Aircraft piston engine oil supply integrated device

Abstract

The utility model discloses an aircraft piston engine oil supply integration device, which comprises an integration box body, and electric fuel pumps, check valves and an internal channel which are integrated in the integration box body, the two electric fuel pumps are symmetrical about the center, one end of each electric fuel pump is communicated with the internal channel, and the other end of each electric fuel pump is communicated with the check valve. The other ends of the electric fuel pumps communicate with the connecting pipes correspondingly, the check valves are installed on the outer end faces of the two sides of the internal channel correspondingly, and the two ends of the internal channel communicate with the side edges of the two connecting pipes correspondingly. The upper end opening of the integrated box body is connected with the box body top cover through disassembly and assembly assemblies on the two sides. According to the utility model, the electric fuel pump, the check valve and the internal channel are integrated in the integrated box body, so that the pipeline layout is optimized, and the space compression and the maintenance efficiency are realized.

Description

Technical Field

[0001] This utility model relates to the field of aircraft piston engine technology, and in particular to an integrated fuel supply device for aircraft piston engines. Background Technology

[0002] An aircraft piston engine is a reciprocating internal combustion engine that burns gasoline. It is one of the earliest types of engines used in the aviation industry. It generates thrust by driving a propeller to rotate at high speed, thus providing flight power for the aircraft.

[0003] The fuel supply system of a traditional aircraft piston engine typically consists of components such as a distributed electric fuel pump and a check valve, which are connected by external pipelines.

[0004] However, the original components were relatively scattered and the pipelines were messy, which increased the space required and made the overall replacement and debugging inconvenient. Therefore, an integrated fuel supply device for aircraft piston engines was proposed to solve the above problems. Utility Model Content

[0005] (a) Purpose of the utility model

[0006] To address the technical problems existing in the background art, this utility model proposes an integrated fuel supply device for aircraft piston engines. By integrating an electric fuel pump, a check valve, and internal channels into an integrated housing, the pipeline layout is optimized, achieving space compression and maintenance efficiency.

[0007] (II) Technical Solution

[0008] This utility model provides an integrated fuel supply device for an aircraft piston engine, including an integrated housing and an electric fuel pump, a check valve, and an internal channel integrated therein. The two electric fuel pumps are centrally symmetrical, with one end of each pump connected to the internal channel and the other end of each pump connected to a connecting pipe. The check valve is installed on the outer end face of both sides of the internal channel. Both ends of the internal channel are connected to the sides of the two connecting pipes. The upper opening of the integrated housing is connected to the top cover of the housing via disassembly and assembly components on both sides.

[0009] Preferably, the side wall of the integrated box has two openings, and the two connecting pipes pass through the openings to the side wall of the integrated box.

[0010] Preferably, the feed end of one of the electric fuel pumps is connected to the feed pipe connector via the connecting pipe, and the discharge end of the other electric fuel pump is connected to the discharge pipe connector of the mounting bracket via another connecting pipe.

[0011] Preferably, the assembly / disassembly component includes a mounting base, fixing bolts, a pin plate, and a socket. Both sides of the integrated housing are connected to the mounting bases, and both sides of the housing top cover are connected to the pin plates. The pin plates on both sides are inserted into the sockets opened above the mounting bases on both sides. The fixing bolts penetrate the side wall of the mounting base and extend into the interior of the pin plates, and the fixing bolts and the pin plates are connected by threads.

[0012] Preferably, both the integrated box body and the top cover are made of lightweight aluminum alloy, and handles are provided on both outer walls of the integrated box body.

[0013] Preferably, it includes a connector mounting bracket, one end of which is connected to the bottom of the electric fuel pump, and the other end of which is connected to the inner bottom wall of the integrated housing.

[0014] Preferably, both sides of the integrated housing have a number of quick-release interfaces.

[0015] Compared with the prior art, the above-mentioned technical solution of this utility model has the following beneficial technical effects:

[0016] The integrated fuel supply unit for the aircraft's piston engine optimizes the pipeline layout by integrating the electric fuel pump, check valve, and internal channels into an integrated housing, thereby achieving space compression and maintenance efficiency. Attached Figure Description

[0017] Figure 1 This is a schematic diagram of the structure of an integrated fuel supply device for an aircraft piston engine proposed in this utility model.

[0018] Figure 2 This is a diagram showing the internal structure of the integrated housing in an integrated fuel supply device for an aircraft piston engine, as proposed in this utility model.

[0019] Figure 3 This is an exploded view of the disassembled components in an integrated fuel supply device for an aircraft piston engine proposed in this utility model.

[0020] Figure 4 This is a partial cross-sectional view of an integrated fuel supply device for an aircraft piston engine proposed in this utility model.

[0021] Reference numerals: 1. Quick-release interface; 2. Integrated housing; 3. Handle; 4. Mounting base; 5. Fixing bolt; 6. Insert plate; 7. Housing top cover; 8. Opening; 9. Feed pipe connector; 10. Internal channel; 11. Check valve; 12. Electric fuel pump; 13. Insert; 14. Mounting bracket; 15. Discharge pipe connector; 16. Connecting pipe. Detailed Implementation

[0022] To make the objectives, technical solutions, and advantages of this utility model clearer, the present utility model will be further described in detail below with reference to specific embodiments and accompanying drawings. It should be understood that these descriptions are merely exemplary and not intended to limit the scope of this utility model. Furthermore, descriptions of well-known structures and technologies are omitted in the following description to avoid unnecessarily obscuring the concept of this utility model.

[0023] In the description of this utility model, it should be noted that the terms "upper," "lower," "inner," "outer," "front end," "rear end," "both ends," "one end," and "the other end," etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used solely for the convenience of describing this utility model and for simplifying the description, and do not 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. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance.

[0024] In the description of this utility model, it should be noted that, unless otherwise explicitly specified and limited, the terms "installed," "equipped with," and "connected," etc., should be interpreted broadly. For example, "connected" can be a fixed connection, such as welding, riveting, or bonding; it can also be a detachable connection, such as threaded connection, keyed connection, or pin connection; or an integral connection; it can be a mechanical connection or an electrical connection; it can be a direct connection or an indirect connection through an intermediate medium; or it can be a connection within two components. Those skilled in the art can understand the specific meaning of the above terms in this utility model based on the specific circumstances.

[0025] like Figure 1-4 As shown, this utility model proposes an integrated fuel supply device for an aircraft piston engine, comprising an integrated housing 2 and an electric fuel pump 12, a check valve 11, and an internal channel 10 integrated therein. The two electric fuel pumps 12 are centrally symmetrical, with one end of each pump connected to the internal channel 10 and the other end connected to a connecting pipe 16. Check valves 11 are installed on the outer end faces of both sides of the internal channel 10, and both ends of the internal channel 10 are connected to the sides of the two connecting pipes 16. The upper opening of the integrated housing 2 is connected to the top cover 7 of the housing via disassembly and assembly components on both sides.

[0026] In this invention, when in use, fuel can enter through one of the connecting pipes 16, then pass through the electric fuel pump 12 and the internal channel 10, and finally be delivered to the aircraft piston engine through the other connecting pipe 16.

[0027] Furthermore, the design of dual electric fuel pumps 12 can serve as backups for each other. When one electric fuel pump 12 fails, the other can still continuously draw fuel from the fuel tank and pressurize and deliver it to the engine, thus avoiding fuel supply interruption.

[0028] Furthermore, the design of the dual check valves 11 allows them to work in conjunction with the dual electric fuel pumps 12, enabling the check valves 11 on both sides to be opened or closed in real time according to the on / off state of the dual electric fuel pumps 12.

[0029] In an optional embodiment, two openings 8 are provided through the side wall of the integrated housing 2, and two connecting pipes 16 pass through the openings 8 to the side wall of the integrated housing 2.

[0030] It should be noted that the inner diameter of opening 8 is larger than the outer diameter of connecting pipe 16.

[0031] In an optional embodiment, the feed end of one electric fuel pump 12 is connected to the feed pipe connector 9 via a connecting pipe 16, and the discharge end of the other electric fuel pump 12 is connected to the discharge pipe connector 15 of the mounting bracket via another connecting pipe 16.

[0032] It should be noted that the connecting pipe 16 connected to the feed end of the electric fuel pump 12 is connected to the feed pipe through the feed pipe connector 9, and the other connecting pipe 16 connected to the discharge end of the electric fuel pump 12 is connected to the discharge pipe through the discharge pipe connector 15 of the mounting bracket. The discharge pipe can provide fuel supply for the aircraft piston engine.

[0033] In an optional embodiment, the assembly includes a mounting base 4, a fixing bolt 5, a pin plate 6, and a socket 13. Both sides of the integrated housing 2 are connected to the mounting base 4, and both sides of the housing top cover 7 are connected to the pin plate 6. The pin plates 6 on both sides are inserted into the sockets 13 opened above the mounting bases 4 on both sides. The fixing bolt 5 passes through the side wall of the mounting base 4 and extends into the interior of the pin plate 6, and the fixing bolt 5 and the pin plate 6 are connected by threads.

[0034] It should be noted that when the top cover 7 of the box needs to be separated, the fixing bolts 5 on both sides are rotated to separate them from the pin plates 6, so that the pin plates 6 on both sides can be pulled out from the sockets 13 above the mounting bases 4 on both sides, thus separating the top cover 7 of the box from the integrated box 2; when the top cover 7 of the box needs to be installed, the pin plates 6 located on both sides of the top cover 7 are inserted into the sockets 13 of the mounting bases 4 on both sides, and the fixing bolts 5 are rotated in the opposite direction to limit the pin plates 6 within the sockets 13 of the mounting bases 4, thus realizing the installation of the pin plates 6.

[0035] The design incorporates a separate top cover 7 and an integrated housing 2, facilitating the inspection and replacement of internal components within the integrated housing 2.

[0036] In an optional embodiment, both the integrated box body 2 and the box top cover 7 are made of lightweight aluminum alloy, and handles 3 are provided on both outer walls of the integrated box body 2.

[0037] It should be noted that the top cover 7 and quick-release interface 1 of the box are made of lightweight aluminum alloy, which improves corrosion resistance and structural strength while reducing weight; and the handles 3 on both sides make it easy to move the integrated box 2.

[0038] In an optional embodiment, a connector mounting bracket 14 is included, one end of which is connected to the bottom of the electric fuel pump 12, and the other end of which is connected to the inner bottom wall of the integrated housing 2.

[0039] It should be noted that the socket mounting bracket 14 can provide support for the electric fuel pump 12, and a layer of elastic rubber material is attached between the contact surface of the socket mounting bracket 14 and the electric fuel pump 12 to absorb engine vibration.

[0040] In an optional embodiment, the integrated housing 2 has multiple quick-release interfaces 1 extending through both sides.

[0041] It should be noted that multiple quick-release interfaces 1 can be used to install the integrated housing 2.

[0042] Although embodiments of the present invention have been shown and described, it will be understood by those skilled in the art that various changes, modifications, substitutions and alterations can be made to these embodiments without departing from the principles and spirit of the present invention, the scope of which is defined by the appended claims and their equivalents.

Claims

1. An oil supply integration device for an aircraft piston engine, characterized in that, The utility model provides an integrated box body (2) and the electric fuel pump (12), check valve (11) and internal passage (10) integrated in its inside, two electric fuel pumps (12) are based on center symmetry, one end of two electric fuel pumps (12) is communicated with internal passage (10), the other end of electric fuel pump (12) is communicated with connecting pipe (16) respectively, and check valve (11) is installed on both sides of internal passage (10) outer end surface respectively, both ends of internal passage (10) are communicated with the side of two connecting pipe (16) respectively, and the upper end opening of integrated box body (2) is connected with box top cover (7) through both sides of dismounting assembly respectively.

2. An oil supply integration device for an aircraft piston engine according to claim 1, characterized in that, Two open holes (8) are penetrated in the side wall of the integrated box body (2), and the two connecting pipes (16) are penetrated in the side wall of the integrated box body (2) through the open holes (8) respectively.

3. An oil supply integration device for an aircraft piston engine according to claim 1, characterized in that, The feeding end of one of the electric fuel pumps (12) is connected with the feeding pipe connecting head (9) through the connecting pipe (16), and the discharging end of the other electric fuel pump (12) is connected with the mounting bracket discharging pipe connecting head (15) through the other connecting pipe (16).

4. An oil supply integration device for an aircraft piston engine according to claim 1, characterized in that, The dismounting assembly comprises a mounting seat (4), a fixing bolt (5), a latch plate (6) and a socket (13), both sides of the integrated box body (2) are connected with the mounting seat (4) respectively, both sides of the box top cover (7) are connected with the latch plate (6) respectively, both sides of the latch plate (6) are inserted into the socket (13) opened above both sides of the mounting seat (4), the fixing bolt (5) penetrates the side wall of the mounting seat (4) and extends into the latch plate (6), and the fixing bolt (5) and the latch plate (6) are screw-connected.

5. An oil supply integration device for an aircraft piston engine according to claim 4, characterized in that, The integrated box body (2) and the box top cover (7) are made of light aluminum alloy material, and the two side walls of the integrated box body (2) are provided with handles (3).

6. An oil supply integration device for an aircraft piston engine according to claim 4, characterized in that, The integrated box body (2) and the box top cover (7) are made of light aluminum alloy material, and the two side walls of the integrated box body (2) are provided with handles (3).

7. An oil supply integration device for an aircraft piston engine according to claim 1, characterized in that, A plurality of quick release interfaces (1) are penetrated in both sides of the integrated box body (2).

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