An aircraft fuel supply system

Abstract

The utility model discloses an aircraft fuel supply system, including oil tank, booster pump is communicated the oil tank through first pipeline, anti bubble bottle is located in the oil tank, the top of anti bubble bottle is equipped with first oil nozzle, first oil nozzle is equipped with oil inlet and oil outlet, the oil outlet is communicated to have oil outlet pipeline, the lower extreme of oil outlet pipeline is located the bottom of anti bubble bottle, the oil inlet is communicated booster pump through first pipeline, the oil outlet is communicated engine through third pipeline. Through booster pump, the oil liquid of oil tank is drawn to anti bubble bottle through first pipeline, and the oil liquid enters from oil inlet, and due to the influence of booster pump, the oil liquid pressure in anti bubble bottle increases, and the bubble in oil liquid accelerates to float up, and the solubility of oil liquid increases, and the bubble in oil liquid reduces, and the oil outlet pipeline supplies engine with the oil liquid without bubble from the bottom of anti bubble bottle, reaches the effect of preventing bubble.

Description

Technical Field

[0001] This utility model relates to the field of aircraft technology, and in particular to an aircraft fuel supply system. Background Technology

[0002] The fuel system has the functions of storing fuel, supplying fuel, adjusting the center of gravity, and cooling medium. Engine self-priming, engine bleed air boosting, and fuel pump boosting are common fuel supply methods for aircraft fuel systems. The existing technology has the following problems: the liquid has low solubility in a low-pressure environment, which makes it easy to generate bubbles. Bubbles may also be generated during the operation of the gear pump, which will affect the normal operation of the engine. Utility Model Content

[0003] This invention provides an aircraft fuel supply system, which aims to solve at least one of the technical problems existing in the prior art.

[0004] The technical solution of this utility model relates to an aircraft fuel supply system, including a fuel tank; The booster pump is connected to the oil storage tank; An anti-bubble bottle is tilted and positioned below the oil reservoir. The top of the anti-bubble bottle is equipped with a first oil nozzle, which has an oil inlet and an oil outlet. The oil outlet is connected to an oil outlet pipeline, the lower end of which is located at the bottom of the anti-bubble bottle. The oil inlet is connected to the booster pump through the first pipeline, and the oil outlet is connected to the engine.

[0005] According to some embodiments of this utility model, the lower end of the oil outlet pipe is connected to a counterweight, and the counterweight is connected to the inner cavity of the anti-bubble bottle.

[0006] According to some embodiments of the present invention, the anti-bubble bottle is tilted at 45° to the horizontal direction of the aircraft.

[0007] According to some embodiments of the present invention, a second oil nozzle is provided on one side of the anti-bubble bottle, and the second oil nozzle is connected to the oil storage tank through a second pipeline.

[0008] According to some embodiments of the present invention, a throttling valve is also provided on the second pipeline.

[0009] According to some embodiments of this utility model, it also includes an oil filter, the two ends of which are connected to the oil storage tank and the booster oil pump through a third pipeline and a fourth pipeline, respectively.

[0010] According to some embodiments of this utility model, a diverter is provided on the third pipeline, and the diverter is connected to the oil storage tank and the oil filter respectively.

[0011] According to some embodiments of this utility model, the oil tank is also connected to a booster pipe, and the other end of the booster pipe is connected to the bleed air port of the engine through a bleed air valve.

[0012] According to some embodiments of this utility model, the anti-bubble bottle is made of metal material.

[0013] According to some embodiments of this utility model, the oil outlet pipeline is a thermoplastic polyurethane rubber hose.

[0014] The beneficial effects of this utility model are as follows: 1. The oil in the reservoir is pumped to the anti-bubble bottle through the first pipeline by the booster pump. The oil enters through the oil inlet. Due to the influence of the booster pump, the oil pressure in the anti-bubble bottle increases, and the air bubbles in the oil rise faster. At the same time, the solubility of the oil increases, reducing the number of air bubbles in the oil. The oil outlet pipeline supplies the engine with the air-free oil from the bottom of the anti-bubble bottle, thus achieving the anti-bubble effect. Attached Figure Description

[0015] Figure 1 This is a schematic diagram of the structure of an aircraft fuel supply system according to an embodiment of the present invention; Figure 2 for Figure 1 A partially enlarged schematic diagram of the aircraft's fuel supply system; Figure 3 This is a top view of the aircraft fuel supply system according to an embodiment of the present invention. Figure 4 This is a schematic diagram of the structure of an anti-bubble bottle according to an embodiment of the present invention; Figure 5 This is a cross-sectional view of an anti-bubble bottle arranged at a 45° angle according to an embodiment of this utility model.

[0016] Icon labels: Oil tank capacity: 100; Booster pump 200; Anti-bubble bottle 300, first oil nozzle 310, oil inlet 311, oil outlet 312, oil outlet pipeline 313, counterweight 314, first pipeline 320, second oil nozzle 340, second pipeline 350, throttle valve 360. Oil filter 400, third pipeline 410, distributor 411, fourth pipeline 420; 500 pressure boosting pipeline. Detailed Implementation

[0017] The following will describe several embodiments of the present invention, including embodiments corresponding to the accompanying drawings. It should be understood that the drawings are used to assist in understanding the technical features and technical solutions of the present invention, and should not be construed as limiting the scope of protection of the present invention.

[0018] The following will provide a clear and complete description of the concept, specific structure, and technical effects of this utility model in conjunction with the embodiments and accompanying drawings, so as to fully understand the purpose, solution, and effects of this utility model. It should be noted that, unless otherwise specified, the embodiments and features described in this application can be combined with each other.

[0019] It should be noted that, unless otherwise explicitly defined, when a feature is referred to as "fixed," "connected," "installed," or "set" on another feature, it can be "fixed," "connected," "installed," or "set" directly on the other feature, or it can be "fixed," "connected," "installed," or "set" on the other feature indirectly. The terms "fixed," "connected," "installed," and "set" should be interpreted broadly, and those skilled in the art can reasonably determine the specific meaning of the above terms in this utility model in conjunction with the specific content of the technical solution.

[0020] It should be noted that the descriptions of orientations or positional relationships indicated by terms such as up, down, left, right, top, bottom, front, back, inside, and outside used in this utility model are based on the orientations or positional relationships indicated by the accompanying drawings or embodiments. They are only for the purpose of facilitating the description of this utility model and simplifying the description, and are not intended to indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this utility model.

[0021] It should be noted that the term "and / or" used in this utility model includes any combination of one or more related listed items, "several" means one or more, "multiple" means at least two, "greater than", "less than", "exceeding" are understood to exclude the number itself, and "above", "below", "within" are understood to include the number itself.

[0022] It should be noted that the use of "first" and "second" in this utility model is only for the purpose of distinguishing technical features, and should not be construed as indicating or implying relative importance, or implicitly indicating the number of technical features indicated, or implicitly indicating the order of the technical features indicated.

[0023] It should be noted that, unless otherwise expressly defined, all technical and scientific terms used herein have the same meaning as commonly understood by one of ordinary skill in the art. The terminology used in this specification is for the purpose of describing particular embodiments only and not for limiting the scope of the invention.

[0024] like Figures 1 to 5As shown, this embodiment proposes an aircraft fuel supply system, including a fuel tank 100; a booster pump 200 connected to the fuel tank 100; and an anti-bubble bottle 300, which is inclinedly disposed below the fuel tank 100. The top of the anti-bubble bottle 300 is provided with a first fuel nozzle 310, which has an inlet 311 and an outlet 312. The outlet 312 is connected to an outlet pipeline 313, the lower end of which is located at the bottom of the anti-bubble bottle 300. The inlet 311 is connected to the booster pump 200 through a first pipeline 320, and the outlet 312 is connected to the engine.

[0025] In the above embodiment, a second oil nozzle 340 is provided on one side of the anti-bubble bottle 300. The second oil nozzle 340 is connected to the oil storage tank 100 through a second pipeline 350. At the same time, a throttle valve 360 ​​is also provided on the second pipeline 350. When there is too much oil or too much pressure in the anti-bubble bottle 300, the oil or excess gas can be discharged outward through the second oil nozzle 340. The discharged oil or gas flows back to the oil storage tank 100 through the throttle valve 360, thereby regulating the flow rate and the internal pressure of the anti-bubble bottle 300.

[0026] The above-mentioned aircraft fuel supply system has at least the following beneficial effects: the booster pump 200 draws the fuel in the fuel tank 100 into the anti-bubble bottle 300 through the first pipeline 210. The fuel enters through the fuel inlet 311. Due to the influence of the booster pump 200, the fuel pressure in the anti-bubble bottle 300 increases, the bubbles in the fuel rise faster, and the fuel solubility increases, reducing the number of bubbles in the fuel. The fuel outlet pipeline 313 supplies the engine with the fuel without bubbles at the bottom of the anti-bubble bottle 300, thus achieving the anti-bubble effect.

[0027] According to some embodiments of this utility model, the lower end of the oil outlet pipe 313 is connected to a counterweight 314, which is connected to the inner cavity of the anti-bubble bottle 300. The counterweight 314 can ensure that the lower end of the oil outlet pipe 313 is always at the bottom of the anti-bubble bottle 300 under the action of gravity, thereby realizing the extraction of oil without bubbles from the bottom.

[0028] According to some embodiments of this utility model, the anti-bubble bottle 300 is tilted at 45° to the horizontal direction of the aircraft to ensure that the second oil nozzle 340 is in a higher position, which is more conducive to oil return and exhaust. At the same time, the position of the counterweight 314 can be lower to reduce the amount of unusable oil.

[0029] According to some embodiments of this utility model, it also includes an oil filter 400. The two ends of the oil filter 400 are connected to the oil tank 100 and the booster oil pump through the third pipeline 410 and the fourth pipeline 420, respectively. The oil filter 400 filters the oil and improves the quality of the oil 400 entering the engine.

[0030] According to some embodiments of the present invention, a distributor 411 is provided on the third pipeline 410. The distributor 411 is connected to the oil tank 100 and the oil filter 400 respectively. The distributor 411 is used to connect multiple oil tanks 100, thereby increasing the oil storage capacity and increasing the range of the aircraft.

[0031] According to some embodiments of this utility model, the oil reservoir 100 is also connected to a booster pipe 500. The other end of the booster pipe 500 is connected to the engine's bleed air port through a bleed air valve. At the same time, the booster pump 200 is a positive displacement booster pump, which causes the internal volume of the booster pump 200 to change when it is working. The volume before the pump increases, forming a negative pressure to draw oil, and the volume after the pump decreases, increasing the oil pressure, maintaining the fuel pressure required by the engine, and ensuring sufficient and stable fuel supply.

[0032] According to some embodiments of this utility model, the anti-bubble bottle 300 is made of metal.

[0033] According to some embodiments of this utility model, the oil outlet pipe 313 is a thermoplastic polyurethane rubber hose.

[0034] It should be noted that in this specification, terms such as "one embodiment", "some embodiments", "basic embodiment", and "extended embodiment" may be used to describe several embodiments of the present invention, and the specific features, structures, materials or characteristics of the several embodiments may be combined in accordance with the principles and spirit of the present invention.

[0035] Although some embodiments of the present invention have been shown and described in this specification, the present invention should not be limited to the above embodiments. As long as they achieve the technical effects of the present invention by the same or equivalent means, any changes, modifications, equivalent substitutions and equivalent variations of these embodiments within the spirit and principles of this disclosure, without departing from the principles and purpose of the present invention, should be included within the scope of protection of this disclosure and should be considered to fall within the protection scope of the present invention.

Claims

1. An aircraft fuel supply system, characterized in that, include: Oil storage tank; The booster pump is connected to the oil storage tank; An anti-bubble bottle is tilted and positioned below the oil reservoir. The top of the anti-bubble bottle is equipped with a first oil nozzle, which has an oil inlet and an oil outlet. The oil outlet is connected to an oil outlet pipeline, the lower end of which is located at the bottom of the anti-bubble bottle. The oil inlet is connected to the booster pump through the first pipeline, and the oil outlet is connected to the engine.

2. The aircraft fuel supply system according to claim 1, characterized in that, The lower end of the oil outlet pipe is connected to a counterweight, which is connected to the inner cavity of the anti-bubble bottle.

3. The aircraft fuel supply system according to claim 2, characterized in that, The anti-bubble bottle is tilted at 45° to the horizontal direction of the aircraft.

4. The aircraft fuel supply system according to claim 3, characterized in that, The anti-bubble bottle is provided with a second oil nozzle on one side, and the second oil nozzle is connected to the oil storage tank through a second pipeline.

5. The aircraft fuel supply system according to claim 4, characterized in that, The second pipeline is also equipped with a throttle valve.

6. The aircraft fuel supply system according to claim 1, characterized in that, It also includes an oil filter, the two ends of which are connected to the oil tank and the booster oil pump through a third pipeline and a fourth pipeline, respectively.

7. The aircraft fuel supply system according to claim 6, characterized in that, The third pipeline is equipped with a distributor, which is connected to the oil storage tank and the oil filter respectively.

8. An aircraft fuel supply system according to any one of claims 1 to 7, characterized in that, The oil tank is also connected to a booster pipe, and the other end of the booster pipe is connected to the bleed air port of the engine via a bleed air valve.

9. An aircraft fuel supply system according to claim 8, characterized in that, The anti-bubble bottle is made of metal.

10. An aircraft fuel supply system according to claim 8, characterized in that, The oil outlet pipeline is a thermoplastic polyurethane rubber hose.

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