A method for laying external pipelines of an aeroengine oriented to modularization

Abstract

The present application provides a method for laying external pipelines of an aeroengine oriented to modularization, belonging to the technical field of aeroengines. The method includes preliminarily laying external pipelines according to the arrangement of engine accessories, the arrangement of external pipeline interfaces between the engine and the aircraft, the pipeline schematic diagram of the engine, and the electrical schematic diagram; re-dividing the unit bodies of the engine mainframe according to the arrangement of engine accessories, pipeline laying, and the difficulty coefficient of pipeline splitting to obtain new unit bodies; based on the interfaces of the new unit bodies and preset truncation rules, performing truncation design on the preliminarily laid pipelines, and fixing the pipeline interfaces for fixing the truncated pipelines on the unit body casing brackets; determining the positions of the remaining brackets according to the arrangement of engine accessories and preset bracket setting rules; and performing cable laying according to the positions of the engine-aircraft cable interfaces, the arrangement of engine accessories, and the laying situation of the truncated pipelines. The present application can reduce the assembly and inspection time of external pipelines in the whole-machine state and improve the assembly efficiency of the whole machine.

Description

Technical Field

[0001] The present application relates to the technical field of aero-engines, and particularly to a method for laying external pipelines of a modular aero-engine. Background Art

[0002] Generally, the method for laying external pipelines of an aero-engine relies on the overall layout design of the engine, mainly considering its functions, performance, reliability, and the maintainability of the pipelines themselves. When an aero-engine is designed and maintained strictly according to unit bodies, the general method for laying external pipelines of an aero-engine cannot meet the requirements of replacing engine unit bodies. Therefore, it is necessary to perform a matching and optimization combination design of modular external pipelines and aero-engine unit bodies, so as to achieve a complete unit body design of the aero-engine. Summary of the Invention

[0003] In view of this, the embodiments of the present application provide a method for laying external pipelines of a modular aero-engine, which improves the assembly efficiency of the external pipelines of the engine and facilitates the installation, repair, and maintenance of the engine unit body.

[0004] The embodiments of the present application provide a method for laying external pipelines of a modular aero-engine, and the method includes: preliminarily laying external pipelines according to the arrangement of engine accessories, the arrangement of external pipeline interfaces between the engine and the aircraft, the pipeline schematic diagram of the engine, and the electrical schematic diagram, where the pipelines include pipelines and cables;

[0005] Recombining and dividing the unit body of the engine main body according to the arrangement of engine accessories, the pipeline laying situation, and the pipeline splitting difficulty coefficient to obtain multiple new unit bodies of the engine;

[0006] Based on the unit body interfaces of each new unit body, determining the truncation positions of the preliminarily laid pipelines based on a preset truncation rule;

[0007] Based on each truncation position, fixing the pipeline interfaces for fixing the truncated pipelines on the brackets of the unit body casing;

[0008] Determining the distribution of the remaining bracket positions on the pipelines according to the arrangement of engine accessories and a preset bracket setting rule;

[0009] Laying cables according to the position of the engine-aircraft cable interface, the arrangement of engine accessories, and the pipeline laying situation after truncation.

[0010] According to a specific implementation manner of the embodiments of the present application, the influencing factors of the pipeline splitting difficulty coefficient include the axial length of the unit body, the outer diameter of the pipeline crossing unit bodies, and the axial length of the accessory interface and a certain interface of the engine unit body.

[0011] According to a specific implementation manner of an embodiment of the present application, the influencing factors of the pipeline splitting difficulty coefficient further include pipeline materials and the assembly relationship between unit bodies.

[0012] According to a specific implementation manner of an embodiment of the present application, the preset truncation rule includes:

[0013] When the pipeline is cross-interface connected into an accessory and meets the first preset condition, the pipeline is supported by setting a fulcrum at the interface and no truncation design is carried out;

[0014] When the pipeline is cross-interface connected into an accessory and meets the second preset condition, the pipeline is truncated within the unit body where the accessory is formed.

[0015] According to a specific implementation manner of an embodiment of the present application, the first preset condition is:

[0016] 10D n ≥L gJ ≥30D n ,

[0017] where D n is the outer diameter of the pipeline, and L gJ is the pipeline length between the unit body interface and the nearest fulcrum of the pipeline;

[0018] The second preset condition is:

[0019] L gJ >40D n .

[0020] According to a specific implementation manner of an embodiment of the present application, the method further includes:

[0021] When designing the external pipeline, adjust the positions of the remaining fulcrums of the pipeline and meet the following conditions:

[0022]

[0023] According to a specific implementation manner of an embodiment of the present application, the preset support setting rule includes:

[0024] Adjust the distance between adjacent fulcrums through the self-vibration frequency of the conduit, and the self-vibration frequency of the conduit meets the following conditions:

[0025] f n ≥1.25f u or 1.25≤0.8f d ,

[0026]

[0027] where f n is the self-vibration frequency of the conduit, and f uis the maximum rotational speed frequency of the engine rotor, f d is the idle speed frequency of the engine rotor, L is the distance between adjacent supports, E is the elastic modulus of the pipe material, J is the moment of inertia of the duct cross-section, g is the acceleration due to gravity, and G is the weight of the duct containing fluid.

[0028] According to a specific implementation manner of an embodiment of the present application, the laying of the cable includes:

[0029] Optimally arrange and organize the cable in bundles, keep each bundle of cables in a tree root shape, there is no intersection between cables, the installation and fixation of the cables are separated from the pipeline, and they are independently fixed at the roots in each unit body.

[0030] According to a specific implementation manner of an embodiment of the present application, the multiple new unit bodies include a fan unit body, a core engine unit body with an accessory case and an outer casing, a mixer unit body, and an afterburner nozzle unit body.

[0031] According to a specific implementation manner of an embodiment of the present application, the pipeline is selected as a flexible pipeline.

[0032] Beneficial effects:

[0033] In the method for laying external pipelines of an aero-engine oriented to modularization in the embodiment of the present application, by dividing the engine into unit bodies and modularizing the external pipelines based on the division of the unit bodies, the assembly and inspection of the external pipelines and the aero-engine unit bodies can be arranged in the previous unit body assembly process, thereby reducing the assembly and inspection time of the external pipelines in the whole machine state and improving the assembly efficiency of the whole machine.

[0034] At the same time, the matching of the modular external pipelines and the aero-engine unit bodies can realize the maintenance and replacement of the unit bodies without completely disassembling the engine into accessories and pipelines in the whole machine state. Description of the drawings

[0035] In order to more clearly illustrate the technical solutions in the embodiments of the present application, the drawings required to be used in the embodiments will be briefly introduced below. Obviously, the drawings in the following description are only some embodiments of the present application. For those of ordinary skill in the art, other drawings can be obtained based on these drawings without creative efforts.

[0036] Figure 1 is a flowchart of a method for laying external pipelines of an aero-engine oriented to modularization according to an embodiment of the present invention;

[0037] Figure 2 is a schematic diagram of the externally laid pipelines in the preliminary laying according to an embodiment of the present invention;

[0038] Figure 3 is a schematic diagram of pipeline truncation according to an embodiment of the present invention;

[0039] Figure 4 Schematic diagram of a pipeline interface with a positioning ring structure according to an embodiment of the present invention;

[0040] Figure 5 Schematic diagram of independent cable rooting and fixing according to an embodiment of the present invention.

[0041] In the figure: 1. First pipeline; 2. Second pipeline; 3. Fan unit body; 4. Core engine unit body with accessory casing and outer casing; 5. Mixer unit body; 6. Afterburner nozzle unit body; 7. First truncated pipeline; 8. Second truncated pipeline; 9. Third truncated pipeline; 10. Fourth truncated pipeline; 11. Fifth truncated pipeline; 12. Screw; 13. Cable; 14. Clamp. Detailed implementation manners

[0042] The embodiments of the present application will be described in detail below with reference to the accompanying drawings.

[0043] The following uses specific specific examples to illustrate the implementation manners of the present application. Those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation manners. Various details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, without conflict, the following embodiments and the features in the embodiments can be combined with each other. All other embodiments obtained by those of ordinary skill in the art based on the embodiments in the present application without creative efforts belong to the scope of protection of the present application.

[0044] It should be noted that the following describes various aspects of the embodiments within the scope of the appended claims. It should be obvious that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is illustrative only. Based on the present application, those skilled in the art should understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects described herein can be used to implement the device and / or practice the method. Additionally, this device and / or practice this method can be implemented using other structures and / or functionality in addition to one or more of the aspects described herein.

[0045] It should also be noted that the illustrations provided in the following embodiments only schematically illustrate the basic concept of the present application. The illustrations only show the components related to the present application, rather than being drawn according to the number, shape, and size of the components in actual implementation. The type, quantity, and ratio of each component in actual implementation can be arbitrarily changed, and the component layout type may also be more complex.

[0046] In addition, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0047] An embodiment of the present application provides a method for laying external pipelines of an aeroengine for modularization. The following will refer to Figures 1 to 5 for a detailed description.

[0048] In this embodiment, referring to Figure 1 , the method for laying external pipelines of an aeroengine for modularization specifically includes the following steps:

[0049] Step 1: Preliminarily lay external pipelines according to the layout of engine accessories, the layout of external pipeline interfaces between the aircraft and the engine, the engine pipeline schematic diagram, and the electrical schematic diagram. The pipelines include pipelines and cables 13.

[0050] Step 2: Recombine and divide the unit bodies of the engine main body according to the layout of engine accessories, the pipeline laying situation, and the pipeline splitting difficulty coefficient to obtain multiple new unit bodies of the engine.

[0051] Step 3: Based on the unit interfaces of each new unit body and a preset truncation rule, determine the truncation positions of the preliminarily laid pipelines.

[0052] Step 4: Fix the pipeline interfaces for fixing the truncated pipelines on the brackets of the unit body casing based on each truncation position.

[0053] Step 5: Determine the distribution of the remaining bracket positions on the pipeline according to the layout of engine accessories and a preset bracket setting rule.

[0054] Step 6: Lay the cable 13 according to the position of the aircraft-engine cable interface, the layout of engine accessories, and the pipeline laying situation after truncation.

[0055] During specific implementation, before performing Step 1, relevant aircraft-engine external pipeline interfaces on the engine are also determined to be set on each unit body of the engine and not on the unit interface (mounting edge) according to the required setting situation of the external pipeline interfaces of the aircraft. Refer to Figure 4The pipeline interface of the positioning ring structure uses connectors such as a clamp 14 and bolts to restrain its middle section and fix it on the bracket of the unit casing, locking the position of the interface, and the electrical interface is fixed on the unit casing with a bracket.

[0056] In one embodiment, the influencing factors of the pipeline disassembly difficulty coefficient include the axial length of the unit, the outer diameter of the pipeline across the unit, and the axial length of the accessory interface and a certain interface of the engine unit.

[0057] In specific implementation, the longer the axial length of the unit, the greater the difficulty of disassembling the unit pipeline; the larger the outer diameter of the pipeline across the unit, the greater the difficulty of disassembling the unit pipeline; the longer the axial length of the accessory interface and a certain interface of the engine unit, the easier it is to perform truncation design, and the smaller the difficulty of disassembling the unit pipeline.

[0058] Furthermore, the influencing factors of the pipeline disassembly difficulty coefficient also include the pipeline material and the assembly relationship between the units.

[0059] In specific implementation, considering the three factors of the layout of engine accessories, the pipeline laying situation, and the pipeline disassembly difficulty coefficient, the unit can generally be re-divided into: a fan unit, a core unit with an accessory casing and an outer casing, a mixer unit, an afterburner nozzle unit, etc.

[0060] In one embodiment, the preset truncation rule includes:

[0061] When the pipeline connects to an accessory across an interface and meets the first preset condition, the pipeline is supported by setting a fulcrum at the interface and no truncation design is performed;

[0062] When the pipeline connects to an accessory across an interface and meets the second preset condition, the pipeline is truncated within the unit where the accessory is located.

[0063] In one embodiment, the first preset condition is:

[0064] 40D n ≥LgJ≥30D n ,

[0065] where D n is the outer diameter of the pipeline, and L gJ is the pipeline length between the unit interface and the nearest fulcrum of the pipeline;

[0066] The second preset condition is:

[0067] L gJ >40D n 。

[0068] Furthermore, the method further includes:

[0069] When designing the external pipeline, adjust the positions of the remaining supports of the pipeline and meet the following conditions:

[0070]

[0071] During specific implementation, determine the truncation position of the pipeline through the constraints of the first preset condition and the second preset condition, as well as the constraints on the positions of the remaining supports of the pipeline. After determining the truncation position, fix the pipeline interface with a positioning ring structure on the bracket of the unit casing using connecting parts such as clamp bolts to lock the position of the interface. After determining the supports, consider the arrangement of accessories and the preset support setting rules, and adjust L through the self-vibration frequency f of the conduit u to further determine the distribution of the positions of the remaining supports on the pipeline.

[0072] Furthermore, the preset support setting rules include:

[0073] Adjust the distance between adjacent supports through the self-vibration frequency of the conduit, and the self-vibration frequency of the conduit satisfies the following conditions:

[0074] f n ≥1.25f u Or 1.25 ≤ 0.8f d ,

[0075]

[0076] wherein, f n is the self-vibration frequency of the conduit, f u is the maximum rotational speed frequency of the engine rotor, f d is the idle speed frequency of the engine rotor, L is the distance between adjacent supports, E is the elastic modulus of the pipe material, J is the moment of inertia of the conduit cross-section, g is the acceleration due to gravity, and G is the weight of the conduit containing fluid.

[0077] Preferably, when the pipeline related to the aircraft and engine is connected to the pipeline on the core engine unit, it can be designed as a flexible pipeline. For example, a non-metallic hose can be used.

[0078] In one embodiment, the laying of the cable 13 includes:

[0079] Optimize and sort the cable in bundles, keep each bundle of cable 13 in a tree root shape, there is no intersection between cable 13 and cable 13, the installation and fixation of cable 13 are separated from the pipeline, and it takes root and is fixed independently in each unit.

[0080] In this embodiment, by discretizing the cable 13 and the pipeline, the independence of the final assembly of the cable 13 is ensured, which is convenient for the final assembly and disassembly of the pipeline system of the whole machine.

[0081] In one embodiment, the multiple new unit bodies include a fan unit body, a core unit body with an accessory case and an outer casing, a mixer unit body, and an afterburner nozzle unit body.

[0082] In one embodiment, the pipeline is selected as a flexible pipeline.

[0083] The method of the present application will be described in detail below with a specific embodiment, including the following steps:

[0084] Referring to Figure 1 , the laying of the external pipelines of the modular aeroengine specifically includes the following steps:

[0085] S1. According to the setting situation of the external pipeline interfaces of the aircraft, determine the relevant aircraft-engine external pipeline interfaces on the engine and set them on each unit body of the engine and not on the unit body interface (mounting flange). Referring to Figure 4 For the pipeline interface of the positioning ring structure, use connecting parts such as clamps and bolts to constrain its middle section to fix it on the bracket of the unit body casing, lock the position of the interface, and fix the electrical interface on the unit body casing with a bracket.

[0086] S2. According to the layout of the engine accessories, the layout of the aircraft-engine external pipeline interfaces, the engine pipeline schematic diagram, and the electrical schematic diagram, preliminarily lay the external pipelines. At this time, it is a general method for laying the external pipelines of an aeroengine. Based on the overall layout design of the engine, referring to Figure 2 the design of the first pipeline 1 and the second pipeline 2 and other pipelines shown. Here, the pipelines are pipelines that have not been subjected to truncation design.

[0087] S3. According to the layout of the engine accessories and the pipeline laying situation, recombine the unit bodies of the engine main body (excluding external accessories and pipelines, etc.). Referring to Figure 3 As shown, the unit bodies of the engine can be re-divided into: a fan unit body 3, a core unit body 4 with an accessory case and an outer casing, a mixer unit body 5, an afterburner nozzle unit body 6, etc. (indicated by the dotted line division).

[0088] S4. According to the re-divided unit body interfaces, perform truncation design on the pipelines.

[0089] S41. Referring to Figure 3 , for the first pipeline 1 (the pipeline in step S2) connecting the fan unit body 3 and the core unit body 4 with an accessory case and an outer casing, after being judged by the preset truncation rule, the first pipeline 1 needs to be truncated to form a first truncated pipeline 7 and a second truncated pipeline 8 so that when the unit body is disassembled, the pipeline can also be adjusted adaptively; and the pipeline interfaces for connecting the two truncated pipelines are set inside the front interface of the core unit body 4 with an accessory case and an outer casing. Referring to Figure 4The pipeline interface with a positioning ring structure uses connectors such as a clamp 14 and bolts to restrain the middle section of the pipeline interface so that it is fixed on the bracket of the unit casing, locking the position of the interface.

[0090] S42. The pipelines on the fan unit 3 are fixed on the surface mounting structure of the unit casing through connectors such as clamp bolts, and the second truncated pipeline 8 connected to the core engine unit 4 of the accessory casing and the outer casing is designed as a flexible pipeline (such as a non-metallic hose).

[0091] S43. Refer to Figure 3 , the second pipeline 2 (through the mixer unit 5) (preliminary scheme) on the core engine unit 4 of the accessory casing and the outer casing, which is connected to the afterburner nozzle unit 6, needs to be truncated to form the third truncated pipeline 9, the fourth truncated pipeline 10 and the fifth truncated pipeline 11 after the judgment of the preset truncation rule, and the pipeline interfaces are respectively arranged inside the rear interface of the core engine unit 4 of the accessory casing and the outer casing and inside the front interface of the afterburner nozzle unit 6. Refer to Figure 4 The pipeline interface with a positioning ring structure uses connectors such as a clamp 14 and bolts to restrain its middle section so that it is fixed on the bracket of the unit casing, locking the position of the interface. The mixer unit 5 serves as a transition to provide a mounting structure to support the pipeline (the fourth truncated pipeline 10).

[0092] S5. According to the positions of the aircraft-engine cables interfaces, the positions of the engine accessories, and the pipeline laying conditions, optimize and arrange the cable bundles, keeping each cable bundle 13 in a tree root shape, without crossing between the cables 13, separating the installation and fixation of the cables 13 from the pipelines, and independently taking root and fixing inside each unit. Refer to Figure 5 , through the screw 12, fix the clamp 14 for fixing the cable 13 on the support 15 on the casing wall surface.

[0093] The method for laying the external pipelines of an aeroengine provided by this application, on the basis of the general pipeline laying method, through optimization methods such as the recombination of unit bodies, the design of pipeline truncation, the adjustment of the support position of the fulcrum, and the independent rooting and fixing of the tree root-shaped cables, realizes the modular design of the external pipelines of the aeroengine on the basis of the design of the engine unit body, significantly improves the assembly efficiency of the external pipelines of the engine, and is convenient for the installation, maintenance and repair of the engine unit body.

[0094] The above is only the specific implementation manner of this application, but the protection scope of this application is not limited thereto. Any changes or substitutions that can be easily thought of by those skilled in the art within the technical scope disclosed by this application should be covered within the protection scope of this application. Therefore, the protection scope of this application should be subject to the protection scope of the claims.

Claims

1. A method for laying external pipelines of an aero-engine oriented to modularization, characterized in that The method includes: Preliminarily laying external pipelines according to the layout of the engine components and accessories, the layout of the external pipeline interfaces of the aircraft-engine, the engine pipeline schematic diagram, and the electrical schematic diagram, where the pipelines include pipes and cables; Recombining and dividing the unit bodies of the engine main unit according to the layout of the engine components and accessories, the pipeline laying situation, and the pipeline splitting difficulty coefficient to obtain multiple new unit bodies of the engine; Based on the unit interfaces of each new unit body, determining the truncation positions of the preliminarily laid pipelines based on a preset truncation rule; Based on each truncation position, fixing the pipeline interfaces for fixing the truncated pipelines on the brackets of the unit body casing; Determining the remaining bracket position distribution on the pipelines according to the layout of the engine components and accessories and the preset bracket setting rule; Laying the cables according to the aircraft-engine cable interface positions, the layout of the engine components and accessories, and the laid pipelines after truncation.

2. The method for laying external pipelines of an aeroengine oriented to modularization according to claim 1, wherein The influencing factors of the pipeline splitting difficulty coefficient include the axial length of the unit body, the outer diameter of the pipeline across unit bodies, and the axial length between the accessory interface and a certain interface of the engine unit body.

3. The method for laying external pipelines of an aero-engine oriented to modularization according to claim 2, wherein The influencing factors of the pipeline splitting difficulty coefficient also include the pipeline material and the assembly relationship between unit bodies.

4. The method for laying external pipelines of an aero-engine oriented to modularization according to claim 1, characterized in that, The preset truncation rule includes: When a pipeline crosses an interface to connect an accessory and meets the first preset condition, the pipeline is supported by setting a fulcrum at the interface without a truncation design; When a pipeline crosses an interface to connect an accessory and meets the second preset condition, the pipeline is truncated within the unit body where the accessory is located.

5. The method for laying external pipelines of an aero-engine oriented to modularization according to claim 4, wherein, The first preset condition is: 40D n ≥L gJ ≥30D n , where D n is the outer diameter of the pipeline, and L gJ is the pipeline length between the unit interface and the nearest fulcrum of the pipeline; The second preset condition is: L gJ > 40D n .

6. The method for laying external pipelines of an aeroengine oriented to modularization according to claim 5, characterized in that, The method further includes: When designing the external pipelines, adjusting the positions of the remaining fulcrums of the pipelines and meeting the following conditions:

7. The method for laying external pipelines of an aero-engine oriented to modularization according to claim 1, characterized in that, The preset bracket setting rule includes: Adjusting the distance between adjacent fulcrums through the self-vibration frequency of the conduit, and the self-vibration frequency of the conduit meets the following conditions: f n ≥ 1.25f u or 1.25 ≤ 0.8f d , Among them, f n is the self-vibration frequency of the conduit, f u is the maximum rotational speed frequency of the engine rotor, f d is the idle speed frequency of the engine rotor, L is the distance between adjacent supports, E is the elastic modulus of the pipe material, J is the moment of inertia of the conduit cross-section, g is the acceleration due to gravity, and G is the weight of the conduit containing fluid.

8. The method for laying external pipelines of an aero-engine oriented to modularization according to claim 1, wherein The laying of the cables includes: Optimizing and arranging the cable bundles, keeping each cable bundle in a tree root shape, without crossing between cables, separating the installation and fixation of the cables from the pipelines, and independently taking root and fixing within each unit body.

9. The method for laying external pipelines of an aeroengine oriented to modularization according to claim 1, wherein The multiple new unit bodies include a fan unit body, a core engine unit body with an accessory casing and an outer casing, a mixer unit body, and an afterburner nozzle unit body.

10. The method for laying external pipelines of an aero-engine oriented to modularization according to claim 1, characterized in that, Flexible pipelines are selected for the pipelines.

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