Aero-engine unit body division method and structure

Abstract

The invention provides an aero-engine unit body division method and structure. The aero-engine unit body division method comprises the following steps that S1, part objects for unit body division are defined, and feature factors are obtained; s2, according to the characteristic factors, carrying out association relationship analysis among the parts; s3, a part incidence relation matrix is established according to the incidence relation between the parts, and according to the part incidence relation matrix, the internal part range of each unit body is obtained, and a unit body division scheme is formed; s4, a unit design scheme is completed according to the unit division scheme; and S5, verifying and evaluating the feasibility and rationality of the unit design scheme. The design requirements of the aero-engine unit body can be met, and the design capacity of the aero-engine unit body is effectively improved.

Description

Technical Field

[0001] The present invention relates to the technical field of aero-engines, and in particular to a method and structure for dividing an aero-engine unit. Background Art

[0002] Aircraft engines are power units for aircraft, drones, etc. To ensure the power, function, and maintainability requirements of the installed objects, advanced aircraft engines adopt a unit design, dividing the engine into several units with interchangeable functions, performance, and structures. When an engine fails, the engine's working capacity can be restored by replacing the faulty unit. Compared with the traditional maintenance and support model based on engine replacement, the unit design can improve maintenance flexibility, enhance maintainability, and reduce engine use costs.

[0003] The existing engine unit design lacks a systematic guidance method and mainly relies on qualitative analysis such as design experience, structural characteristics, and spatial distribution to divide components with similar structures and spatial proximity into one unit. The functional performance of some units is not independent, and the purpose of condition-based maintenance cannot be achieved. Summary of the invention

[0004] In view of this, the present invention provides an aircraft engine unit division method and structure, which forms an engine unit division scheme and design scheme through dimensional analysis such as structural relationship, functional performance relationship, and failure mode relationship. After analysis, evaluation, and verification, an engine unit structure is formed, thereby improving the engine unit design level and meeting the aircraft engine's requirements for unit design.

[0005] The present invention provides the following technical solution: a method for dividing an aero-engine unit, comprising the following steps:

[0006] S1. Clarify the component objects divided by the unit body and obtain the characteristic factors;

[0007] S2. Conduct correlation analysis between components based on the characteristic factors;

[0008] S3, establishing a component association relationship matrix according to the association relationship between components, obtaining the scope of components inside each unit and forming a unit division scheme according to the component association relationship matrix;

[0009] S4. Complete the unit design plan according to the unit division plan;

[0010] S5. Verify and evaluate the feasibility and rationality of the unit design scheme.

[0011] Furthermore, the step S2 comprises:

[0012] According to the formula Obtain the structural relationship index between components to clarify the structural influence relationship between components, where Nintf ij Represents the total number of interfaces between component i and component j; Cintf ijk represents the kth interface complexity between component i and component j; Ncons ij Represents the total number of constraints between component i and component j; Ccons ijm Represents the mth constraint strength between component i and component j, Cstrc ij Represents the structural relationship index between component i and component j.

[0013] Furthermore, the step S2 comprises:

[0014] According to the formula Obtain the functional performance relationship index between components to clarify the functional performance impact relationship between components, among which Pcap m Represents the importance of the mth function of the engine; Ncap m Represents the number of components required for the mth function in the components that serve as the basis for unit body division; Ccap mi Represents the correlation coefficient between the mth function and the ith component; Ccap mj Represents the correlation coefficient between the mth function and the jth component; Ccap ij Represents the functional performance relationship index between the i-th and j-th components.

[0015] Furthermore, the step S2 comprises:

[0016] According to the formula Obtain the failure mode relationship index to clarify the failure mode influence relationship of the components; among them, Pflm m Represents the criticality of the mth failure mode of the engine; Cflm mi represents the correlation coefficient between the mth failure mode and the ith component; Cflm mj represents the correlation coefficient between the mth failure mode and the jth component, Cflm ij Represents the failure relationship index between the ith component and the jth component.

[0017] Furthermore, the step S2 further includes:

[0018] According to the formula Cm ij =a·Cstrc ij 2 +b·Ccap ij 2 +c·Cflm ij 2 Conduct comprehensive evaluation and analysis of the relationship between components, among which Cm ijis the comprehensive evaluation coefficient of the relationship between component i and component j; a is the weight coefficient of the structural relationship index; b is the weight coefficient of the functional performance relationship index; c is the weight coefficient of the failure mode relationship index.

[0019] Furthermore, the step S3 comprises:

[0020] Establish the component association matrix according to the comprehensive evaluation analysis coefficient of the association relationship between components;

[0021] The component association matrix is ​​optimized to obtain the scope of components within each unit and form a unit division plan.

[0022] Furthermore, the step S4 comprises:

[0023] Complete the unit design plan according to the unit division plan.

[0024] Furthermore, the step S5 comprises:

[0025] Verify and evaluate the feasibility and rationality of the unit design scheme;

[0026] When the verification evaluation result does not meet the actual demand, steps S3 to S5 are repeated until the unit body design scheme meets the actual demand.

[0027] The present invention also provides an aircraft engine unit body division structure, which is obtained by using the above-mentioned aircraft engine unit body division method.

[0028] Furthermore, the aircraft engine unit division structure includes an interconnected fan unit, a core engine unit, a low-pressure turbine unit with a mixer and an inner cone, an outer casing unit, a mixing section unit, an afterburner cylinder and a nozzle unit and an accessory casing unit.

[0029] Compared with the prior art, the beneficial effects that can be achieved by at least one of the above-mentioned technical solutions adopted by the present invention include at least the following: the unit division method and structural scheme proposed in the present invention can meet the requirements of condition-based maintenance through unit replacement, improve the functional interchangeability and structural independence of engine units, meet the requirements of unit replacement required for condition-based maintenance to restore engine functional performance, meet the unit division and structural scheme design for condition-based maintenance of different aircraft engines, and effectively improve the condition-based maintenance capability of aircraft engines. BRIEF DESCRIPTION OF THE DRAWINGS

[0030] 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.

[0031] Figure 1 is a schematic diagram of a flow chart of an embodiment of the present invention;

[0032] Figure 2 It is a schematic diagram of unit body division and structural scheme;

[0033] Figure 3 It is a schematic diagram of the structural scheme of the air intake load-bearing frame unit and the fan rotor and stator unit;

[0034] Figure 4 It is a schematic diagram of the structural scheme of the low-pressure turbine unit;

[0035] Figure 5 It is a schematic diagram of the structural scheme of the low-pressure turbine rotor and stator unit and the turbine support unit;

[0036] Figure 6 It is a schematic diagram of the structural scheme of the unit body of the afterburner head device;

[0037] Figure 7 It is a schematic diagram of a certain aircraft engine component;

[0038] Figure 8 This is a schematic diagram of the engine's nine unit division scheme. DETAILED DESCRIPTION

[0039] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0040] 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.

[0041] like Figure 1 As shown, an embodiment of the present invention provides a method for dividing an aircraft engine unit, comprising the following steps:

[0042] S1. Clarify the component objects divided by the unit body and obtain the characteristic factors;

[0043] S2. Conduct correlation analysis between components based on characteristic factors;

[0044] S3, establishing a component association relationship matrix according to the association relationship between components, obtaining the scope of components inside each unit and forming a unit division scheme according to the component association relationship matrix;

[0045] S4. Complete the unit design plan according to the unit division plan;

[0046] S5. Verify and evaluate the feasibility and rationality of the unit design scheme.

[0047] The present invention can meet the requirements of condition-based maintenance through unit replacement, improve the functional interchangeability and structural independence of engine units, meet the requirements of unit replacement required for condition-based maintenance to restore engine functional performance, and can meet the unit division and structural scheme design for condition-based maintenance of different aircraft engines, effectively improving the condition-based maintenance capabilities of aircraft engines.

[0048] Among them, step S1 is specifically as follows: clarify the unit body division structural objects and their characteristic factors, preliminarily clarify the main components and accessories of the engine according to the engine configuration and scheme design results, and sort out their structural characteristics, spatial distribution, functional allocation, performance indicators, fault modes, failure analysis and other characteristic factors to support subsequent work.

[0049] The structural analysis method mainly analyzes the spatial relationship, interface coordination, assembly relationship, assembly route influence, etc. between components to clarify the structural influence between components.

[0050] For the N parts of the engine participating in the unit body division, the structural relationship index between the i-th part and the j-th part is defined as Cstrc ij , the above step S2 specifically includes:

[0051] According to the formula Obtain the structural relationship index between components to clarify the structural influence relationship between components, where Nintf ij Represents the total number of interfaces between component i and component j; Cintf ijk represents the kth interface complexity between component i and component j; Ncons ij Represents the total number of constraints between component i and component j; Ccons ijm Represents the mth constraint strength between component i and component j.

[0052] The functional performance analysis method mainly analyzes the mapping relationship between components and functional performance, the functional coupling between components, the requirements of functional realization principles on components, etc., to clarify the impact relationship between functional performance of components.

[0053] According to all Ncap functions of the engine, define the functional performance relationship index Ccap between component i and component j ij The above step S2 specifically includes:

[0054] According to the formula Obtain the functional performance relationship index between components to clarify the functional performance impact relationship between components, among which Pcap m Represents the importance of the mth function of the engine; Ncap m Represents the number of components required for the mth function in the components that serve as the basis for unit body division; Ccap mi Represents the correlation coefficient between the mth function and the ith component; Ccap mj Represents the correlation coefficient between the mth function and the jth component; Ccap ij Represents the strength of the relationship between the functional performance of the i-th and j-th components.

[0055] The failure mode analysis method mainly analyzes the failure mode of components, influencing factors, functional hazard analysis, failure causes, etc., and clarifies the influence relationship of component failure mode.

[0056] According to all Nflm failure modes of the engine, the relationship index of the failure mode between component i and component j is defined as Cflm ij , then the above step S2 includes:

[0057] According to the formula Obtain the failure mode relationship index to clarify the failure mode influence relationship of the components; among them, Pflm m Represents the criticality of the mth failure mode of the engine; Cflm mi represents the correlation coefficient between the mth failure mode and the ith component; Cflm mj Represents the correlation coefficient between the mth failure mode and the jth component.

[0058] Further, according to the formula Cm ij =a·Cstrc ij 2 +b·Ccap ij 2 +cCflm ij 2 Conduct comprehensive evaluation and analysis of the relationship between components, among which Cm ijis the comprehensive evaluation coefficient of the relationship between component i and component j; a is the weight coefficient of the structural relationship index; b is the weight coefficient of the functional performance relationship index; c is the weight coefficient of the failure mode relationship index.

[0059] Step S3 includes:

[0060] Establish the component association matrix according to the comprehensive evaluation analysis coefficient of the association relationship between components;

[0061] The component association matrix is ​​optimized to obtain the scope of components within each unit and form a unit division plan.

[0062] Among them, the optimization operation is a structural partitioning multi-factor comprehensive optimization method. According to the principle of relative structural independence, the engine is initially divided into several spatial regions. The component composition, functional performance distribution, failure mode and influencing factors of the region are analyzed. The unit body with relatively closed functional performance, relatively independent and complete structure, and similar failure mode and influencing factors is identified with the region as the object, forming a regional unit body definition and combining them to form a unit body division.

[0063] Step S4 includes:

[0064] The unit design plan is completed according to the unit division plan. The adjustment method is to adjust the unit division plan based on the unit division identified by the area, through the interface design between the units, and comprehensively consider the processability, accessibility, ergonomics and other factors of the replacement process.

[0065] Step S5 includes:

[0066] Verify and evaluate the feasibility and rationality of new unit design solutions;

[0067] When the verification evaluation result does not meet the actual demand, steps S3 to S5 are repeated until the unit body design scheme meets the actual demand.

[0068] Based on the target scenario and maintenance mode of condition-based maintenance, the new unit design scheme is evaluated from the dimensions of maintenance scheme design, process simulation, human-machine efficiency analysis, etc., and maintainability tests are carried out to verify and optimize the divisions.

[0069] Reference Figures 2 to 6 As shown, the present invention also provides an aircraft engine unit division structure, which is obtained by an aircraft engine unit division method. The aircraft engine unit division structure includes a fan unit 1, a core engine unit 2, a low-pressure turbine unit 3 with a mixer and an inner cone, an outer casing unit 4, a mixing section unit 5, a booster cylinder and nozzle unit 6 and an accessory casing unit 7 that are interconnected.

[0070] Specifically, the fan unit 1 includes an air intake load-bearing frame unit 101, a fan rotor 102, a fan stator 103, and external accessories and pipelines.

[0071] The core engine unit 2 includes an intermediate casing 201, a 2# bearing seat including a 2# bearing 202, a central transmission including a 3# fulcrum bearing 203, a high-pressure compressor rotor 204, a high-pressure compressor stator 205, a main combustion chamber 206, a high-pressure turbine guide vane 207, a high-pressure turbine rotor 208, core engine pipelines, etc.

[0072] The low-pressure turbine unit 3 with a mixer and an inner cone comprises a low-pressure turbine rotor 301 , a low-pressure turbine guide vane 302 , a turbine rear support 303 , an afterburner mixer 304 , and an afterburner inner cone 305 .

[0073] The outer casing unit body 4 includes an outer casing 401, a reinforcement ring 402, and accessories and pipelines installed on the outer casing.

[0074] The mixing section unit 5 comprises an afterburner mixing section casing 501, afterburner fuel supply pipeline and nozzle 502, a stabilizer 503 and installed accessories and pipelines.

[0075] The booster cylinder and nozzle unit 6 includes the booster cylinder 601 and the nozzle 602, and the related pipelines and accessories for installation.

[0076] The accessory casing unit 7 comprises an accessory casing 701, an oil tank 702 and related accessories and pipelines installed on the accessory casing.

[0077] Preferably, the air intake load-bearing frame 101 in the fan unit 1 serves as the air intake load-bearing frame unit 8, and the fan rotor 102 and the fan stator 103 can serve as the fan rotor-stator unit 9, so as to adapt to the maintenance and support modes of different engine configurations.

[0078] Furthermore, the low-pressure turbine unit 3 with a mixer and an inner cone can be composed of a low-pressure turbine guide vane 32 , a low-pressure turbine rotor 31 , and a turbine rear support 33 to form a low-pressure turbine unit 10 .

[0079] The low-pressure turbine rotor 301 and the low-pressure turbine guide vane 302 in the low-pressure turbine unit body 10 can constitute a low-pressure turbine rotor and stator unit body 11, and the turbine support 303 can serve as a rear-bearing casing unit body 12.

[0080] The afterburner mixer 304, the afterburner inner cone 305 and the mixing section unit 5 can form a afterburner head device unit 13, which is suitable for engine modular development and replacement.

[0081] The following is an example with reference to a specific embodiment:

[0082] like Figure 7As shown in the figure, according to the design results of a turbofan engine scheme, the components within the unit body division range are identified. Taking into account the strong internal correlation of some components, they are no longer split, such as the fan discs and blades at various stages are not considered.

[0083] The structural objects and characteristic factors of the unit body division are clarified. According to the engine configuration and scheme design results, the main components and accessories of the engine are preliminarily clarified, and their structural characteristics, spatial distribution, functional allocation, performance indicators, failure modes, failure analysis and other characteristic factors are sorted out to support subsequent work. See Table 1 for details.

[0084] Table 1 Schematic diagram of aircraft engine characteristic factors

[0085]

[0086]

[0087] The structural analysis method quantitatively analyzes the structural influence between parts based on the interface coordination, structural relationship, assembly constraints and other factors between parts. The calculation results of the structural analysis method of a certain engine are shown in Table 2:

[0088] Table 2 Correlation coefficient of a certain engine structure

[0089]

[0090] Similarly, the calculation of the functional correlation coefficient and the failure mode correlation coefficient is completed, and finally the correlation coefficient matrix between components is obtained as shown in Table 3:

[0091] Table 3 Correlation coefficients between engine components

[0092]

[0093] A multi-factor comprehensive optimization method based on structural partitioning divides the engine into several units according to the principle of relative structural independence, and optimizes according to the internal correlation matrix of the unit to obtain the engine unit division with close internal correlation and loose relationship between units.

[0094] According to different scene objectives, considering the unit division of the target engine, 7 and 9 units are formed (see Figure 8 The unit division scheme is shown in the figure, and the unit interface design and evaluation are completed to meet the unit design needs.

[0095] 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 method for dividing an aircraft engine unit, characterized in that: The following steps are involved: S1. Clarify the component objects divided by the unit body and obtain the characteristic factors; S2. Conduct correlation analysis between components based on the characteristic factors; S3, establishing a component association relationship matrix according to the association relationship between components, obtaining the scope of components inside each unit and forming a unit division scheme according to the component association relationship matrix; S4. Complete the unit design plan according to the unit division plan; S5. Verify and evaluate the feasibility and rationality of the unit design scheme.

2. The method for dividing an aircraft engine unit according to claim 1, characterized in that: The step S2 comprises: According to the formula Obtain the structural relationship index between components to clarify the structural influence relationship between components, where Nintf ij Represents the total number of interfaces between component i and component j; Cintf ijk represents the kth interface complexity between component i and component j; Ncons ij Represents the total number of constraints between component i and component j; Ccons ijm Represents the mth constraint strength between component i and component j, Cstrc ij Represents the structural relationship index between component i and component j.

3. The method for dividing an aircraft engine unit according to claim 2, characterized in that: The step S2 comprises: According to the formula Obtain the functional performance relationship index between components to clarify the functional performance impact relationship between components, among which Pcap m Represents the importance of the mth function of the engine; Ncap m Represents the number of components required for the mth function in the components that serve as the basis for unit body division; Ccap mi Represents the correlation coefficient between the mth function and the ith component; Ccap mj Represents the correlation coefficient between the mth function and the jth component; Ccap ij Represents the functional performance relationship index between the i-th and j-th components.

4. The method for dividing an aircraft engine unit according to claim 3, characterized in that: The step S2 comprises: According to the formula Obtain the failure mode relationship index to clarify the failure mode influence relationship of the components; among them, Pflm m Represents the criticality of the mth failure mode of the engine; Cflm mi represents the correlation coefficient between the mth failure mode and the ith component; Cflm mj represents the correlation coefficient between the mth failure mode and the jth component, Cflm ij Represents the failure relationship index between the ith component and the jth component.

5. The method for dividing an aircraft engine unit according to claim 4, characterized in that: The step S2 further comprises: According to the formula Cm ij =a·Cstrc ij 2 +b·Ccap ij 2 +c·Cflm ij 2 Conduct comprehensive evaluation and analysis of the relationship between components, among which Cm ij is the comprehensive evaluation coefficient of the relationship between component i and component j; a is the weight coefficient of the structural relationship index; b is the weight coefficient of the functional performance relationship index; c is the weight coefficient of the failure mode relationship index.

6. The method for dividing an aircraft engine unit according to claim 5, characterized in that: The step S3 comprises: Establish the component association matrix according to the comprehensive evaluation analysis coefficient of the association relationship between components; The component association matrix is ​​optimized to obtain the scope of components within each unit and form a unit division plan.

7. The method for dividing an aircraft engine unit according to claim 6, characterized in that: The step S4 comprises: Complete the unit design plan according to the unit division plan.

8. The method for dividing an aircraft engine unit according to claim 7, characterized in that: The step S5 comprises: Verify and evaluate the feasibility and rationality of the unit design scheme; When the verification evaluation result does not meet the actual demand, steps S3 to S5 are repeated until the unit body design scheme meets the actual demand.

9. An aircraft engine unit body division structure, obtained by using an aircraft engine unit body division method, characterized in that: The aircraft engine unit body division method is the aircraft engine unit body division method according to any one of claims 1 to 8.

10. The aircraft engine unit division structure according to claim 9, characterized in that: The aircraft engine unit division structure includes an interconnected fan unit, a core unit, a low-pressure turbine unit with a mixer and an inner cone, an outer casing unit, a mixing section unit, an afterburner cylinder, a nozzle unit and an accessory casing unit.

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