Aircraft engine system butt joint multi-separation-surface device

Abstract

The invention provides a docking multi-separation-surface device of an aircraft engine system, which can meet the design requirement of reducing the hanging width. The aircraft engine system butt joint multi-separation-face device comprises a vertical firewall used for separating a fire area of an engine from a hanger located in a non-fire area, and the outer contour of the vertical firewall corresponds to the outer contour of the hanger; the liquid pipeline is arranged on the front side of the vertical firewall, one end of the liquid pipeline is installed on the vertical firewall and connected with the machine body side liquid pipeline, and the liquid pipeline comprises at least one first liquid pipeline and at least one second liquid pipeline, and the first liquid pipeline is provided with a first quick-release connector at one end and the second liquid pipeline is provided with a second quick-release connector at the other end. The first liquid pipeline is provided with a first quick-release connector, the first quick-release connector is connected with a firewall side quick-release connector arranged on the vertical firewall, the second liquid pipeline is provided with a fastening connector at one end and a second quick-release connector at the other end, the fastening connector is fastened to the vertical firewall, and the second quick-release connector is arranged in a finger-shaped cover area at the position, closer to the front side than the vertical firewall, of the joint of the nacelle and the hanger.

Description

Technical Field

[0001] This invention relates to a multi-separation surface device for docking an aircraft engine system. Background Technology

[0002] During the integrated design of the aircraft, since the engine fan nacelle and core compartment are generally designated fire zones, structural firewalls need to be installed between them and the aircraft pylons in non-fire zones to meet airworthiness requirements and system fireproof sealing requirements. At the same time, fuel, hydraulic, and air supply pipelines and EWIS cables in the fan nacelle are connected to the fuselage side pipelines. The design of the connection and disconnection of this system affects the maintainability and aerodynamic shape of the entire aircraft, and thus affects the overall economic efficiency of the aircraft.

[0003] A known structure employs a vertical firewall to isolate the engine fire zone and achieve system isolation. In this structure, fuel lines, hydraulic lines, and other connections typically use quick-release couplings, with male and female quick-release couplings located on opposite sides of the vertical firewall. Due to the limited space of the vertical firewall and constraints imposed by the design of seals and supporting structures, the fuel and hydraulic quick-release couplings require significant space for maintenance and operation. This generally necessitates enlarging the aerodynamic shape of the suspension system, increasing aerodynamic drag and impacting aircraft fuel economy.

[0004] In addition, there are structures that install firewalls on both sides forward of the sling to isolate the fan compartment from the fire zone. These also employ quick-release couplings to disconnect the system and provide fire protection. This structure increases the overall weight of the sling and places higher demands on manufacturing processes and subsequent maintenance. Summary of the Invention

[0005] The purpose of this invention is to provide a multi-separation surface device for docking aircraft engine systems, which can reduce the design requirements for the hanging width, facilitate maintenance, and improve the overall economy of the aircraft.

[0006] This invention relates to a multi-separation surface device for docking an aircraft engine system, comprising: a vertical firewall for isolating the engine's fire zone from the pylon located in the non-fire zone, the outer contour of the vertical firewall corresponding to the outer contour of the pylon; and a liquid pipeline disposed forward of the vertical firewall, one end of which is mounted on the vertical firewall and connected to a fuselage-side liquid pipeline, the liquid pipeline including at least one first liquid pipeline and at least one second liquid pipeline, the first liquid pipeline having a first quick-release connector at one end, the first quick-release connector being connected to a firewall-side quick-release connector disposed on the vertical firewall, the second liquid pipeline having a fastening connector at one end and a second quick-release connector at the other end, the fastening connector being fastened to the vertical firewall, the second quick-release connector being disposed in the finger-shaped cover area at the nacelle and pylon connection point forward of the vertical firewall.

[0007] The multi-separation surface device for aircraft engine system docking according to the present invention can reduce the design requirements for sling width, facilitate maintenance, and improve the overall economy of the aircraft.

[0008] Furthermore, in the aforementioned multi-separation surface device for aircraft engine system docking, it may also include a pipe separation wall, which is positioned separately from the vertical firewall in the finger-shaped cover area. The second quick-release connector connects to a quick-release connector on the separation wall side of the pipe separation wall, thereby connecting to the engine-side liquid pipeline. According to the above structure, the second quick-release connector enables rapid connection and disconnection between the second liquid pipeline and the engine-side liquid pipeline, facilitating maintenance.

[0009] In addition, in the above-mentioned aircraft engine system docking multi-separation surface device, the pipeline separation wall may be fixed to the support frame, and the support frame may be fixed to the fan nacelle casing.

[0010] Furthermore, in the aforementioned multi-separation surface device for aircraft engine system docking, multiple pipe separation walls may be provided. This simplifies the structure of each pipe separation wall and further facilitates maintenance.

[0011] Furthermore, in the aforementioned aircraft engine system docking multi-separation surface device, at least a portion of the first liquid line and / or the second liquid line may be made of flexible tubing. This structure facilitates handling situations such as pipe deformation when the lines are disconnected.

[0012] Furthermore, in the aforementioned multi-disengagement surface device for aircraft engine system docking, there may be multiple second liquid lines, and the fastening joint has a triangular flange, which is fastened to the vertical firewall via fasteners. According to this structure, the area occupied by the pipe joints is easily reduced, thereby further reducing the design requirements for the hanging width. Preferably, the corners of the triangle shape are rounded or have their sharp points cut off. This further reduces the area occupied by the pipe joints.

[0013] Furthermore, in the aforementioned aircraft engine system docking multi-separation surface device, it can also include a cable group consisting of multiple EWIS cables, with the vertical firewall having a through hole. The cable group passes through the vertical firewall at the through hole and is sealed to the through hole by a fire-resistant sealing material. According to this structure, for example, compared to placing the connectors of these EWIS cables in the vertical firewall, the design requirements for the sling width can be further reduced.

[0014] In addition, in the above-mentioned aircraft engine system docking multi-separation surface device, the EWIS cable may have a cable connector at the other end, which is disposed in the finger-shaped cover area for connecting the engine-side EWIS cable.

[0015] Furthermore, in the aforementioned multi-disconnect surface assembly for aircraft engine systems, the first liquid line can also be a fuel line. By installing the fuel line, which requires relatively frequent maintenance, at the vertical firewall via a first quick-release connector, the number of fuel line connections can be reduced, thereby mitigating the risk of fuel line leakage.

[0016] In addition, in the above-mentioned aircraft engine system docking multi-separation surface device, the second liquid line may also be a hydraulic line. Attached Figure Description

[0017] Figure 1 This is a schematic diagram showing the general structure near the engine of an aircraft to which an aircraft engine system with a multi-separation surface device according to an embodiment of the present invention is applied.

[0018] Figure 2 This is a schematic perspective view showing the docking of a multi-separation surface device for an aircraft engine system according to an embodiment of the present invention, viewed from above.

[0019] Figure 3 This is a schematic block diagram illustrating an example of an aircraft engine system docking multi-separation surface device according to an embodiment of the present invention.

[0020] Figure 4 This is a perspective view schematically showing the area near the vertical firewall of an aircraft engine system docking multi-separation surface device according to an embodiment of the present invention.

[0021] Figure 5 This is a schematic diagram showing the vertical firewall as viewed from the front.

[0022] Figure 6 It is a perspective view schematically showing the finger-shaped dome area of ​​the engine nacelle and the aircraft's pylon connection.

[0023] Figure 7 It is a perspective view schematically showing the finger-shaped dome area of ​​the engine nacelle and the aircraft's pylon connection.

[0024] Figure 8 This is a perspective view schematically illustrating an example of the liquid piping of an aircraft engine system docking multi-separation surface device according to an embodiment of the present invention.

[0025] Figure 9 This is a perspective view schematically illustrating an example of a fuel line for an aircraft engine system docking with a multi-separation surface device according to an embodiment of the present invention.

[0026] Figure 10 This is a perspective view schematically illustrating an example of the hydraulic piping of an aircraft engine system docking multi-separation surface device according to an embodiment of the present invention.

[0027] Symbol Explanation

[0028] 1 Finger-shaped cover area at the nacelle and pylon connection; 2 Nacelle; 10 Vertical firewall; 11 Through-hole for liquid lines; 12 Through-hole for gas supply lines; 13 Through-hole for EWIS cables; 14 Through-hole for fan compartment fire suppression lines; 20 Pylon; 21 Pylon fairing; 30 Liquid lines; 31 First liquid line; 32-37 Second liquid lines; 40 Pipe separation wall; 41 First pipe separation wall; 42 Second pipe separation wall; 50 Cable group; 51 One cable group; 52 Another cable group; 60 Forward mounting section; 71 Firewall side quick-release connector; 72 Separation wall side quick-release connector; 73 Nut connector; 80 Support frame; 90 Fan compartment casing; 100 Aircraft engine system docking multi-separation surface device; 111 Through-hole for hydraulic lines; 112 Through-hole for fuel lines; 131 132 Through hole for cable assembly; 211 Finger cover; 301 First quick-release connector; 302 Fastening connector; 303 Second quick-release connector; 304 Flexible tubing portion of the second liquid line; 312 Rigid tubing portion of the first liquid line; 313 Flexible tubing portion of the first liquid line; 511 Cable connector; 521 Another cable connector; 3021 Flange. Detailed Implementation

[0029] The following describes specific embodiments of the present invention. It should be noted that, in order to provide a concise description, this specification cannot exhaustively describe all features of the actual embodiments. It should be understood that, in the actual implementation of any embodiment, just as in any engineering or design project, various specific decisions are often made to achieve the developer's specific goals and to meet system-related or business-related constraints, and this can change from one embodiment to another. Furthermore, it is understood that although the efforts made in this development process may be complex and lengthy, for those skilled in the art related to the content disclosed in this invention, some design, manufacturing, or production modifications based on the technical content disclosed herein are merely conventional technical means and should not be construed as insufficient content of this disclosure.

[0030] Unless otherwise defined, the technical or scientific terms used in the claims and description shall have the ordinary meaning understood by one of ordinary skill in the art to which this invention pertains. The terms "first," "second," and similar terms used in the patent application description and claims of this invention do not indicate any order, quantity, or importance, but are merely used to distinguish different components. Terms such as "comprising" or "including" indicate that the elements or objects preceding "comprising" encompass the elements or objects listed following "comprising" or "including" and their equivalents, and do not exclude other elements or objects. Terms such as "connected" or "linked" are not limited to physical or mechanical connections, nor are they limited to direct or indirect connections.

[0031] In the following description, numerous directional terms will be used to clearly illustrate the structure and operation of the present invention. However, terms such as "front," "rear," "left," "right," "outer," "inner," "upper," and "lower" should be understood as convenient terms and not as limiting terms. It is particularly important to note that "front" and "rear" are determined based on the air intake direction. "Left" and "right" refer to left and right when viewed from the front of the engine.

[0032] This invention provides a multi-separation surface device for aircraft engine system docking. For liquid piping, quick-release connectors for some liquid piping can be designed on the vertical firewall, while another portion of the liquid piping can be designed as a multi-separation surface. One end of the liquid piping is designed on the vertical firewall via a fastening connector (mechanical connector), and the other end's quick-release connector is designed in the finger-shaped cover area at the nacelle and pylon connection. For EWIS cables, depending on design requirements, some EWIS cables can be designed on the vertical firewall using connectors, while another portion of the EWIS cables passes through the vertical firewall in a sealed frame manner, with the docking separation surface designed in the finger-shaped cover area. In this way, by optimizing the docking arrangement on the vertical firewall, the aerodynamic width of the pylon is reduced. Simultaneously, the device designed in this invention meets fire zone isolation requirements, design clearance requirements, and maintainability requirements.

[0033] <First Implementation>

[0034] Figure 1 This is a schematic diagram showing the general structure near the engine of an aircraft to which the aircraft engine system of the first embodiment of the present invention is docked with the multi-separation surface device 100. Figure 2 It is a schematic perspective view of the aircraft engine system docking multi-separation surface device 100 as viewed from above. Figure 4 This is a schematic perspective view of the area near the vertical firewall 10 of the aircraft engine system docking multi-separation surface device 100, viewed from the front. Figure 5 This is a schematic diagram showing the vertical firewall 10 as viewed from the front. Figure 6 It is a perspective view schematically showing the finger-shaped dome area of ​​the engine nacelle and the aircraft's pylon connection, viewed from the right front. Figure 7 It is a perspective view schematically showing the finger-shaped dome area of ​​the engine nacelle and the aircraft's pylon connection, viewed from the left front. Figure 8 This is a perspective view schematically illustrating an example of the liquid piping of an aircraft engine system docking with a multi-separation surface device 100. Figure 9 This is a perspective view schematically illustrating an example of the fuel lines of an aircraft engine system docking with a multi-separation surface device 100. Figure 10 This is a perspective view schematically illustrating an example of the hydraulic lines 32-34 of the aircraft engine system docking multi-separation surface device 100. In some figures, for the sake of simplicity, illustrations of certain components are sometimes omitted.

[0035] The multi-separation surface device 100 for aircraft engine system docking in this embodiment combines a first separation surface (vertical firewall) and a second to X (X is a natural number of three or more) separation surface in the finger-shaped cover area 1 at the connection between the engine nacelle 2 and the aircraft pylon 20. Some of the space-consuming quick-release connectors for liquid pipelines and connectors for EWIS cables are arranged at the second to X separation surface, which can reduce the design requirements for pylon width. At the same time, the second to X separation surface has sufficient operating space and is closer to the outside of the engine nacelle, making it more accessible to maintenance personnel.

[0036] An aircraft employing an aircraft engine system docking multi-split surface assembly 100 includes an engine and a pylon 20 connecting the engine to the wing. The engine includes a nacelle 2. The fairing 21 of the pylon 20 includes finger-shaped fairings 211. The finger-shaped fairings 211 are located on the forward side of the fairing 21 of the pylon and are connected to the nacelle 2 from above. The finger-shaped fairings 211 cover the outer side of the vertical firewall 10, described later.

[0037] like Figure 2 and Figure 7 As shown, the aircraft engine system docking multi-separation surface device 100 includes a vertical firewall 10 as the first separation surface, a liquid pipeline 30, a pipeline separation wall 40 as the second to third separation surfaces, and a cable group 50 composed of multiple EWIS cables.

[0038] The vertical firewall 10 is positioned perpendicular or substantially perpendicular to the extension direction of the finger-shaped cover 211. The vertical firewall 10 isolates the engine fan nacelle (fire zone) from the pylon 20 located in the non-fire zone. Furthermore, the vertical firewall 10 facilitates frame-to-frame connections and sealing between systems on both sides of the engine. The vertical firewall 10 is located at the front end of the pylon 20 frame. Fuel, hydraulic, air supply, and EWIS systems are typically arranged on the rearward side of the vertical firewall 10. The outer contour of the vertical firewall 10 corresponds to the outer contour of the pylon 20. Additionally, the vertical firewall 10 is equipped with interfaces for hydraulic lines, fuel lines, air supply lines, etc., of the aircraft engine system, as well as through-wall seals for power and signal harnesses.

[0039] In this embodiment, such as Figure 5 As shown, the vertical firewall 10 is provided with: through holes 11 for liquid lines, for example, formed in the right-side region of the vertical firewall 10, including through holes 111 for hydraulic lines and through holes 112 for fuel lines; through holes 12 for gas supply lines, for example, formed in the approximately central region of the vertical firewall 10, for sealing gas supply lines through the firewall; through holes 13 for EWIS cables, for example, formed in the left-side region of the vertical firewall 10, including through holes 131 for cable assemblies and through holes 132 for connectors; and through holes 14 for fan compartment fire suppression lines. By providing these through holes, the fire zone and non-fire zone are isolated while connecting fuel lines, hydraulic lines, gas supply lines, EWIS cables, and other pipelines on the engine side and fuselage side.

[0040] In addition, such as Figure 4 As shown, a front mounting section 60 is also provided on the vertical firewall 10. The front mounting section 60 has the function of isolating fire zones and can also provide space for the EWIS system to be arranged and cross-framed.

[0041] Multiple liquid lines 30 are provided. For example... Figure 2 As shown, a plurality of liquid lines 30 are positioned forward of the vertical firewall 10, with one end installed in a portion of the vertical firewall 10 that has a liquid line through-hole 11, thereby connecting to the fuselage-side liquid lines. Here, "forward" refers to the forward direction of the aircraft's nose relative to the tail. The plurality of liquid lines 30 include at least one (in this embodiment, one) first liquid line 31 and at least one (in this embodiment, six) second liquid lines 32 to 37 (see... Figure 6 ).

[0042] In this embodiment, the first liquid line 31 is a fuel line (engine fuel line). The second liquid lines 32 to 37 are hydraulic lines. For example, the second liquid lines 32 to 34 are connected to the engine drive pump (EDP); the second liquid lines 35 to 37 are connected to the hydraulic thrust reverser system. One end of the first liquid line 31 is installed in the vertical firewall 10 at the location where the fuel line through hole 112 is provided. One end of the second liquid lines 32 to 37 is installed in the vertical firewall 10 at the location where the hydraulic line through hole 111 is provided. Alternatively, a portion of the hydraulic line may be installed in the vertical firewall 10 in the same manner as the first liquid line 31.

[0043] like Figure 9 As shown, the first liquid line 31 has a first quick-release connector 301 (e.g., a female quick-release connector) at one end (the end away from the engine side). The first quick-release connector 301 can be manually disassembled by an operator. The first quick-release connector 301 enables quick connection and disconnection between the engine fuel line and the aircraft fuel system supply line (fuselage-side fuel line). The first quick-release connector 301 is connected to a firewall-side quick-release connector 71 (e.g., a male quick-release connector) located on the vertical firewall 10. For example, the firewall-side quick-release connector 71 is located at the other end of the fuselage-side fuel line (the end closer to the engine side) and is installed on the vertical firewall 10 via fasteners such as screws at its flange made of refractory material. After tightening the screws, a fire-retardant sealant is applied to protect the structural integrity of the vertical firewall 10 and prevent flame penetration through the firewall structure. Preferably, at least a portion of the first liquid line 31 uses a flexible tube to accommodate deformation of the line when disconnected. In this embodiment, the first fluid line 31 has a rigid pipe portion 312 and a flexible pipe portion 313 sequentially extending from the first quick-release connector 301 toward the engine side. The rigid pipe portion 312 can ensure a safe clearance when there are many nearby systems and components. By installing the fuel line, which has a relatively high maintenance frequency, at the vertical firewall 10 via the first quick-release connector 301, the number of fuel line joints can be reduced, thereby suppressing the risk of fuel line leakage.

[0044] Each of the second liquid lines 32 to 37 has a fastening fitting 302 at one end (see...). Figure 10 Fastening joint 302 is, for example, a mechanical joint such as a flange joint that is crimped to one end of the flexible tube portion 304 of the second liquid line 32-37 during manufacturing (corresponding to...). Figure 3(Referring to the "flange separation" in the text). The fastening joint 302 is secured to the vertical firewall 10. For example, the second liquid lines 32-37 are connected to the nut joint 73 at the other end of the liquid line on the fuselage side via a threaded structure at the fastening joint 302. Preferably, the fastening joint 302 has a triangular flange 3021 made of refractory material, and is secured to the vertical firewall 10 at the flange 3021 by fasteners such as screws. After tightening the screws, a fire-retardant sealant is applied to protect the structural integrity of the vertical firewall 10 (corresponding to...). Figure 3 The "sealed frame" design prevents flame penetration through the firewall structure. Because flange 3021 has a triangular outer contour, it easily reduces the area occupied by pipe joints, especially when there are multiple second liquid lines arranged adjacent to each other, thereby further reducing the design requirements for hanging width. More preferably, the corners of the aforementioned triangle are rounded or have their sharp points cut off.

[0045] Each of the second fluid lines 32-37 has a second quick-release connector 303 (e.g., a female quick-release connector) at its other end. The second quick-release connector 303 is located in the finger-shaped cover area 1 at the connection between the nacelle 2 and the sling 20, which is forward of the vertical firewall 10. The second quick-release connector 303 can be manually disassembled by an operator. The second quick-release connector 303 enables quick connection and disconnection between the second fluid lines 32-37 (which are hydraulic lines) and the engine-side fluid lines (engine-side hydraulic lines).

[0046] In this embodiment, the second quick-release connector 303 is connected to the quick-release connector 72 (e.g., a male quick-release connector) on the separation wall side of the pipeline separation wall 40, thereby connecting to the engine-side hydraulic pipeline. For example, the quick-release connector 72 on the separation wall side is provided at one end of the engine-side hydraulic pipeline and is installed on the pipeline separation wall 40 at its flange via fasteners such as screws. Preferably, at least a portion of each of the second liquid pipelines 32-37 uses flexible tubing to accommodate pipeline deformation when disconnected. In this embodiment, each of the second liquid pipelines 32-37 has a portion 304 using flexible tubing (see...). Figure 10 ).

[0047] The piping separation wall 40 is positioned separately from the vertical firewall 10 within the finger-shaped enclosure area 1 at the connection point between the nacelle 2 and the pylon 20, located forward of the vertical firewall 10. Multiple piping separation walls 40 may be provided. In this embodiment, as... Figure 2 , Figure 6 and Figure 10As shown, the pipe separation wall 40 includes a first pipe separation wall 41 for installing the second quick-release connectors 303 of the second liquid pipes 32-34 and a second pipe separation wall 42 for installing the second quick-release connectors 303 of the second liquid pipes 35-37. For example, the first pipe separation wall 41 and the second pipe separation wall 42 are fixed at different positions on the support frame 80. The support frame 80 is located on the front side of the hanger 20 and is fixed to the fan nacelle casing 90.

[0048] In addition, the aircraft engine system docking multi-separation surface device 100 includes a cable group 51 consisting of multiple EWIS cables and another cable group 52 consisting of multiple EWIS cables as a cable group 50 consisting of multiple EWIS cables (see Figure 7 A cable group 51 and another cable group 52 pass through the vertical firewall 10 at a cable group through-hole 131 (equivalent to the "through-hole" of the present invention) and are sealed between the through-hole 131 and the cable group through-hole 131 with fire-resistant sealing material. Each EWIS cable of the cable group 51 has a cable connector 511 at the other end, which is disposed in the finger cover area 1 for connection of the engine-side EWIS cable. Each EWIS cable of the other cable group 52 has another cable connector 521 at the other end, which is also disposed in the finger cover area 1 for connection of the engine-side EWIS cable.

[0049] In addition, such as Figure 2 As shown, the vertical firewall 10 is provided with a through hole 132 for a connector, which is used to install a connector for an EWIS cable or another cable group consisting of multiple fuselage-side EWIS cables on the vertical firewall 10, and the connector is connected to the engine-side EWIS cable.

[0050] According to the multi-separation surface device 100 for aircraft engine system docking of the present invention, based on the scheme of using a vertical firewall 10 (first separation surface) between the pylon 20 and the fan nacelle, a second to X separation surface are added. The positions of hydraulic quick-release connectors (or other pipelines with quick-release connectors) and some EWIS cable connectors (e.g., quick-release connectors for liquid pipelines and EWIS cable connectors that do not require frequent disassembly for engine loading / unloading) on ​​the vertical firewall 10 are moved to the finger-shaped cover area at the connection between the nacelle and the pylon. The connectors on the vertical firewall are modified. Specifically, according to design requirements, some EWIS cable assemblies can directly pass through the first separation surface and be sealed on the vertical firewall using seals. Some hydraulic pipelines can pass through the vertical firewall (first separation surface) via flange connections. This scheme can significantly reduce the design width requirements of the pylon, reduce the aircraft's overall width, thereby reducing aerodynamic drag and improving the aircraft's economy. Compared with the prior art, the structure / design used in this invention is easy to implement, the device structure is lightweight, the maintenance space requirements are low, and maintenance operations are convenient. It reduces the width and weight of the pylon while meeting the maintenance requirements for engine loading / unloading. The aircraft engine system docking multi-separation surface device 100 of the present invention is particularly suitable for situations with dense pipelines passing through vertical firewalls.

[0051] The embodiments and variations of the present invention have been described above. However, it should be understood that this disclosure is not limited to the above embodiments and structures. This disclosure also includes various variations and modifications within the equivalent scope. In addition, various combinations and methods, and further combinations and methods that include only one element or more or less thereof, also fall within the scope and spirit of this disclosure.

Claims

1. A multi-separation surface device for docking an aircraft engine system, characterized in that, include: A vertical firewall is used to isolate the engine's fire zone from the hanger located in the non-fire zone, and the outer contour of the vertical firewall corresponds to the outer contour of the hanger. as well as The liquid piping is positioned forward of the vertical firewall, with one end installed on the vertical firewall and connected to the liquid piping on the fuselage side. The liquid pipeline includes at least one first liquid pipeline and at least one second liquid pipeline. The first liquid pipeline has a first quick-release connector at one end, and the first quick-release connector is connected to a quick-release connector located on the firewall side of the vertical firewall. The second liquid line has a fastening connector at one end and a second quick-release connector at the other end. The fastening connector is fastened to the vertical firewall, and the second quick-release connector is located in the finger-shaped cover area of ​​the nacelle and the sling connection on the front side of the vertical firewall.

2. The aircraft engine system docking multi-separation surface device according to claim 1, characterized in that, This includes a pipe separation wall, which is positioned separately from the vertical firewall within the finger-shaped enclosure area. The second quick-release connector is connected to the quick-release connector on the separation wall side of the pipeline separation wall, thereby connecting to the engine-side liquid pipeline.

3. The aircraft engine system docking multi-separation surface device according to claim 2, characterized in that, The pipeline separation wall is fixed to the support frame, and the support frame is fixed to the fan compartment casing.

4. The aircraft engine system docking multi-separation surface device according to claim 2, characterized in that, The pipeline separation wall is provided in multiple locations.

5. The aircraft engine system docking multi-separation surface device according to claim 1, characterized in that, At least a portion of the first liquid line and / or the second liquid line uses flexible tubing.

6. The aircraft engine system docking multi-separation surface device according to claim 1, characterized in that, The second liquid pipeline has multiple sections. The fastening joint has a triangular flange and is fastened to the vertical firewall at the flange by fasteners.

7. The aircraft engine system docking multi-separation surface device according to claim 6, characterized in that, The corners of the triangle are rounded or have their sharp points cut off.

8. The aircraft engine system docking multi-separation surface device according to claim 1, characterized in that, Includes a cable group consisting of multiple EWIS cables. The vertical firewall has a through hole, and the cable assembly passes through the vertical firewall at the through hole and is sealed between the cable assembly and the through hole by a fireproof sealing material.

9. The aircraft engine system docking multi-separation surface device according to claim 8, characterized in that, The EWIS cable has a cable connector at the other end, which is located in the finger-shaped cover area for connecting the engine-side EWIS cable.

10. The aircraft engine system docking multi-separation surface device according to claim 1, characterized in that, The first liquid line is a fuel line. The second liquid line is a hydraulic line.

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