Freezing test device and test method for aero-engine fuel system

Abstract

The invention relates to an aeroengine fuel system icing test device and test method. The icing test device for the aero-engine fuel system comprises a supercooled water manufacturing unit used for generating liquid water at a set temperature; the supercooled water and fuel oil collision unit is used for injecting the liquid water with the set temperature into the fuel oil to generate water-containing fuel oil or ice-containing fuel oil; the fuel oil storage unit is used for storing fuel oil; the circulation control and heat exchange unit is used for heating and cooling the fuel oil in the fuel oil storage unit; and the jet pump is connected with the circulation control and heat exchange unit and the supercooled water and fuel collision unit through a fuel pipeline, the jet pump is connected into an inlet pipeline of the engine, and the jet pump is used for sucking water-containing fuel or ice-containing fuel in the fuel pipeline into the inlet pipeline of the engine. The invention provides an aeroengine fuel system icing test device and a test method, which can realize transient icing verification and steady icing verification.

Description

Technical Field

[0001] The invention relates to the field of engine fuel system testing, and in particular to an icing test device and a test method for an aviation engine fuel system. Background Art

[0002] The aircraft engine fuel system will encounter water contamination operating conditions under the expected atmospheric conditions. The most severe water contamination condition is usually water freezing. Ice may block tiny pipes in the fuel supply system such as fuel filters, valves and other components, affecting fuel flow. In severe cases, it may cause the engine to shut down. At the same time, the airworthiness clause CCAR 33.67(b)(4)(ii) stipulates the fuel icing verification requirements. In order to demonstrate the requirements of the corresponding airworthiness clauses, fuel system icing tests are generally carried out. Therefore, there is a need for an aircraft engine fuel system icing test device that can meet the requirements of verifying the normal operation of the engine fuel system in a real icing environment (including steady-state fuel icing environment and transient fuel icing environment).

[0003] For the fuel system icing test, the existing scheme focuses on the steady-state icing verification test device of the fuel system, lacks a special test device for transient icing verification of the fuel system, and to achieve transient icing verification, the transient icing conditions of the fuel system are usually simulated by running the typical cycle of the engine. However, this scheme requires the establishment of a complete original test pipeline from the aircraft to the engine, and the engine needs to be operated for a long time to obtain a transient icing environment. Moreover, the transient icing test conditions are difficult to simulate, and it is necessary to comprehensively consider the coupling of multiple factors such as fuel flow, fuel temperature, specific pipeline structure, external temperature changes, vibration, etc., and the simulated transient icing environment may not meet the requirements of the authority. At the same time, it is difficult for the existing test schemes to achieve steady-state icing verification and transient icing verification at the same time. In addition, the existing schemes for test fuel configuration are usually offline water distribution methods or methods of mixing oil and liquid first and then directly injecting them into the engine inlet pipeline. Both of them cannot ensure that water is evenly distributed in the fuel, resulting in unreliable test results. Summary of the invention

[0004] In view of the above problems in the prior art, the present invention proposes an icing test device and a test method for an aircraft engine fuel system, which can realize transient icing verification and steady-state icing verification.

[0005] Specifically, the present invention proposes an aircraft engine fuel system icing test device, comprising:

[0006] A supercooled water production unit for generating liquid water at a set temperature;

[0007] A supercooled water and fuel collision unit, used for injecting the liquid water of the set temperature into the fuel to generate water-containing fuel or ice-containing fuel;

[0008] A fuel storage unit, used for storing fuel, wherein the fuel storage unit and the supercooled water and fuel collision unit are connected via a fuel pipeline;

[0009] A circulation control and heat exchange unit is connected to the fuel storage unit through a fuel pipeline, and the circulation control and heat exchange unit is used to increase or decrease the temperature of the fuel in the fuel storage unit;

[0010] The priming pump is connected to the circulation control and heat exchange unit and the supercooled water and fuel collision unit through the fuel pipeline respectively. The priming pump is connected to the inlet pipeline of the engine. The priming pump is used to suck the water-containing fuel or ice-containing fuel in the fuel pipeline into the inlet pipeline of the engine.

[0011] According to one embodiment of the present invention, the supercooled water manufacturing unit includes a temperature control system, a constant temperature box and a water storage device, the temperature control system is used to control the temperature of the constant temperature box, the water storage device is arranged in the constant temperature box, and the bottom of the water storage device is connected to the supercooled water and fuel collision unit through a first fuel pipeline.

[0012] According to one embodiment of the present invention, the supercooled water production unit further comprises a first temperature sensor for measuring the temperature of the thermostat or the water storage device, and the temperature control system controls the temperature of the thermostat based on the first temperature sensor;

[0013] The first fuel pipeline is a downwardly expanding pipeline, and a first valve is provided on the first fuel pipeline.

[0014] According to one embodiment of the present invention, the supercooled water and fuel collision unit includes a fuel storage tank and an agitator disposed on the fuel storage tank, wherein the agitator is used to fully mix the fuel and liquid water.

[0015] According to one embodiment of the present invention, the supercooled water and fuel collision unit also includes a first refueling port and an observation window, wherein the first refueling port is arranged at the top of the fuel storage tank, and the observation window is arranged on the fuel storage tank. The bottom of the fuel storage tank is connected to the ejection pump through a second fuel pipeline, and a second valve and a third valve are arranged on the second fuel pipeline. The second valve is used to control the injection of water-containing fuel or ice-containing fuel in the fuel storage tank into the second fuel pipeline, and the third valve is used to control the injection of water-containing fuel or ice-containing fuel in the second fuel pipeline into the ejection pump.

[0016] According to an embodiment of the present invention, an ice collection unit is further provided in the second fuel pipeline, and the ice collection unit is arranged between the third valve and the ejector pump.

[0017] According to one embodiment of the present invention, the fuel storage unit includes a fuel storage tank, on which a sampling port, a second temperature sensor and a second refueling port are provided, the second temperature sensor is used to measure the temperature inside the fuel storage tank, and the sampling port and the second refueling port are respectively arranged at the bottom and the top of the fuel storage tank.

[0018] According to one embodiment of the present invention, a fuel inlet is provided on the fuel storage tank, and the fuel storage tank is connected to the second fuel pipeline through a third fuel pipeline, one end of the third fuel pipeline is connected to the fuel inlet, and the other end is connected to the second fuel pipeline and is located between the second valve and the third valve, and a fourth valve is provided on the third fuel pipeline.

[0019] According to one embodiment of the present invention, the fuel storage tank is further provided with a delivery port and a return port, the circulation control and heat exchange unit is connected to the delivery port and the return port through a fourth fuel pipeline to form a circulating fuel passage, and a heat exchanger is provided on the fourth fuel pipeline;

[0020] A fifth valve and a power pump are provided on the fuel pipeline between the heat exchanger and the return port, the fifth valve is arranged between the return port and the power pump, and a sixth valve is provided on the fuel pipeline between the heat exchanger and the delivery port.

[0021] According to one embodiment of the present invention, the circulation control and heat exchange unit also includes a fuel bypass, one end of which is connected to the fuel pipeline between the heat exchanger and the power pump, and the other end is connected to the fuel pipeline between the sixth valve and the return port, and a seventh valve is provided on the fuel bypass.

[0022] According to one embodiment of the present invention, the circulation control and heat exchange unit is connected to the ejector pump through a fifth fuel pipeline, one end of the fifth fuel pipeline is connected to the fourth fuel channel and is located between the fifth valve and the power pump, and the other end is connected to the ejector pump, and an eighth valve is provided on the fifth fuel pipeline.

[0023] According to one embodiment of the present invention, a ninth valve and a flow meter are provided on the inlet pipeline of the engine.

[0024] The present invention also provides an aircraft engine fuel system icing test method, which is applicable to the aforementioned aircraft engine fuel system icing test device, including a transient icing test, comprising the steps of:

[0025] S1, adjusting the temperature of the fuel stored in the fuel storage unit to reach a first set temperature through a circulation control and a heat exchange unit;

[0026] S2, the supercooled water production unit generates supercooled water of a set temperature, and injects a set amount of supercooled water into the supercooled water and fuel collision unit storing fuel;

[0027] S3, the fuel in the fuel storage unit is delivered to the ejector pump through the circulation control and heat exchange unit, and the fuel containing supercooled water is delivered to the ejector pump through the supercooled water and fuel collision unit, and the supercooled water forms ice and enters the inlet pipeline of the engine through the ejector pump along with the fuel;

[0028] S4, the engine operates under the most severe transient icing condition and monitors relevant operating parameters of the engine.

[0029] According to one embodiment of the present invention, the aviation engine fuel system icing test method further includes a steady-state icing test, comprising the steps of:

[0030] T1, adjusting the temperature of the fuel stored in the fuel storage unit to reach a second set temperature through the circulation control and heat exchange unit;

[0031] T2, the supercooled water production unit generates liquid water of a set temperature and injects it into the supercooled water and fuel collision unit, the supercooled water and fuel collision unit fully mixes the liquid water and fuel into an oil-water emulsion, and the supercooled water and fuel collision unit transports the oil-water emulsion with a set water content to the fuel storage unit through the fuel pipeline;

[0032] T3, circulating and cooling the fuel containing the oil-water emulsion stored in the fuel storage unit through the circulation control and heat exchange unit to reach a third set temperature;

[0033] T4, transporting the water-containing fuel in the fuel storage unit to the ejector pump through the circulation control and heat exchange unit, and entering the inlet pipeline of the engine through the ejector pump;

[0034] T5, the engine operates in the most severe steady-state icing condition, and monitors relevant operating parameters of the engine.

[0035] According to one embodiment of the present invention, in step T2, the liquid water and fuel are stirred and fully mixed into an oil-water emulsion.

[0036] The invention provides an icing test device for an aircraft engine fuel system, in which a supercooled water manufacturing unit and a supercooled water and fuel collision unit are designed to provide a transient ice generation environment, thereby realizing transient icing verification and steady-state icing verification.

[0037] It is to be understood that both the foregoing general description and the following detailed description of the present invention are exemplary and explanatory and are intended to provide further explanation of the invention as described. BRIEF DESCRIPTION OF THE DRAWINGS

[0038] The accompanying drawings are included to provide a further understanding of the present invention and are incorporated in and constitute a part of this application. The accompanying drawings illustrate embodiments of the present invention and together with the description serve to explain the principle of the present invention.

[0039] In the attached figure:

[0040] Figure 1 A schematic structural diagram of an aircraft engine fuel system icing test device according to an embodiment of the present invention is shown.

[0041] Figure 2 A flowchart of a transient icing test of an icing test device for an aircraft engine fuel system according to an embodiment of the present invention is shown.

[0042] Figure 3 A flowchart of a steady-state icing test of an icing test device for an aircraft engine fuel system according to an embodiment of the present invention is shown.

[0043] The above drawings include the following reference numerals:

[0044] Supercooled water production unit 100

[0045] Supercooled water and fuel collision unit 200

[0046] Fuel storage unit 300

[0047] Cycle Control and Heat Exchange Unit 400

[0048] Ejector Pump 500

[0049] Engine 600

[0050] Temperature Control Systems 101

[0051] Constant temperature box 102

[0052] Water storage device 103

[0053] First fuel line 104

[0054] First temperature sensor 105

[0055] First valve 106

[0056] Oil tank 201

[0057] Mixer 202

[0058] First refueling port 203 Observation window 204 Second fuel line 205

[0059] Second valve 206

[0060] The third valve 207 Ice collection unit 208 Fuel storage tank 301 Sampling port 302 Second temperature sensor 303

[0061] Second fuel filler port 304 Oil inlet 305 The third fuel line 306

[0062] Fourth valve 307 Delivery port 308 Return port 309 Fourth fuel line 401 Heat exchanger 402

[0063] Fifth valve 403 Power Pump 404

[0064] The sixth valve 405 Fuel Bypass 406

[0065] Seventh Valve 407 Fifth fuel line 408

[0066] The eighth valve 409 Inlet pipeline 601

[0067] Ninth Valve 602 Flow meter 603 DETAILED DESCRIPTION

[0068] It should be noted that, in the absence of conflict, the embodiments and features in the embodiments of the present application may be combined with each other.

[0069] The technical solutions 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 only a part of the embodiments of the present application, rather than all of the embodiments. The following description of at least one exemplary embodiment is actually merely illustrative and is by no means intended to limit the present application and its application or use. 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.

[0070] It should be noted that the terms used herein are only for describing specific embodiments and are not intended to limit the exemplary embodiments according to the present application. As used herein, unless the context clearly indicates otherwise, the singular form is also intended to include the plural form. In addition, it should be understood that when the terms "comprise" and / or "include" are used in this specification, it indicates the presence of features, steps, operations, devices, components and / or combinations thereof.

[0071] Unless otherwise specifically stated, the relative arrangement, numerical expressions and numerical values ​​of the parts and steps set forth in these embodiments do not limit the scope of the present application. At the same time, it should be understood that, for ease of description, the sizes of the various parts shown in the accompanying drawings are not drawn according to the actual proportional relationship. The technology, method and equipment known to those of ordinary skill in the relevant field may not be discussed in detail, but in appropriate cases, the technology, method and equipment should be considered as a part of the authorization specification. In all examples shown and discussed here, any specific value should be interpreted as being merely exemplary, rather than as a limitation. Therefore, other examples of exemplary embodiments may have different values. It should be noted that similar reference numerals and letters represent similar items in the following drawings, so that once a certain item is defined in an accompanying drawing, it does not need to be further discussed in subsequent drawings.

[0072] In the description of the present application, it should be understood that the directions or positional relationships indicated by directional words such as "front, back, up, down, left, right", "lateral, vertical, perpendicular, horizontal" and "top, bottom" are usually based on the directions or positional relationships shown in the drawings, and are only for the convenience of describing the present application and simplifying the description. Unless otherwise specified, these directional words do not indicate or imply that the device or element referred to must have a specific direction or be constructed and operated in a specific direction, and therefore cannot be understood as limiting the scope of protection of the present application; the directional words "inside and outside" refer to the inside and outside relative to the contours of each component itself.

[0073] For ease of description, spatially relative terms such as "above", "above", "on the upper surface of", "above", etc. may be used herein to describe the spatial positional relationship between a device or feature and other devices or features as shown in the figure. It should be understood that spatially relative terms are intended to include different orientations of the device in use or operation in addition to the orientation described in the figure. For example, if the device in the accompanying drawings is inverted, the device described as "above other devices or structures" or "above other devices or structures" will be positioned as "below other devices or structures" or "below other devices or structures". Thus, the exemplary term "above" may include both "above" and "below". The device may also be positioned in other different ways, rotated 90 degrees or in other orientations, and the spatially relative descriptions used herein are interpreted accordingly.

[0074] In addition, it should be noted that the use of words such as "first" and "second" to define components is only for the convenience of distinguishing the corresponding components. If not otherwise stated, the above words have no special meaning and cannot be understood as limiting the scope of protection of this application. In addition, although the terms used in this application are selected from well-known and commonly used terms, some terms mentioned in the specification of this application may be selected by the applicant at his or her discretion, and their detailed meanings are explained in the relevant parts of the description of this article. In addition, it is required to understand this application not only by the actual terms used, but also by the meaning implied by each term.

[0075] Figure 1 The structure diagram of an aircraft engine fuel system icing test device according to an embodiment of the present invention is shown. As shown in the figure, an aircraft engine fuel system icing test device mainly includes a supercooled water production unit 100, a supercooled water and fuel collision unit 200, a fuel storage unit 300, a circulation control and heat exchange unit 400, and an ejector pump 500.

[0076] The supercooled water production unit 100 is used to generate liquid water of a set temperature. Liquid water includes supercooled water, that is, water that remains liquid at a temperature below zero degrees.

[0077] The supercooled water and fuel collision unit 200 is used to inject the liquid water generated by the supercooled water production unit 100 into the fuel to generate the fuel containing liquid water.

[0078] The fuel storage unit 300 is used to store fuel. The fuel storage unit 300 and the supercooled water and fuel collision unit 200 are connected through a fuel pipeline.

[0079] The circulation control and heat exchange unit 400 is connected to the fuel storage unit 300 through a fuel pipeline. The circulation control and heat exchange unit 400 is used to increase or decrease the temperature of the fuel in the fuel storage unit 300 so that the fuel reaches a set temperature that meets the test conditions.

[0080] The priming pump 500 is connected to the circulation control and heat exchange unit 400 and the supercooled water and fuel collision unit 200 through the fuel pipeline. The priming pump 500 is connected to the inlet pipeline 601 of the engine 600. The priming pump 500 is used to suck the water-containing fuel or ice-containing fuel in the fuel pipeline into the inlet pipeline 601 of the engine 600 to ensure that the fuel can effectively enter the pipeline at the inlet of the engine 600 without causing backflow. It should be noted that the engine 600 is a test piece.

[0081] The present invention provides an icing test device for an aircraft engine fuel system, which can realize transient icing verification and steady-state icing verification. During the transient icing verification process, the supercooled water and fuel collision unit 200 injects the supercooled water generated by the supercooled water manufacturing unit 100 into the fuel to generate fuel containing supercooled water. The fuel stored in the fuel storage unit 300 is temperature-controlled to reach a set temperature through the circulation control and heat exchange unit 400. The fuel containing supercooled water in the supercooled water and fuel collision unit 200 and the fuel in the fuel storage unit 300 are transported to the ejector pump 500 through the fuel pipeline, and flow into the inlet pipeline 601 of the engine 600 through the ejector pump 500, thereby simulating the transient icing environment of the fuel. During the steady-state icing verification process, the supercooled water and fuel collision unit 200 injects the liquid water generated by the liquid water manufacturing unit into the fuel to generate water-containing fuel. The water-containing fuel is injected into the fuel storage unit 300 through the fuel pipeline. Next, the water-containing fuel stored in the fuel storage unit 300 is temperature-controlled to reach a set temperature through the circulation control and heat exchange unit 400. Finally, the water-containing fuel in the fuel storage unit 300 is transported to the ejector pump 500 through the circulation control and heat exchange unit 400, and flows into the inlet pipe 601 of the engine 600 through the ejector pump 500.

[0082] Preferably, the supercooled water manufacturing unit 100 includes a temperature control system 101, a thermostat 102 and a water storage device 103. The temperature control system 101 is used to control the temperature of the liquid water in the thermostat 102. The supercooled water manufacturing unit 100 can use cooling equipment such as liquid nitrogen to reduce the water temperature so that the water is kept at the supercooled water temperature or other set temperature. The water storage device 103 is arranged in the thermostat 102, and the water storage device 103 is wrapped by the thermostat 102. Distilled water or water with higher purity can be cooled down in the thermostat 102 to become supercooled water. The water storage device 103 provides the amount of water required for the test. The water temperature in the water storage device 103 is consistent with the temperature of the thermostat 102. The bottom of the water storage device 103 is connected to the supercooled water and fuel collision unit 200 through the first fuel pipeline 104.

[0083] Preferably, the supercooled water manufacturing unit 100 further includes a first temperature sensor 105 for measuring the temperature of the thermostat 102 or the water storage device 103. The temperature control system 101 controls the temperature of the thermostat 102 based on the first temperature sensor 105. A first valve 106 is provided on the first fuel pipeline 104. The first valve 106 is close to the bottom of the water storage device 103. The first valve 106 is used to control the liquid water in the water storage device 103 to enter the first fuel pipeline 104. The first fuel pipeline 104 is a downwardly expanded pipeline. It is ensured that once the first valve 106 is opened, the liquid water will directly reach the supercooled water and fuel collision unit 200, and will not contact the pipe wall of the first fuel pipeline 104 during the process, which can effectively prevent the supercooled water from accumulating into ice in the first fuel pipeline 104.

[0084] Preferably, the supercooled water and fuel collision unit 200 includes a fuel tank 201 and a stirrer 202 disposed on the fuel tank 201. The stirrer 202 is used to fully mix the fuel and liquid water. As an example and not a limitation, the stirrer 202 can be an ultrasonic generator. More preferably, the fuel tank 201 is used to store fuel, and the fuel tank 201 is in a convergent shape from the top to the bottom, such as an inverted cone shape. The convergent shape of the fuel tank 201 can ensure that the water-containing fuel or the ice-containing fuel can be completely delivered to the bottom of the fuel tank 201 when transporting downward.

[0085] Preferably, the supercooled water and fuel collision unit 200 further includes a first refueling port 203 and an observation window 204. The first refueling port 203 is arranged at the top of the fuel tank 201, and is used to fill the fuel tank 201 with ordinary engine fuel. The observation window 204 is arranged on the fuel tank 201, which is convenient for the staff to observe the freezing of the fuel inside the fuel tank 201. In this embodiment, the observation window 204 is arranged at the top of the fuel tank 201 for easy observation. The bottom of the fuel tank 201 is connected to the priming pump 500 through the second fuel pipeline 205. A second valve 206 and a third valve 207 are arranged on the second fuel pipeline 205, and the second valve 206 is used to control the injection of the water-containing fuel or ice-containing fuel in the fuel tank 201 into the second fuel pipeline 205, and the third valve 207 is used to control the injection of the water-containing fuel or ice-containing fuel in the second fuel pipeline 205 into the priming pump 500.

[0086] Preferably, an ice collecting unit 208 is further provided in the second fuel pipeline 205. The ice collecting unit 208 is provided between the third valve 207 and the ejector pump 500, and is used to collect ice in the fuel. The ice collecting unit 208 may be a detachable filter, and after being detached, the fuel flow from the second fuel pipeline 205 to the ejector pump 500 is not affected.

[0087] Preferably, the fuel storage unit 300 includes a fuel storage tank 301, on which a sampling port 302, a second temperature sensor 303, and a second refueling port 304 are provided. The second temperature sensor 303 is used to measure the temperature in the fuel storage tank 301, and the sampling port 302 and the second refueling port 304 are respectively provided at the bottom and the top of the fuel storage tank 301. A staff member can extract a fuel sample through the sampling port 302 to analyze the water content in the fuel. The second refueling port 304 is used to refuel the fuel storage tank 301 with ordinary engine fuel.

[0088] Preferably, the fuel storage tank 301 is provided with an oil inlet 305. The fuel storage tank 301 is connected to the second fuel pipeline 205 through the third fuel pipeline 306. One end of the third fuel pipeline 306 is connected to the oil inlet 305, and the other end is connected to the second fuel pipeline 205 and is located between the second valve 206 and the third valve 207. A fourth valve 307 is provided on the third fuel pipeline 306. By opening the second valve 206 and the fourth valve 307 and closing the third valve 207, the water-containing fuel in the supercooled water and fuel collision unit 200 can be injected into the fuel storage tank 301.

[0089] Preferably, the fuel storage tank 301 is also provided with a delivery port 308 and a return port 309. The circulation control and heat exchange unit 400 connects the delivery port 308 and the return port 309 through the fourth fuel pipeline 401 to form a circulating fuel passage. In this example, the delivery port 308 is arranged on the side wall of the fuel storage tank 301 and close to the bottom, and the return port 309 is arranged on the top of the fuel storage tank 301. A heat exchanger 402 is arranged on the fourth fuel pipeline 401. The heat exchanger 402 adjusts the temperature of the fuel in the fuel storage tank 301 through the circulating fuel passage, and increases or decreases the temperature based on the temperature measured by the second temperature sensor 303. By way of example and not limitation, the heat exchanger 402 can heat the fuel by exchanging heat with hot lubricating oil, and can reduce the temperature by a compressor / liquid nitrogen. Furthermore, a fifth valve 403 and a power pump 404 are provided on the fuel pipeline between the heat exchanger 402 and the return port 309, and the fifth valve 403 is provided between the return port 309 and the power pump 404. The power pump 404 provides power for fuel delivery, and the power pump 404 can be a gear pump. The fifth valve 403 and the power pump 404 are started, so that the fuel in the fuel pipeline is returned to the fuel storage tank 301 through the fifth valve 403 and the return port 309. A sixth valve 405 is provided on the fuel pipeline between the heat exchanger 402 and the delivery port 308. The sixth valve 405, the fifth valve 403 and the power pump 404 are opened, and the fuel output from the delivery port 308 of the fuel storage tank 301 passes through the heat exchanger 402 and returns to the fuel storage tank 301 from the return port 309.

[0090] Preferably, the circulation control and heat exchange unit 400 further includes a fuel bypass 406, which is connected in parallel to the fourth fuel pipeline 401. One end of the fuel bypass 406 is connected to the fuel pipeline between the heat exchanger 402 and the power pump 404, and the other end is connected to the fuel pipeline between the sixth valve 405 and the return port 309. A seventh valve 407 is provided on the fuel bypass 406. The purpose of setting the fuel bypass 406 is that when the fuel in the fuel storage tank 301 reaches a set temperature, the fuel does not need to pass through the heat exchanger 402, and the fuel can flow through the fuel bypass 406 for fuel circulation or be delivered to the priming pump 500 through the fuel bypass 406.

[0091] Preferably, the circulation control and heat exchange unit 400 is connected to the ejector pump 500 through the fifth fuel pipeline 408. One end of the fifth fuel pipeline 408 is connected to the fourth fuel channel 401 and is located between the fifth valve 403 and the power pump 404, and the other end is connected to the ejector pump 500. An eighth valve 409 is provided on the fifth fuel pipeline 408. It is easy to understand that the fifth valve 403, the sixth valve 405, and the power pump 404 are opened, and the seventh valve 407 and the eighth valve 409 are closed, and the fuel is circulated through the heat exchanger 402. The fifth valve 403, the seventh valve 407, and the power pump 404 are opened, and the sixth valve 405 and the eighth valve 409 are closed, and the fuel is circulated through the fuel bypass 406. The seventh valve 407, the eighth valve 409, and the power pump 404 are opened, and the fifth valve 403 and the sixth valve 405 are closed, and the fuel is delivered to the ejector pump 500 through the fuel bypass 406 and the fourth fuel channel 401.

[0092] Preferably, a ninth valve 602 and a flow meter 603 are provided on the inlet pipe 601 of the engine 600. The ninth valve 602 is opened, and the fuel containing water or ice enters the engine 600 through the ejector pump 500. The flow meter 603 is used to monitor the fuel flow rate flowing into the engine 600.

[0093] Figure 2 A flowchart of a transient icing test of an aircraft engine fuel system icing test device according to an embodiment of the present invention is shown. As shown in the figure, the present invention also provides an aircraft engine fuel system icing test method, which is applicable to the aforementioned aircraft engine fuel system icing test device. The test method includes a transient icing test, comprising the steps of:

[0094] S1, the temperature of the fuel stored in the fuel storage unit 300 is adjusted to reach the first set temperature through the circulation control and heat exchange unit 400. Specifically, the required fuel is injected into the fuel storage tank 301 through the second refueling port 304, the fifth valve 403, the sixth valve 405, and the power pump 404 are opened, and the seventh valve 407 and the eighth valve 409 are closed, so that the fuel is returned from the fuel storage tank 301 through the delivery port 308, the sixth valve 405, the heat exchanger 402, the power pump 404, the fifth valve 403, and the return port 309 to the fuel storage tank 301 for circulation until the fuel is adjusted to the first set temperature. The first set temperature is set to -11°C.

[0095] S2, the supercooled water production unit 100 generates supercooled water of a set temperature and transfers a set amount of supercooled water into the water storage device 103. The first valve 106 is opened to inject the supercooled water into the fuel storage tank 201 of the supercooled water and fuel collision unit 200 storing fuel for mixing.

[0096] S3, open the seventh valve 407, the eighth valve 409, and the power pump 404, close the fifth valve 403 and the sixth valve 405, and the fuel in the fuel storage unit 300 is delivered to the ejector pump 500 through the fuel bypass 406 and the fourth fuel channel of the circulation control and heat exchange unit 400, and at the same time open the second valve 206, the third valve 207, and the ninth valve 602, and close the fourth valve 307, and deliver the fuel containing supercooled water to the ejector pump 500 through the fuel storage tank 201 of the supercooled water and fuel collision unit 200, and the supercooled water forms ice and enters the inlet pipe 601 of the engine 600 through the ejector pump 500 with the fuel, so as to simulate the transient freezing environment of the fuel. The transient freezing environment of the fuel refers to the environment in which the fuel delivered to the engine contains a high concentration of ice content due to the accumulation of ice in the aircraft fuel system and the subsequent shedding in a relatively short period of time.

[0097] S4, the engine 600 operates under the most severe transient icing condition, and monitors relevant operating parameters of the engine 600 to determine whether the engine 600 operates normally.

[0098] Figure 3 A flowchart of a steady-state icing test of an icing test device for an aircraft engine fuel system according to an embodiment of the present invention is shown. As shown in the figure, preferably, the icing test method for an aircraft engine fuel system also includes a steady-state icing test, comprising the steps of:

[0099] T1, the temperature of the fuel stored in the fuel storage unit 300 is adjusted to the first set temperature through the circulation control and heat exchange unit 400. Specifically, the required fuel is injected into the fuel storage tank 301 through the second refueling port 304, the fifth valve 403, the sixth valve 405, and the power pump 404 are opened, and the seventh valve 407 and the eighth valve 409 are closed, so that the fuel is returned from the fuel storage tank 301 through the delivery port 308, the sixth valve 405, the heat exchanger 402, the power pump 404, the fifth valve 403, and the return port 309 to the fuel storage tank 301 for circulation until the fuel is adjusted to the second set temperature. The second set temperature is set to 27°C.

[0100] T2, the supercooled water production unit 100 generates liquid water of a set temperature, and stores a set amount of liquid water in the water storage device 103. The first valve 106 is opened to inject liquid water into the supercooled water and fuel collision unit 200 storing fuel. The supercooled water and fuel collision unit 200 fully mixes liquid water and fuel into an oil-water emulsion in the fuel storage tank 201. The second valve 206 and the fourth valve 307 are opened, and the third valve 207 is closed. The supercooled water and fuel collision unit 200 transports the oil-water emulsion with a set water content to the fuel storage unit 300 through the third fuel pipeline 306.

[0101] T3, referring to step T1, the fuel containing the oil-water emulsion stored in the fuel storage unit 300 is circulated and cooled to a third set temperature through the circulation control and heat exchange unit 400. The third set temperature is the lowest fuel temperature and critical freezing temperature that the aircraft can experience. The fuel circulation further ensures that the water is evenly distributed in the oil.

[0102] T4, once the third set temperature is reached, the seventh valve 407, the eighth valve 409, and the power pump 404 are opened, and the fifth valve 403 and the sixth valve 405 are closed. The water-containing fuel in the fuel storage unit 300 is transported to the ejector pump 500 through the fuel bypass 406 and the fourth fuel channel of the circulation control and heat exchange unit 400, and enters the inlet pipeline 601 of the engine 600 through the ejector pump 500.

[0103] T5, the engine 600 operates under the most severe steady-state icing condition, and the relevant operating parameters of the engine 600 are monitored to determine whether the engine 600 operates normally.

[0104] Preferably, after completing step T2 and before executing step T3, a fuel sample is obtained from sampling port 302 to perform a moisture test to determine whether the water content meets the requirements of airworthiness clause 33.67(b)(4)(ii). It should be noted that the moisture test can be performed using the Karl Fischer water content test method.

[0105] Preferably, in step T2, the liquid water and the fuel oil can be fully stirred by the stirrer 202 provided on the fuel tank 201 so that the two are fully mixed into an oil-water emulsion.

[0106] The invention provides an aircraft engine fuel system icing test device and test method, which have the following advantages:

[0107] 1. By designing devices such as supercooled water manufacturing units and supercooled water and fuel collision units, the effect of transient water injection into ice can be achieved, and the ice-containing fuel can be effectively injected into the aircraft engine inlet pipeline, which can effectively solve the problem that the actual transient ice environment is difficult to simulate.

[0108] 2. This test method can better control the amount of ice generated.

[0109] 3. The test device can realize steady-state icing test and transient icing test of fuel system, and effectively coordinates the test resources.

[0110] 4. This test device can improve the uniform distribution of water in fuel.

[0111] It will be apparent to those skilled in the art that various modifications and variations may be made to the above exemplary embodiments of the present invention without departing from the spirit and scope of the present invention. Therefore, it is intended that the present invention covers modifications and variations of the present invention that fall within the scope of the appended claims and their equivalent technical solutions.

Claims

1. An aircraft engine fuel system icing test device, comprising: A supercooled water production unit for generating liquid water at a set temperature; A supercooled water and fuel collision unit, used for injecting the liquid water of the set temperature into the fuel to generate water-containing fuel or ice-containing fuel; A fuel storage unit, used for storing fuel, wherein the fuel storage unit and the supercooled water and fuel collision unit are connected via a fuel pipeline; A circulation control and heat exchange unit is connected to the fuel storage unit through a fuel pipeline, and the circulation control and heat exchange unit is used to increase or decrease the temperature of the fuel in the fuel storage unit; The priming pump is connected to the circulation control and heat exchange unit and the supercooled water and fuel collision unit through the fuel pipeline respectively. The priming pump is connected to the inlet pipeline of the engine. The priming pump is used to suck the water-containing fuel or ice-containing fuel in the fuel pipeline into the inlet pipeline of the engine.

2. The aircraft engine fuel system icing test device according to claim 1, characterized in that: The supercooled water manufacturing unit includes a temperature control system, a thermostat and a water storage device. The temperature control system is used to control the temperature of the thermostat. The water storage device is arranged in the thermostat. The bottom of the water storage device is connected to the supercooled water and fuel collision unit through a first fuel pipeline.

3. The aircraft engine fuel system icing test device according to claim 2, characterized in that: The supercooled water production unit further includes a first temperature sensor for measuring the temperature of the thermostat or the water storage device, and the temperature control system controls the temperature of the thermostat based on the first temperature sensor; The first fuel pipeline is a downwardly expanding pipeline, and a first valve is provided on the first fuel pipeline.

4. The aircraft engine fuel system icing test device according to claim 1, characterized in that: The supercooled water and fuel collision unit comprises a fuel storage tank and a stirrer arranged on the fuel storage tank, and the stirrer is used for fully mixing the fuel and liquid water.

5. The aircraft engine fuel system icing test device according to claim 4, characterized in that: The supercooled water and fuel collision unit also includes a first refueling port and an observation window, wherein the first refueling port is arranged on the top of the fuel storage tank, and the observation window is arranged on the fuel storage tank. The bottom of the fuel storage tank is connected to the ejector pump through a second fuel pipeline, and a second valve and a third valve are arranged on the second fuel pipeline. The second valve is used to control the injection of water-containing fuel or ice-containing fuel in the fuel storage tank into the second fuel pipeline, and the third valve is used to control the injection of water-containing fuel or ice-containing fuel in the second fuel pipeline into the ejector pump.

6. The aircraft engine fuel system icing test device according to claim 5, characterized in that: An ice collecting unit is also provided in the second fuel pipeline, and the ice collecting unit is arranged between the third valve and the ejector pump.

7. The aircraft engine fuel system icing test device according to claim 5, characterized in that: The fuel storage unit includes a fuel storage tank, on which a sampling port, a second temperature sensor and a second refueling port are provided. The second temperature sensor is used to measure the temperature inside the fuel storage tank. The sampling port and the second refueling port are respectively arranged at the bottom and the top of the fuel storage tank.

8. The aircraft engine fuel system icing test device according to claim 7, characterized in that: The fuel storage tank is provided with an oil inlet, and the fuel storage tank is connected to the second fuel pipeline through a third fuel pipeline. One end of the third fuel pipeline is connected to the oil inlet, and the other end is connected to the second fuel pipeline and is located between the second valve and the third valve. A fourth valve is provided on the third fuel pipeline.

9. The aircraft engine fuel system icing test device according to claim 8, characterized in that: The fuel storage tank is also provided with a delivery port and a return port, the circulation control and heat exchange unit is connected to the delivery port and the return port through a fourth fuel pipeline to form a circulating fuel passage, and a heat exchanger is provided on the fourth fuel pipeline; A fifth valve and a power pump are provided on the fuel pipeline between the heat exchanger and the return port, the fifth valve is arranged between the return port and the power pump, and a sixth valve is provided on the fuel pipeline between the heat exchanger and the delivery port.

10. The aircraft engine fuel system icing test device according to claim 9, characterized in that: The circulation control and heat exchange unit also includes a fuel bypass, one end of which is connected to the fuel pipeline between the heat exchanger and the power pump, and the other end is connected to the fuel pipeline between the sixth valve and the return port. A seventh valve is provided on the fuel bypass.

11. The aircraft engine fuel system icing test device according to claim 10, characterized in that: The circulation control and heat exchange unit is connected to the ejector pump through a fifth fuel pipeline. One end of the fifth fuel pipeline is connected to the fourth fuel channel and is located between the fifth valve and the power pump, and the other end is connected to the ejector pump. An eighth valve is provided on the fifth fuel pipeline.

12. The aircraft engine fuel system icing test device according to claim 1, characterized in that: A ninth valve and a flow meter are arranged on the inlet pipeline of the engine.

13. An aircraft engine fuel system icing test method, applicable to the aircraft engine fuel system icing test device as claimed in claim 1, characterized in that: Including transient icing test, including steps: S1, adjusting the temperature of the fuel stored in the fuel storage unit to reach a first set temperature through a circulation control and a heat exchange unit; S2, the supercooled water production unit generates supercooled water of a set temperature, and injects a set amount of supercooled water into the supercooled water and fuel collision unit storing fuel; S3, the fuel in the fuel storage unit is delivered to the ejector pump through the circulation control and heat exchange unit, and the fuel containing supercooled water is delivered to the ejector pump through the supercooled water and fuel collision unit, and the supercooled water forms ice and enters the inlet pipeline of the engine through the ejector pump along with the fuel; S4, the engine operates under the most severe transient icing condition and monitors relevant operating parameters of the engine.

14. The aviation engine fuel system icing test method according to claim 13, characterized in that: It also includes a steady-state icing test, which includes the following steps: T1, adjusting the temperature of the fuel stored in the fuel storage unit to reach a second set temperature through the circulation control and heat exchange unit; T2, the supercooled water production unit generates liquid water of a set temperature and injects it into the supercooled water and fuel collision unit, the supercooled water and fuel collision unit fully mixes the liquid water and fuel into an oil-water emulsion, and the supercooled water and fuel collision unit transports the oil-water emulsion with a set water content to the fuel storage unit through the fuel pipeline; T3, circulating and cooling the fuel containing the oil-water emulsion stored in the fuel storage unit through the circulation control and heat exchange unit to reach a third set temperature; T4, transporting the water-containing fuel in the fuel storage unit to the ejector pump through the circulation control and heat exchange unit, and entering the inlet pipeline of the engine through the ejector pump; T5, the engine operates in the most severe steady-state icing condition, and monitors relevant operating parameters of the engine.

15. The aviation engine fuel system icing test method according to claim 14, characterized in that: In step T2, the liquid water and fuel are stirred and fully mixed into an oil-water emulsion.

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