tank (101) and the cooling heat exchanger (301) respectively.

5. The fuel supply device for transient icing test of aero-engine fuel according to claim 4, characterized in that, It also includes an environmental test chamber (5), on which a three-way valve (104) is provided. The three-way valve (104) and the engine (2) are located inside the environmental test chamber (5).

6. The fuel supply device for transient icing test of aero-engine fuel according to claim 5, characterized in that, The test assembly (1) also includes a power pump (105), a pressure sensor (106) and a temperature sensor (107), which are arranged sequentially from the test pipeline (102) toward the three-way valve (104).

7. The fuel supply device for transient icing test of aero-engine fuel according to claim 1, characterized in that, It also includes a fuel supply assembly (6), which includes a fuel tank (602) and an oil-water separator (603). The oil-water separator (603) is connected to the test fuel tank (101) and the fuel tank (602) respectively. The fuel tank (602) is connected to the engine (2).

8. A testing system, characterized in that, Includes the fuel supply device for transient icing test of fuel for aero-engine (2) as described in any one of claims 1-7.

9. A test method for a fuel supply device for transient icing testing of aero-engines, used with the fuel supply device for transient icing testing of aero-engines as described in claim 1, characterized in that, The cooling heat exchanger (301) cools the fuel in the test oil tank (101) to a preset temperature. The fuel at the preset temperature enters the engine (2) through the test pipeline (102). The liquid in the transient water injection pipeline (402) mixes with the fuel at the preset temperature in the test pipeline (102) to form a fuel mixture. The water in the fuel mixture freezes.

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