Modularization-oriented aero-engine external pipeline laying method

Abstract

The invention provides a modularization-oriented aero-engine external pipeline laying method, and belongs to the technical field of aero-engines, and the method comprises the steps: preliminarily laying external pipelines according to the arrangement of engine accessories, the arrangement of flying engine external pipeline interfaces, an engine pipeline schematic diagram and an electrical schematic diagram; according to accessory arrangement, pipeline laying and pipeline splitting difficulty coefficients of the engine, unit bodies of the engine main engine are divided again, and new unit bodies are obtained; on the basis of the new unit body interface and a preset truncation rule, truncation design is conducted on the preliminarily laid pipeline, and a pipeline connector used for fixing the truncation pipeline is fixed to a unit body case support; according to engine accessory arrangement and preset support arrangement rules, the positions of remaining supports are determined; and laying the cable according to the position of the flying cable interface, the accessory arrangement of the engine and the laying condition of the cut-off pipeline. According to the invention, the assembly and inspection time of external pipelines in a complete machine state can be reduced, and the complete machine assembly efficiency is improved.

Description

Technical Field

[0001] The present application relates to the field of aero-engine technology, and in particular to a modular method for laying external pipelines of an aero-engine. Background Art

[0002] The general method of laying external pipelines for aircraft engines relies on the overall layout design of the engine, mainly considering its function, performance, reliability and the maintainability of the pipeline itself. When the aircraft engine is strictly designed and maintained as a unit, the general method of laying external pipelines for aircraft engines cannot meet the needs of engine unit replacement. Therefore, it is necessary to match and optimize the modular external pipelines with the aircraft engine unit to achieve a complete unit design for the aircraft engine. Summary of the invention

[0003] In view of this, an embodiment of the present application provides a modularized method for laying external pipelines of an aircraft engine, which improves the efficiency of assembling the external pipelines of the engine and facilitates the installation, repair and maintenance of the engine unit.

[0004] The embodiment of the present application provides a modularized method for laying external pipelines of an aircraft engine, the method comprising: preliminarily laying external pipelines according to the arrangement of engine components and accessories, the arrangement of external pipeline interfaces of the aircraft engine, the engine pipeline schematic diagram and the electrical schematic diagram, the pipelines comprising pipelines and cables;

[0005] According to the arrangement of engine components and accessories, the laying of pipelines and the difficulty coefficient of pipeline splitting, the unit body of the engine main engine is reassembled and divided to obtain multiple new unit bodies of the engine;

[0006] Based on the unit body interface of each new unit body and the preset truncation rule, the truncation position of the initially laid pipeline is determined;

[0007] Based on each cut-off position, a pipeline interface for fixing the cut-off pipeline is fixed on a bracket of the unit casing;

[0008] Determine the remaining bracket positions on the pipeline according to the layout of engine components and accessories and the preset bracket setting rules;

[0009] The cable is laid according to the position of the aircraft cable interface, the layout of the engine accessories and the laying of the pipeline after cutting.

[0010] According to a specific implementation method of an embodiment of the present application, factors affecting the difficulty coefficient of pipeline splitting include the axial length of the unit body, the outer diameter of the pipeline across the unit body, and the axial length of a certain interface between the accessory interface and the engine unit body.

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

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

[0013] The pipeline is connected across the interface to form an accessory. When the first preset condition is met, the pipeline is supported by setting a fulcrum at the interface without truncation design;

[0014] The pipeline is connected across the interface to form an accessory, and when the second preset condition is met, the pipeline is cut off within the unit body where the accessory is located.

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

[0016] 10D n ≥L gJ ≥30D n ,

[0017] Among them, D n is the outer diameter of the pipe, L gJ It is the length of the pipeline between the unit interface and the pipeline to its nearest support point;

[0018] The second preset condition is:

[0019] L gJ >40D n .

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

[0021] When designing external piping, adjust the positions of other piping support points and meet the following conditions:

[0022]

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

[0024] The distance between adjacent pivots is adjusted by the natural frequency of the conduit, and the natural frequency of the conduit satisfies the following conditions:

[0025] f n ≥1.25f u Or 1.25≤0.8f d ,

[0026]

[0027] Among them, f n is the natural frequency of the catheter, f uis the maximum speed frequency of the engine rotor, f d is the engine rotor slow speed frequency, L is the distance between adjacent support points, E is the elastic modulus of the pipe, J is the moment of inertia of the conduit section, g is the gravitational acceleration, and G is the weight of the fluid in the conduit.

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

[0029] The cable bundles are optimized and organized to keep each bundle in a tree-root shape, with no crossover between cables. The cable installation and fixation are separated from the pipelines, and they are independently rooted and fixed in each unit.

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

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

[0032] Beneficial effects:

[0033] The modular aircraft engine external pipeline laying method in the embodiment of the present application divides the engine into units and modularizes the external pipelines based on the division of the units, so that the assembly and inspection of the external pipelines and the aircraft engine units can be arranged in the preceding unit 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 modular external pipelines and aircraft engine units can realize the maintenance and replacement of the units without completely disassembling the engine into accessories and pipelines in the whole machine state. BRIEF DESCRIPTION OF THE DRAWINGS

[0035] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0036] Figure 1 A flowchart of a modularized aircraft engine external pipeline laying method according to an embodiment of the present invention;

[0037] Figure 2 A schematic diagram of an external pipeline preliminarily laid out according to an embodiment of the present invention;

[0038] Figure 3 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 rooting and fixing of cables according to an embodiment of the present invention.

[0041] In the figure: 1, first pipeline; 2, second pipeline; 3, fan unit; 4, core unit with accessory casing and outer casing; 5, mixer unit; 6, afterburner nozzle unit; 7, first cut-off pipeline; 8, second cut-off pipeline; 9, third cut-off pipeline; 10, fourth cut-off pipeline; 11, fifth cut-off pipeline; 12, screws; 13, cables; 14, clamps. DETAILED DESCRIPTION

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

[0043] The following describes the implementation methods of the present application through specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the contents 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 methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that, in the absence of conflict, the following embodiments and the features in the embodiments can be combined with each other. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0044] It should be noted that various aspects of the embodiments within the scope of the appended claims are described below. It should be apparent that the aspects described herein can be embodied in a wide variety of forms, and any specific structure and / or function described herein is merely illustrative. Based on the present application, it should be understood by those skilled in the art that an 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. In addition, other structures and / or functionalities other than one or more of the aspects described herein can be used to implement this device and / or practice this method.

[0045] It should also be noted that the illustrations provided in the following embodiments are only schematic illustrations of 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. In actual implementation, the type, quantity and proportion of each component may be changed at will, and the component layout may also be more complicated.

[0046] Additionally, in the following description, specific details are provided to facilitate a thorough understanding of the examples. However, it will be understood by those skilled in the art that the aspects described may be practiced without these specific details.

[0047] The present application embodiment provides a modularized method for laying external pipelines of an aircraft engine. Figures 1 to 5 Describe in detail.

[0048] In this embodiment, refer to Figure 1 The modularized aircraft engine external pipeline laying method specifically includes the following steps:

[0049] Step 1, preliminarily laying external pipelines according to the layout of 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, the pipelines include pipelines and cables 13;

[0050] Step 2: Recombine and divide the unit bodies of the engine main engine according to the arrangement of engine components and accessories, the laying of pipelines, and the difficulty coefficient of pipeline splitting to obtain multiple new unit bodies of the engine;

[0051] Step 3: Based on the unit body interface of each new unit body and the preset truncation rule, the truncation position of the initially laid pipeline is determined;

[0052] Step 4: Based on each cut-off position, a pipeline interface for fixing the cut-off pipeline is fixed on a bracket of the unit casing;

[0053] Step 5: Determine the distribution of the remaining bracket positions on the pipeline according to the layout of the engine components and accessories and the preset bracket setting rules;

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

[0055] In specific implementation, before step 1, it is also determined that the relevant external pipeline interfaces of the engine are set on each unit of the engine and are not on the unit interface (installation edge) according to the need to set the external pipeline interface of the aircraft. Figure 4The pipeline interface of the positioning ring structure uses a clamp 14, bolts and other connectors to constrain the middle section so that it is fixed on the bracket of the unit body casing, locking the position of the interface, and the electrical interface is fixed on the unit body casing with a bracket.

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

[0057] During specific implementation, the longer the axial length of the unit body, the more difficult it is to split the unit body pipeline; the larger the outer diameter of the pipeline across the unit body, the more difficult it is to split the unit body pipeline; the longer the axial length of a certain interface between the accessory interface and the engine unit body, the easier it is to perform truncation design, and the easier it is to split the unit body pipeline.

[0058] Furthermore, factors influencing the difficulty coefficient of pipeline disassembly also include pipeline materials and assembly relationships between unit bodies.

[0059] During the specific implementation, taking into account the three factors of engine component and accessory layout, pipeline laying and pipeline splitting difficulty coefficient, the unit can generally be redivided into: fan unit, core engine unit with accessory casing and outer casing, mixer unit and afterburner nozzle unit, etc.

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

[0061] The pipeline is connected across the interface to form an accessory. When the first preset condition is met, the pipeline is supported by setting a fulcrum at the interface without truncation design;

[0062] The pipeline is connected across the interface to form an accessory, and when the second preset condition is met, the pipeline is cut off within the unit body where the accessory is located.

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

[0064] 40D n ≥LgJ≥30D n ,

[0065] Among them, D n is the outer diameter of the pipe, L gJ It is the length of the pipeline between the unit interface and the pipeline to its nearest support point;

[0066] The second preset condition is:

[0067] L gJ >40D n .

[0068] Furthermore, the method further comprises:

[0069] When designing external piping, adjust the positions of other piping support points and meet the following conditions:

[0070]

[0071] In specific implementation, the truncation position of the pipeline is determined by the constraints of the first preset condition and the second preset condition, as well as the constraints of the positions of the remaining fulcrums of the pipeline. After the truncation position is determined, the pipeline interface with the positioning ring structure is fixed to the bracket of the unit casing with a clamp bolt and other connectors to lock the position of the interface. After the fulcrum is determined, the arrangement of the accessories and the preset bracket setting rules are considered, and the natural vibration frequency f of the duct is calculated. u Adjust L to further determine the position distribution of other brackets on the pipeline.

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

[0073] The distance between adjacent pivots is adjusted by the natural frequency of the conduit, and the natural frequency of the conduit satisfies the following conditions:

[0074] f n ≥1.25f u Or 1.25≤0.8f d ,

[0075]

[0076] Among them, f n is the natural frequency of the catheter, f u is the maximum speed frequency of the engine rotor, f d is the engine rotor slow speed frequency, L is the distance between adjacent support points, E is the elastic modulus of the pipe, J is the moment of inertia of the conduit section, g is the gravitational acceleration, and G is the weight of the fluid in the conduit.

[0077] Preferably, the pipelines related to the aircraft engine can be designed as flexible pipelines when connected to the pipelines on the core engine unit body, for example, using non-metallic hoses.

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

[0079] The cable bundles are optimized and organized to keep each bundle of cables 13 in a tree root shape, without any crossing between cables 13 , and the installation and fixation of cables 13 are separated from the pipelines, and are independently rooted and fixed in each unit body.

[0080] In this embodiment, the independence of the final assembly of the cable 13 is ensured by discrete cables 13 and pipelines, which facilitates the final assembly and disassembly of the entire pipeline.

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

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

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

[0084] Reference Figure 1 The external pipeline laying of modular aircraft engines specifically includes the following steps:

[0085] S1. According to the need to set up the external pipeline interface of the aircraft, determine to set the relevant external pipeline interface of the engine on each engine unit and not on the unit interface (installation edge). Figure 4 The pipeline interface of the positioning ring structure uses clamps, bolts and other connectors to constrain the middle section so that it is fixed on the bracket of the unit body casing, and the position of the interface is locked. The electrical interface is fixed to the unit body casing with a bracket.

[0086] S2. Preliminary external pipeline laying is performed based on the layout of engine components and accessories, the layout of external pipeline interfaces of the aircraft engine, the engine pipeline schematic diagram and the electrical schematic diagram. This is a general method for laying external pipelines of aircraft engines. Based on the overall layout design of the engine, refer to Figure 2 The pipeline designs shown are the first pipeline 1 and the second pipeline 2, and the pipelines here are pipelines without truncation design.

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

[0088] S4. According to the re-divided unit interface, the pipeline is truncation-designed.

[0089] S41. Reference Figure 3 The first pipeline 1 (pipeline in step S2) connecting the fan unit 3 and the core unit 4 with the accessory casing and the outer casing needs to be cut off to form a first cut-off pipeline 7 and a second cut-off pipeline 8 after the preset cut-off rule is judged, so that when the unit is disassembled, the pipeline can also be adaptively adjusted; and the pipeline interface for connecting the two cut-off pipelines is set in the front interface of the core unit 4 with the accessory casing and the outer casing, referring to Figure 4The pipeline interface of the positioning ring structure uses a clamp 14, bolts and other connecting parts to constrain the middle section of the pipeline interface so that it is fixed on the bracket of the unit body casing, thereby locking the position of the interface.

[0090] S42, the pipeline on the fan unit body 3 is fixed on the unit body casing surface mounting structure by means of connectors such as clamp bolts, and the second cut-off pipeline 8 connected to the core unit body 4 with accessory casing and outer casing is designed as a flexible pipeline (such as a non-metallic hose).

[0091] S43. Reference Figure 3 The second pipeline 2 (through the mixer unit 5) (preliminary solution) connected to the afterburner nozzle unit 6 on the core unit 4 with the accessory casing and the outer casing needs to be cut to form a third cut-off pipeline 9, a fourth cut-off pipeline 10 and a fifth cut-off pipeline 11 according to the judgment of the preset cut-off rule, and the pipeline interfaces are respectively arranged in the rear interface of the core unit 4 with the accessory casing and the outer casing and in the front interface of the afterburner nozzle unit 6, referring to Figure 4 The pipeline interface of the positioning ring structure uses a clamp 14, bolts and other connectors to constrain the middle section so that it is fixed on the bracket of the unit casing, locking the position of the interface, and the mixer unit 5 serves as a transition to provide an installation structure to support the pipeline (the fourth truncated pipeline 10).

[0092] S5. According to the position of the cable interface of the aircraft engine, the position of the engine accessories, and the laying of the pipeline, the cable bundles are optimized and arranged to keep each bundle of cables 13 in a tree root shape, without crossing between cables 13 and cables 13, and the installation and fixation of cables 13 are separated from the pipelines, and they are independently rooted and fixed in each unit body, refer to Figure 5 The clamp 14 for fixing the cable 13 is fixed to the support 15 on the wall of the casing by means of screws 12.

[0093] The modular aircraft engine external pipeline laying method provided in the present application is based on the general pipeline laying method. Through optimization methods such as unit reassembly, pipeline truncation design, fulcrum support position adjustment, and independent rooting and fixation of tree-like cables, on the basis of the engine unit design, a modular design of the aircraft engine external pipeline is achieved, which significantly improves the assembly efficiency of the engine external pipeline and facilitates the installation, repair and maintenance of the engine unit.

[0094] The above is only a specific implementation of the present application, but the protection scope of the present application is not limited thereto. Any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed in the present application should be included in the protection scope of the present application. Therefore, the protection scope of the present application shall be based on the protection scope of the claims.

Claims

1. A modularized method for laying external pipelines of an aircraft engine, characterized in that: The method comprises: According to the layout of 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, the external pipelines are preliminarily laid, and the pipelines include pipes and cables; According to the arrangement of engine components and accessories, the laying of pipelines and the difficulty coefficient of pipeline splitting, the unit body of the engine main engine is reassembled and divided to obtain multiple new unit bodies of the engine; Based on the unit body interface of each new unit body and the preset truncation rule, the truncation position of the initially laid pipeline is determined; Based on each cut-off position, a pipeline interface for fixing the cut-off pipeline is fixed on a bracket of the unit casing; Determine the remaining bracket positions on the pipeline according to the layout of engine components and accessories and the preset bracket setting rules; The cable is laid according to the position of the aircraft cable interface, the layout of the engine accessories and the laying of the pipeline after cutting.

2. The modularized aircraft engine external pipeline laying method according to claim 1, characterized in that: The factors affecting the difficulty coefficient of pipeline splitting include the axial length of the unit body, the outer diameter of the pipeline across the unit body, and the axial length of a certain interface between the accessory interface and the engine unit body.

3. The modularized aircraft engine external pipeline laying method according to claim 2 is characterized in that: The factors affecting the difficulty coefficient of pipeline disassembly also include pipeline materials and the assembly relationship between unit bodies.

4. The modularized aircraft engine external pipeline laying method according to claim 1, characterized in that: The preset truncation rules include: The pipeline is connected across the interface to form an accessory. When the first preset condition is met, the pipeline is supported by setting a fulcrum at the interface without truncation design; The pipeline is connected across the interface to form an accessory, and when the second preset condition is met, the pipeline is cut off within the unit body where the accessory is located.

5. The modularized aircraft engine external pipeline laying method according to claim 4, characterized in that: The first preset condition is: 40D n ≥L gJ ≥30D n , Among them, D n is the outer diameter of the pipe, L gJ It is the length of the pipeline between the unit interface and the pipeline to its nearest support point; The second preset condition is: L gJ >40D n 。 6. The modularized aircraft engine external pipeline laying method according to claim 5, characterized in that: The method further comprises: When designing external piping, adjust the positions of other piping support points and meet the following conditions:

7. The modularized aircraft engine external pipeline laying method according to claim 1, characterized in that: The preset bracket setting rules include: The distance between adjacent pivots is adjusted by the natural frequency of the conduit, and the natural frequency of the conduit satisfies the following conditions: f n ≥1.25f u Or 1.25≤0.8f d , Among them, f n is the natural frequency of the catheter, f u is the maximum speed frequency of the engine rotor, f d is the engine rotor slow speed frequency, L is the distance between adjacent support points, E is the elastic modulus of the pipe, J is the moment of inertia of the conduit section, g is the gravitational acceleration, and G is the weight of the fluid in the conduit.

8. The modularized aircraft engine external pipeline laying method according to claim 1, characterized in that: The laying of the cable comprises: The cable bundles are optimized and organized to keep each bundle in a tree-root shape, with no crossover between cables. The cable installation and fixation are separated from the pipelines, and they are independently rooted and fixed in each unit.

9. The modularized aircraft engine external pipeline laying method according to claim 1, characterized in that: The multiple new units include a fan unit, a core unit with an accessory casing and an outer casing, a mixer unit and an afterburner nozzle unit.

10. The modularized aircraft engine external pipeline laying method according to claim 1, characterized in that: The pipeline is a flexible pipeline.

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