Method, system and equipment for calculating contribution of technical solutions for aircraft engine components

Abstract

The present application discloses a method, system and device for calculating the contribution of the technical solution of an aero-engine component, which relates to the field of aviation project management. The method includes: obtaining the overall aerodynamic and thermal performance index of the aero-engine and the aerodynamic and thermal performance parameters of each component of the aero-engine in the overall technical solution during multiple design processes; establishing a scar model based on the overall aerodynamic and thermal performance index of the aero-engine and the aerodynamic and thermal performance parameters of each component of the aero-engine; obtaining the degree of improvement of the technical solution of each component on the overall aerodynamic and thermal performance of the aero-engine based on the scar model; establishing a double-layer complex network based on the overall aerodynamic and thermal performance index-technical solution-time-space coupling relationship based on Bayesian and complex network theory; calculating the contribution of the technical solution of each component based on the improvement and the double-layer complex network. The present application can provide technical support for improving the aerodynamic and thermal performance of the overall technical solution of an aero-engine.

Description

Technical Field

[0001] The present application relates to the field of aviation project management, and in particular to a method, system and device for calculating the contribution of a technical solution for an aviation engine component. Background Art

[0002] With the continuous development of the aviation industry, the research and development of the new generation of aircraft engines faces unprecedented challenges. In this process, there is an extremely complex coupling relationship between the multi-component and multi-disciplinary technical solutions of the engine, and the integration of different technical solutions has great uncertainty, which greatly increases the difficulty of evaluating the performance of the aerodynamic and thermal principle configuration of the aircraft engine under the overall scheme of multi-disciplinary and multi-component coupling. In addition, from the perspective of the multi-technical solution level such as the aircraft engine system level and the component level, in the long-term development process of the aircraft engine, the technical solutions at different levels show a high degree of reusability in this process, which makes the different technical solutions at different levels have different contributions to the improvement of the aerodynamic and thermal performance of the overall solution in the collaborative design of the aircraft engine. At the same time, the iterative update process of the aircraft engine is often accompanied by the emergence of breakthrough technical solutions, which inevitably leads to unreasonable contribution evaluation results. Therefore, under the framework of forward development of aircraft engine collaborative design, it is necessary to conduct in-depth research on how to accurately measure the contribution of different technical solutions to improving the aerodynamic and thermal performance of the overall solution of the aircraft engine, so as to realize the efficient coupling calculation and evaluation of the component-level technical solution and the overall engine solution in aerodynamic and thermal performance. At the same time, a set of scientific and reasonable evaluation methods are established to support the optimized collaborative design of aircraft engines under multidisciplinary constraints, and to provide technical support for improving the aerodynamic and thermal performance of the overall scheme in the optimized collaborative design of aircraft engines under multidisciplinary constraints. Summary of the invention

[0003] The purpose of this application is to provide a method, system and equipment for calculating the contribution of the technical solution of aircraft engine components, which can provide technical support for improving the aerodynamic and thermal performance of the overall technical solution of the aircraft engine.

[0004] To achieve the above objectives, this application provides the following solutions.

[0005] In a first aspect, the present application provides a method for calculating the contribution of a technical solution for an aircraft engine component, comprising the following steps.

[0006] An overall design process for obtaining an overall technical solution of an aircraft engine; the overall technical solution includes technical solutions for each component; and the overall design process includes multiple design processes.

[0007] The overall aerodynamic and thermal performance indicators of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine in the overall technical solution during multiple design processes are obtained.

[0008] A scar model is established according to the overall aerodynamic and thermal performance index of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine; the scar model includes: an overall one-dimensional simulation model of the aircraft engine and a three-dimensional simulation model of each component in the aircraft engine.

[0009] Based on the scar model, the degree to which the technical solutions of each component can improve the overall aerodynamic and thermal performance of the aircraft engine is obtained.

[0010] Based on Bayesian and complex network theories, a double-layer complex network is established according to the overall aerodynamic and thermal performance indicators-technical solutions-time-space coupling relationship; the upper layer of the double-layer complex network is the overall technical solution layer, and the lower layer of the double-layer complex network is the technical solution layer of each component; the nodes in the overall technical solution layer represent the overall technical solution; the nodes in the technical solution layer of each component represent the technical solution of each component.

[0011] The contribution of the technical solution of each component is calculated based on the improvement degree and the double-layer complex network.

[0012] Optionally, obtaining the degree of improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of each component based on the scar model specifically includes the following steps.

[0013] Based on the scar model, the aerodynamic thermodynamic conservation equations of the overall aerodynamic thermodynamic performance index and the aerodynamic thermodynamic conservation equations of the aerodynamic thermodynamic performance parameters of each component are solved to obtain the changes in the aerodynamic thermodynamic performance parameters of each component of the aircraft engine.

[0014] Based on the changes in the aerodynamic and thermal performance parameters of various aircraft engine components, the improvement degrees of different overall aerodynamic and thermal performance indicators are obtained.

[0015] Based on the improvement degree of different overall aerodynamic and thermal performance indicators, the improvement degree of the technical solutions of various components on the overall aerodynamic and thermal performance of the aircraft engine is obtained.

[0016] Optionally, the contribution of the technical solution of each component is calculated based on the improvement and the two-layer complex network, which specifically includes the following steps.

[0017] Based on the calculation formula of the importance of nodes in a double-layer complex network, the importance of the technical solution of each component is calculated respectively; the importance of the node includes degree centrality, core number, betweenness and eigenvector centrality.

[0018] Based on a double-layer complex network, the conditional probability of the associated technical solutions under the technical solution of the current component is calculated; the associated technical solutions are the technical solutions of other components associated with the technical solution of the current component.

[0019] Based on the conditional probability and the improvement of the overall aerodynamic and thermal performance of the aircraft engine, the comprehensive improvement of the technical solutions of each component on the overall aerodynamic and thermal performance of the aircraft engine is calculated.

[0020] Based on the comprehensive improvement of the technical solutions of each component to the overall aerodynamic and thermal performance of the aircraft engine and the importance of the technical solutions of each component, the contribution of the technical solutions of each component is calculated.

[0021] Optionally, a calculation formula for the degree of improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of the components is as follows.

[0022] .

[0023] .

[0024] in, For the The degree to which the technical solution of each component improves the overall aerodynamic and thermal performance of the aircraft engine; For the The technical solutions of each component have different overall aerodynamic and thermal performance indicators The degree of improvement; The overall aerodynamic and thermal performance index The weight parameter of .

[0025] Optionally, the calculation formula for the importance of the technical solutions of the components is as follows.

[0026] .

[0027] in, For the The importance of the node The node is Technical solutions for each component; Based on the analytic hierarchy process , , , The relative weight of For the The degree centrality of each node; For the The number of cores per node; For the The betweenness of the nodes; For the The eigenvector centrality of each node.

[0028] Optionally, the calculation formula for the comprehensive improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of the above-mentioned components is as follows.

[0029] .

[0030] in, For the The comprehensive improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of each component; For the The degree to which the technical solution of each component improves the overall aerodynamic and thermal performance of the aircraft engine; For the j The degree to which the technical solution of each component improves the overall aerodynamic and thermal performance of the aircraft engine; For the j The technical solution for each component is in The conditional probability of the technical solution of each component; j The technical solution for each component is Other technical solutions associated with the technical solution of a component.

[0031] Optionally, the calculation formula of the conditional probability is as follows.

[0032] .

[0033] in, Representative j The technical solution of each component is The number of times the technical solutions of the components are connected, among which the j The technical solution of each component is a related technical solution. The technical solution of a component is the technical solution of the current component; For the The degree centrality of the nodes.

[0034] Optionally, the calculation formula for the contribution of the technical solutions of the components is as follows.

[0035] .

[0036] in, For the The contribution of the technical solution of each component; For the The importance of the technical solution for each component; For the The technical solutions of each component can comprehensively improve the overall aerodynamic and thermal performance of the aircraft engine.

[0037] In a second aspect, the present application provides a system for calculating the contribution of technical solutions for aircraft engine components, including the following modules.

[0038] The design process acquisition module is used to acquire the overall design process of the overall technical solution of the aircraft engine; the overall technical solution includes the technical solutions of each component; and the overall design process includes multiple design processes.

[0039] The statistical quantity acquisition module is used to obtain the overall aerodynamic and thermal performance indicators of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine in the overall technical solution during multiple design processes.

[0040] The scar model generation module is used to establish a scar model according to the overall aerodynamic and thermal performance indicators of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine; the scar model includes: an overall one-dimensional simulation model of the aircraft engine and a three-dimensional simulation model of each component in the aircraft engine.

[0041] The comprehensive improvement calculation module is used to obtain the improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of each component based on the scar model.

[0042] A double-layer complex network generation module is used to establish a double-layer complex network based on Bayesian and complex network theories, according to the overall aerodynamic and thermal performance indicators-technical solutions-time-space coupling relationship; the upper layer of the double-layer complex network is the overall technical solution layer, and the lower layer of the double-layer complex network is the technical solution layer of each component; the nodes in the overall technical solution layer represent the overall technical solution; the nodes in the technical solution layer of each component represent the technical solution of each component.

[0043] A contribution calculation module is used to calculate the contribution of the technical solution of each component based on the improvement degree and the double-layer complex network.

[0044] In a third aspect, the present application provides a computer device, comprising: a memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the steps of the method for calculating the contribution of a technical solution for an aircraft engine component as described in any one of the above-mentioned methods.

[0045] According to the specific embodiments provided in this application, this application has the following technical effects.

[0046] The present application provides a method, system and device for calculating the contribution of technical solutions for aircraft engine components. By analyzing the overall design process of the overall technical solution of the aircraft engine, the contribution of multiple overall technical solutions can be calculated, so as to achieve efficient calculation and evaluation of the aerodynamic and thermal performance under the coupling of the overall and component-level technical solutions with the overall solution of the aircraft engine. Through the scar model of the overall one-dimensional simulation of the aircraft engine and the three-dimensional simulation data of the components, the aerodynamic and thermal design of the aircraft engine components and the overall are adjusted and optimized, and a double-layer complex network is established through Bayesian and complex network theories to calculate the contribution of the technical solution of each component, so as to provide technical support for improving the aerodynamic and thermal performance of the overall solution in the optimized collaborative design of aircraft engines under multidisciplinary constraints. BRIEF DESCRIPTION OF THE DRAWINGS

[0047] In order to more clearly illustrate the technical solutions in the embodiments of the present application or related technologies, 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.

[0048] Figure 1 This is an application environment diagram of a method for calculating the contribution of technical solutions for aircraft engine components in one embodiment of the present application.

[0049] Figure 2 A flowchart of a method for calculating the contribution of a technical solution to an aerospace engine component provided in one embodiment of the present application.

[0050] Figure 3 A schematic diagram of calculating the comprehensive improvement of the overall aerodynamic and thermal performance of an aircraft engine based on a scar model provided in one embodiment of the present application.

[0051] Figure 4 A schematic diagram of a double-layer complex network of an overall level technical solution and a component level technical solution provided for one embodiment of the present application.

[0052] Figure 5 A schematic diagram of a module for calculating the contribution of a technical solution for collaborative design of aircraft engines provided in one embodiment of the present application to the improvement of the aerodynamic and thermal performance of the overall solution.

[0053] Figure 6 A schematic diagram of establishing a scar model provided in one embodiment of the present application.

[0054] Figure 7 for Figure 6 Schematic diagram of the overall one-dimensional simulation model of the aircraft engine.

[0055] Figure 8A schematic diagram of the structure of a computer device provided in one embodiment of the present application. DETAILED DESCRIPTION

[0056] The following will be combined with the drawings in the embodiments of the present application to clearly and completely describe the technical solutions in the embodiments of the present application. Obviously, the described embodiments are only part of the embodiments of the present application, not all of the embodiments. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of this application.

[0057] In order to make the above-mentioned objects, features and advantages of the present application more obvious and easy to understand, the present application is further described in detail below with reference to the accompanying drawings and specific implementation methods.

[0058] The method for calculating the contribution of each component technical solution provided in the embodiment of the present application can be applied to Figure 1In the application environment shown, the terminal 102 communicates with the server 104 through a network. The data storage system can store data that the server 104 needs to process. The data storage system can be set up separately, integrated on the server 104, or placed on the cloud or other servers. The terminal 102 may send the overall aerodynamic and thermal performance indicators of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine in the overall technical solution during multiple design processes to the server 104. After receiving the overall aerodynamic and thermal performance indicators of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine in the overall technical solution during multiple design processes, the server 104 establishes a scar model based on the overall aerodynamic and thermal performance indicators of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine in the overall technical solution during multiple design processes, and obtains the comprehensive improvement of the technical solutions of each component to the overall aerodynamic and thermal performance of the aircraft engine based on the scar model; then, based on the Bayesian and complex network theories, a double-layer complex network is established according to the overall aerodynamic and thermal performance indicator-technical solution-time-space coupling relationship; finally, the contribution of the technical solution of each component is calculated based on the comprehensive improvement and the double-layer complex network. The server 104 can feed back the obtained contribution of the technical solutions of each component to the terminal 102. In addition, in some embodiments, the method for calculating the contribution of the technical solutions of aircraft engine components can also be implemented by the server 104 or the terminal 102 alone. For example, the terminal 102 can directly calculate the contribution of the technical solutions of each component of the aircraft engine to be calculated, or the server 104 can obtain the overall aerodynamic and thermal performance indicators of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine in the overall technical solution in multiple design processes from the data storage system, and calculate the contribution of the technical solutions of each component of the aircraft engine to be calculated.

[0059] The terminal 102 may be, but is not limited to, various desktop computers, laptop computers, smart phones, tablet computers, IoT devices, and portable wearable devices. The IoT devices may be smart speakers, smart TVs, smart air conditioners, smart vehicle-mounted devices, etc. The portable wearable devices may be smart watches, smart bracelets, head-mounted devices, etc. The server 104 may be implemented as an independent server or a server cluster consisting of multiple servers, or may be a cloud server.

[0060] In an exemplary embodiment, Figure 2 As shown, a method for calculating the contribution of technical solutions for aircraft engine components is provided. The method is executed by a computer device, and can be executed by a computer device such as a terminal or a server alone, or by a terminal and a server together. In the embodiment of the present application, the method is applied to Figure 1 The server 104 in the example is used for explanation, and the specific steps 1 to 6 are as follows.

[0061] Step 1: Obtain an overall design process of an overall technical solution of an aircraft engine; the overall technical solution includes technical solutions of various components; and the overall design process includes multiple design processes.

[0062] Specifically, the overall design process of the overall technical solution of the aircraft engine is an iterative process of collaborative design of the aircraft engine, and a technical solution that improves the overall aerodynamic and thermal performance of the aircraft engine will be generated during the iterative process.

[0063] Step 2: Obtain the overall aerodynamic and thermal performance indicators of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine in the overall technical solution during multiple design processes.

[0064] Specifically, the multiple design processes can be multiple times in the iterative update process of the aircraft engine. The multiple design processes are designed based on the expected values ​​of the overall aerodynamic and thermal performance indicators of the aircraft engine as the traction indicators. Among them, the overall aerodynamic and thermal performance indicators of the aircraft engine in the overall technical solution include: thrust F , Thermal efficiency of aircraft engines , aircraft engine propulsion efficiency , thrust-to-weight ratio , Unit fuel consumption rate sfc , engine total efficiency , Unit thrust Etc.; The aerodynamic and thermal performance parameters of various components of aircraft engines include: compressor pressure ratio, turbine inlet temperature, turbine expansion ratio, etc.

[0065] The multiple design processes may be the initial overall technical solution of the aircraft engine composed of the technical solutions of multiple components of the initial aircraft engine under the guidance of the overall aerodynamic and thermal performance indicators without collaborative design; or they may be the technical solution for improving the overall aerodynamic and thermal performance of the aircraft engine in the iterative process of collaborative design of the aircraft engine.

[0066] Step 3: Establish a scar model based on the overall aerodynamic and thermal performance indicators of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine; the scar model includes: an overall one-dimensional simulation model of the aircraft engine and a three-dimensional simulation model of each component in the aircraft engine.

[0067] Step 4: Based on the scar model, obtain the degree of improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of each component.

[0068] As an optional implementation, step 4 specifically includes the following steps 41 to 43.

[0069] Step 41: Based on the scar model, the aerodynamic thermodynamic conservation equation of the overall aerodynamic thermodynamic performance index and the aerodynamic thermodynamic conservation equation of the aerodynamic thermodynamic performance parameters of each component are solved to obtain the change in the aerodynamic thermodynamic performance parameters of each component of the aircraft engine.

[0070] Step 42: Based on the changes in the aerodynamic and thermal performance parameters of each component of the aircraft engine, the improvement degree of different overall aerodynamic and thermal performance indicators is obtained.

[0071] Step 43: Based on the improvement of different overall aerodynamic and thermal performance indicators, the improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of each component is obtained.

[0072] Specifically, a collaborative design model is established to realize performance correlation analysis, iterative interaction of solutions and data correlation sharing between the overall technical solution and the technical solutions of each component. Aiming at the collaborative design of new aerodynamic and thermal principle configurations of aircraft engines, a scar model of data correlation and interaction between the overall one-dimensional simulation of aircraft engines and the three-dimensional simulation of components is established based on an integrated simulation platform. By ablating the original overall technical solution and the technical solutions of each component (i.e., the solution with fewer iterations in the two design processes) in the overall one-dimensional simulation model, and embedding the new overall technical solution and the technical solutions of each component (i.e., the solution with more iterations in the two design processes), the simulation in the field of computational fluid dynamics is used. The real software CFX uses digital language to process the above technical solutions in CFX, establishes a one-dimensional simulation model of the aircraft engine and a three-dimensional simulation model of each component in the aircraft engine, and then solves the aerodynamic thermodynamic conservation equations under the above-mentioned overall and component aerodynamic thermodynamic performance indicators and parameters, calculates the matching working points of the aircraft engine under the new overall-level technical solution and component-level technical solution, and obtains the changes in the aerodynamic thermodynamic performance parameters of the aircraft engine components at each working point, thereby realizing the evaluation of the overall aerodynamic thermodynamic performance improvement of the aircraft engine under the new technical solution in multiple scenarios (that is, the improvement of the technical solution of each component on the overall aerodynamic thermodynamic performance of the aircraft engine).

[0073] Specifically, Figure 3 As shown in the figure, the improvement degree of the technical solution on different overall aerodynamic thermal performance indicators and the weight parameters of the overall aerodynamic thermal performance indicators are obtained through the above scar model, and then the dimensionless and normalized performance improvement degree and the first The technical solution for each component calculates the weight parameters of the improvement degree of different performance indicators. Figure 3 Medium self-improvement For the The calculation formula for the degree to which the technical solution of each component improves the overall aerodynamic and thermal performance of the aircraft engine is as follows.

[0074] .

[0075] .

[0076] in, For the The degree to which the technical solution of each component improves the overall aerodynamic and thermal performance of the aircraft engine, that is, the degree of self-improvement; For the The technical solutions of each component have different overall aerodynamic and thermal performance indicators The degree of improvement; The overall aerodynamic and thermal performance index The weight parameter can be determined by the entropy weight method.

[0077] Step 5: Based on Bayesian and complex network theories, a double-layer complex network is established according to the overall aerodynamic and thermal performance indicators-technical solutions-time-space coupling relationship; the upper layer of the double-layer complex network is the overall technical solution layer, and the lower layer of the double-layer complex network is the technical solution layer of each component; the nodes in the overall technical solution layer represent the overall technical solution; the nodes in the technical solution layer of each component represent the technical solution of each component.

[0078] Specifically, the technical scheme for collaborative design of aircraft engines (i.e. the overall technical scheme of aircraft engines) is divided into overall-level technical schemes (i.e. the overall technical scheme layer) and component-level technical schemes (i.e. the technical scheme layer of each component). According to the generation, iteration and sequential association sequence of component-level technical schemes with other technical schemes, multi-agent and temporal event graph modeling theory is introduced. Based on Bayesian and complex network theory, and according to the overall aerodynamic and thermal performance indicators-technical schemes-space-time coupling relationship, a double-layer complex network of overall-level technical schemes and component-level technical schemes is established for multiple technical schemes for collaborative design of aircraft engines.

[0079] The technical solution of the two-layer complex network is as follows Figure 4 As shown in the figure, the upper overall level technical solution layer (i.e. the overall technical solution layer) and the lower aircraft engine component level technical solution layer (i.e. the technical solution layer for each component) are established respectively, and a mapping association between the upper and lower levels is generated; at the same time, the nodes in the complex network represent the technical solutions, and their importance is measured by the degree centrality, core number, betweenness and eigenvector centrality of the nodes in the same level.

[0080] Step 6: Calculate the contribution of the technical solutions of each component based on the lifting degree and the two-layer complex network.

[0081] As an optional implementation, step 6 specifically includes the following steps 61 to 64.

[0082] Step 61: Based on the calculation formula of the importance of nodes in the double-layer complex network, calculate the importance of the technical solution of each component respectively; the importance of the node includes degree centrality, core number, betweenness and eigenvector centrality.

[0083] Specifically, the degree centrality of a node is calculated according to the following formula: .

[0084] .

[0085] in, N is the number of nodes in the two-layer complex network; For Node The degree value of the node The number of edges connecting nodes with causal relationships.

[0086] Specifically, follow the steps below to calculate the number of cores of a node: .

[0087] The first step, initialization, starts from each node and initializes its core number to 1.

[0088] The second step is iteration. For each node , check to remove and the connectivity of the remaining network after all its directly connected solution nodes.

[0089] Step 3: If you remove After the network is still connected to the technical solution node directly connected to it, The number of cores increases by 1.

[0090] Step 4: Repeat steps 2 and 3 until the number of cores of all nodes stops increasing. The final number of cores is .

[0091] Specifically, the betweenness of a node is calculated according to the following formula: .

[0092] .

[0093] in, Representation Node j and The number of shortest paths between Representation Node j and The shortest path between nodes The number of items.

[0094] Specifically, the eigenvector centrality is calculated according to the following formula: .

[0095] .

[0096] Among them, A represents the adjacency matrix of the adjacent relationship between nodes; is the adjacency matrix A The eigenvector of x The corresponding eigenvalue; eigenvector x The eigenvector corresponding to the largest eigenvalue is the eigenvector centrality .

[0097] Specifically, the calculation formula for the importance of the technical solution of each component is as follows.

[0098] .

[0099] in, For the The importance of the node The node is Technical solutions for each component; Based on the analytic hierarchy process , , , The relative weight of For the The degree centrality of each node; For the The number of cores per node; For the The betweenness of the nodes; For the The eigenvector centrality of each node.

[0100] Specifically, the analytic hierarchy process includes.

[0101] By , , and Compare each other two by two, quantify the relative weight of each indicator and construct a pairwise comparison matrix; determine the weight of each parameter on the importance of the technical solution represented by the node, and establish a weight matrix ; The largest characteristic root of ,correspond The eigenvector of , The amount is the weight, and its corresponding weight matrix Medium Element Single sorting correspondence.

[0102] Weight vector With the largest characteristic root The calculation steps are as follows.

[0103] (1) According to the following calculation formula, the weight matrix Find the product of the row elements and then find The power is obtained .

[0104] .

[0105] in, is the weight matrix the unnormalized weights of the components of the eigenvector corresponding to the largest eigenroot; is the weight matrix The elements in .

[0106] (2) Normalization (making the sum of all elements in the vector equal to 1) is recorded as ,but This is the desired eigenvector.

[0107] (3) The weight is obtained according to the following normalization calculation formula: .

[0108] .

[0109] (4) Solve the maximum eigenvalue of the normalized weight matrix and consistency indicators , the calculation formulas are as follows.

[0110] .

[0111] .

[0112] in, A is the weight matrix; W is the feature vector; express , , and The number of pairwise combination solutions.

[0113] (5) Random consistency index by looking up the table RI The value table of , the characterization matrix is ​​obtained according to the following formula The degree of consistency .

[0114] .

[0115] The consistency test determines whether there are logical problems in the constructed comparison matrix. If If the value is less than 0.1, the one-time test is passed, indicating that the weight matrix Determine the rationale for the approach.

[0116] Step 62: Based on the double-layer complex network, calculate the conditional probability of the associated technical solutions under the technical solution of the current component; the associated technical solutions are the technical solutions of other components associated with the technical solution of the current component.

[0117] Specifically, the Bayesian network is a probabilistic graph model that simulates the uncertainty processing model of causal relationships in the human reasoning process. Its network topology is a directed acyclic graph (DAG). The Bayesian theory formula is a method for calculating conditional probability, which updates the credibility of a hypothesis based on new evidence and previous probabilities.

[0118] Specifically, the Bayesian theory is used to analyze the causal relationship in the double-layer complex network under the condition of traction target (i.e., overall aerodynamic and thermal performance index)-technical solution-time-space coupling evolution, so as to realize the calculation of technical contribution. By applying Bayesian theory in the complex network, the node j (i.e. related technical solutions) at known condition nodes The conditional probability calculation formula under (i.e. the technical solution of the current component).

[0119] .

[0120] in, For the j The technical solution of each component is in The conditional probability of the technical solution of the components, where j The technical solution of each component is a related technical solution. The technical solution of a component is the technical solution of the current component; Representative j The technical solution of each component is The number of times the technical solutions of the components are connected; For the The degree centrality of the nodes.

[0121] Step 63: Based on the conditional probability and the improvement of the overall aerodynamic and thermal performance of the aircraft engine, calculate the comprehensive improvement of the technical solutions of each component on the overall aerodynamic and thermal performance of the aircraft engine.

[0122] Specifically, the calculation formula for the comprehensive improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of each component is as follows.

[0123] .

[0124] in, For the The comprehensive improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of each component; For the The degree to which the technical solution of each component improves the overall aerodynamic and thermal performance of the aircraft engine; For the j The degree to which the technical solution of each component improves the overall aerodynamic and thermal performance of the aircraft engine; For the The sum of the improvements in the overall aerodynamic and thermal performance of an aircraft engine supported by the technical solutions of each component and other technical solutions can be calculated by Bayesian theory.

[0125] like Figure 5 The The technical solution of each component produces the j The probability diagram of the technical solution of each component, the obtained probability formula can be expressed as: , Figure 5 In a , b , c Representatives and and j Related technical solutions.

[0126] Step 64: Based on the comprehensive improvement of the technical solutions of each component to the overall aerodynamic and thermal performance of the aircraft engine and the importance of the technical solutions of each component, calculate the contribution of the technical solutions of each component.

[0127] Specifically, Figure 5 As shown in the figure, based on the double-layer complex network, a calculation model for the contribution of the technical solutions for collaborative design of aircraft engines to the improvement of the aerodynamic and thermal performance of the overall solution is established (i.e., the contribution of the technical solutions of each component ). The calculation formula for the contribution of the technical solutions of each specific component is as follows.

[0128] .

[0129] in, For the The contribution of the technical solution of each component; For the The importance of the technical solution for each component; For the The technical solutions of each component can comprehensively improve the overall aerodynamic and thermal performance of the aircraft engine.

[0130] Finally, based on the changes in aerodynamic and thermal performance parameters of various aircraft engine components and the comprehensive improvement of the overall aerodynamic and thermal performance indicators obtained in the above steps, efficient computational evaluation of aerodynamic and thermal performance under the coupling of overall and component-level technical solutions with the overall aircraft engine solution is achieved. Through the scar model of the correlation and interaction between the overall one-dimensional simulation of the aircraft engine and the three-dimensional simulation data of the components, the aerodynamic and thermal design of the aircraft engine components and the overall system is adjusted and optimized, providing technical support for improving the aerodynamic and thermal performance of the overall solution in the optimized collaborative design of aircraft engines under multidisciplinary constraints.

[0131] The beneficial effects of the method for calculating the contribution of technical solutions for aircraft engine components proposed in this application are mainly manifested in: the method can accurately evaluate the problems of high reusability and strong divergence of different overall and component-level technical solutions and the unreasonable contribution evaluation caused by the emergence of breakthrough technical solutions during the iterative update of the overall solution. Through the scar model of the overall one-dimensional simulation of the aircraft engine and the three-dimensional simulation data of the components, the aerodynamic and thermal design of the aircraft engine components and the overall are adjusted and optimized, and a double-layer complex network is established through Bayesian and complex network theories to calculate the contribution of the technical solutions of each component, and realize the efficient computational evaluation of the aerodynamic and thermal performance under the coupling of the overall and component-level technical solutions with the overall solution of the aircraft engine, providing technical support for the improvement of the aerodynamic and thermal performance of the overall solution in the optimized collaborative design of aircraft engines under multidisciplinary constraints. At the same time, the contribution of the technical solutions of each component can also support the comprehensive benefit evaluation of the embedding of the technical solutions of the components into the overall solution or technology integration, and provide a theoretical basis for related research on the technical contribution evaluation of the collaborative design of new principles and configurations of aerodynamic and thermal dynamics of aircraft engines.

[0132] In an exemplary embodiment, taking a compressor component solution as an example, the contribution is calculated as follows.

[0133] According to step 1 and step 2, taking the compressor component solution as an example, since the initial version of the compressor component technical solution in the overall aerodynamic and thermal performance simulation model of the aircraft engine cannot meet the requirements of the traction index, it is necessary to carry out the collaborative design of the compressor component solution. According to the overall aerodynamic and thermal performance traction index, the aerodynamic and thermal performance parameters of the components associated with the existing compressor component technical solution are determined to be the converted speed, pressure ratio, etc. (independent variables), and the corresponding overall aerodynamic and thermal performance indicators of the aircraft engine are thrust. F , unit fuel consumption sfc etc. (dependent variable).

[0134] According to steps 3 and 4, relying on the integrated simulation platform, a scar model is established for the interaction between the overall one-dimensional simulation of the aircraft engine and the three-dimensional simulation data of the compressor components. After removing the initial version of the compressor from the original whole machine model, the interaction boundary with physical information is exposed, among which the boundary input interface ( Figure 6 The aerodynamic and thermal performance parameters include the converted speed, pressure ratio, adjustable geometric vector, bleed air vector, etc.; the boundary output interface ( Figure 6 The aerodynamic and thermal performance parameters include the converted flow rate, adiabatic efficiency, dimensionless axial force, dimensionless temperature at the bleed air position, dimensionless pressure at the bleed air position, etc., and the performance calculation of the whole machine after the component technical solution is updated can be realized by giving the corresponding replacement parameters at the boundary, such as Figure 6 The overall one-dimensional simulation model of the aircraft engine (i.e., the one-dimensional simulation model of the aircraft engine) established based on the integrated simulation platform shown in the figure exposes the interaction boundary with physical information after eliminating the original technical solution of the compressor components, and embeds the existing technical solution V2.0 of the compressor components (i.e., Figure 6 The new component solution is embedded in the 3D model. Figure 6 The CFX compressor 3D simulation model in the engine is then used to solve the aerodynamic thermodynamic conservation equation to calculate the matching working point of the component design scheme and the overall scheme, and the changes in the aerodynamic thermodynamic performance parameters of the components such as the converted speed and pressure ratio under the existing compressor component scheme are obtained, as well as the thrust of the overall aerodynamic thermodynamic performance index of the aircraft engine. F , unit fuel consumption sfc The improvement degree, etc., can evaluate the effectiveness of the existing compressor component technical solution design at the level of the overall aerodynamic and thermal performance index gain; at the same time, the original fan, high-pressure turbine, low-pressure turbine and other component solutions cannot be adapted to the existing compressor component technical solution V2.0 version, so it is necessary to carry out overall-component collaborative design, realize the iterative update of other component solutions, thereby further improving the overall aerodynamic and thermal performance of the aircraft engine.

[0135] Specifically, the overall one-dimensional simulation model (i.e., the one-dimensional simulation model of the aircraft engine) is as follows: Figure 7 As shown, Figure 7 The components include a fan, a compressor, a combustion chamber, a turbine, a tail nozzle and their connecting components, wherein the compressor component is directly connected to the fan and the combustion chamber, and is associated with the turbine through the rotor shaft, and the other components are connected in sequence. An overall one-dimensional simulation model of the aircraft engine is built on the Simulink simulation platform. The compressor components represented by this operation example have been marked in the figure, and the remaining connecting parts are necessary components of the aircraft engine (not related to the subject of this application) and will not be repeated here.

[0136] According to step 5, determine the node position of the existing compressor component technical solution in the double-layer complex network and the original fan, high-pressure turbine, low-pressure turbine and other component technical solution nodes that have a direct causal relationship with it.

[0137] According to step 6, the degree centrality, core number, betweenness and eigenvector of the existing compressor component technical solution node are calculated based on the double-layer complex network node importance calculation formula, and then the importance of the compressor component technical solution is calculated by the compressor component technical solution importance calculation formula. A calculation model for the degree of improvement of the overall aerodynamic and thermal performance of the aircraft engine by the existing compressor component technical solution is established to calculate the degree of improvement of the overall aerodynamic and thermal performance of the aircraft engine by the existing compressor component technical solution.

[0138] Finally, the importance of the existing compressor component technical solution and the degree of improvement of the existing compressor component technical solution on the overall aerodynamic and thermal performance of the aircraft engine are multiplied together to obtain the contribution of the compressor component technical solution for collaborative design of aircraft engines to the improvement of the aerodynamic and thermal performance of the overall solution (v1.0).

[0139] Based on the same inventive concept, the embodiment of the present application also provides a system for calculating the contribution of technical solutions for aircraft engine components. The implementation solution provided by the system for solving the problem is similar to the implementation solution recorded in the above method, so the specific limitations in the embodiments of one or more aircraft engine component technical solution contribution calculation systems provided below can refer to the limitations of the aircraft engine component technical solution contribution calculation method above, and will not be repeated here.

[0140] In an exemplary embodiment, a system for calculating the contribution of technical solutions for aircraft engine components is provided, comprising the following modules.

[0141] The design process acquisition module is used to acquire the overall design process of the overall technical solution of the aircraft engine; the overall technical solution includes the technical solutions of each component; the overall design process includes multiple design processes.

[0142] The statistical quantity acquisition module is used to obtain the overall aerodynamic and thermal performance indicators of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine in the overall technical solution during multiple design processes.

[0143] The scar model generation module is used to establish a scar model according to the overall aerodynamic and thermal performance indicators of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine; the scar model includes: an overall one-dimensional simulation model of the aircraft engine and a three-dimensional simulation model of each component in the aircraft engine.

[0144] The comprehensive improvement calculation module is used to obtain the improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of each component based on the scar model.

[0145] The double-layer complex network generation module is used to establish a double-layer complex network based on Bayesian and complex network theories, according to the overall aerodynamic and thermal performance indicators-technical solutions-time-space coupling relationship; the upper layer of the double-layer complex network is the overall technical solution layer, and the lower layer of the double-layer complex network is the technical solution layer of each component; the nodes in the overall technical solution layer represent the overall technical solution; the nodes in the technical solution layer of each component represent the technical solution of each component.

[0146] The contribution calculation module is used to calculate the contribution of the technical solutions of each component based on the lifting degree and the double-layer complex network.

[0147] The present application also provides an application scenario, which applies the above-mentioned method for calculating the contribution of the technical solution of aircraft engine components. Specifically: the method for calculating the contribution of the technical solution of aircraft engine components provided in this embodiment can be applied to the relevant research on the evaluation of the technical contribution of the collaborative design of the new principle and configuration of aerodynamic and thermal power of aircraft engines. The relevant research on the evaluation of the technical contribution of the collaborative design of the new principle and configuration of aerodynamic and thermal power of aircraft engines includes: the overall design process of aircraft engines, the contribution evaluation process of aircraft engines and the re-development process of aircraft engines; the research and development of aircraft engines calculates the contribution of the technical solutions of various components of aircraft engines according to the existing overall design process of aircraft engines, and evaluates the improvement effect of the technical solutions of various components on the aerodynamic and thermal performance of the overall technical solution according to the contribution, thereby providing technical support for the innovative research and development process of aircraft engines. The method for calculating the contribution of the technical solution of aircraft engine components provided in this embodiment belongs to the process of evaluating the contribution of aircraft engines. Specifically, in the process of evaluating the contribution of aircraft engines, the contribution of the technical solutions of various components of aircraft engines is calculated by establishing a scar model and a double-layer complex network.

[0148] In an exemplary embodiment, a computer device is provided. The computer device may be a server or a terminal. The internal structure diagram thereof may be as follows: Figure 8As shown. The computer device includes a processor, a memory, an input / output interface (Input / Output, referred to as I / O) and a communication interface. Among them, the processor, the memory and the input / output interface are connected through a system bus, and the communication interface is connected to the system bus through the input / output interface. Among them, the processor of the computer device is used to provide computing and control capabilities. The memory of the computer device includes a non-volatile storage medium and an internal memory. The non-volatile storage medium stores an operating system, a computer program and a database. The internal memory provides an environment for the operation of the operating system and the computer program in the non-volatile storage medium. The database of the computer device is used to store the overall design process of the overall technical solution of the aircraft engine. The input / output interface of the computer device is used to exchange information between the processor and an external device. The communication interface of the computer device is used to communicate with an external terminal through a network connection. When the computer program is executed by the processor, a method for calculating the contribution of the technical solution of an aircraft engine component is implemented.

[0149] Those skilled in the art will understand that Figure 8 The structure shown in the figure is only a block diagram of a part of the structure related to the solution of the present application, and does not constitute a limitation on the computer device to which the solution of the present application is applied. The specific computer device may include more or fewer components than those shown in the figure, or combine certain components, or have a different arrangement of components. In an exemplary embodiment, a computer device is provided, including a memory and a processor, wherein a computer program is stored in the memory, and the processor implements the steps in the above-mentioned method embodiments when executing the computer program.

[0150] In an exemplary embodiment, a computer-readable storage medium is provided, storing a computer program, and when the computer program is executed by a processor, the steps in the above method embodiments are implemented.

[0151] In an exemplary embodiment, a computer program product is provided, including a computer program, and when the computer program is executed by a processor, the steps in the above method embodiments are implemented.

[0152] It should be noted that the user information (including but not limited to user device information, user personal information, etc.) and data (including but not limited to data used for analysis, stored data, displayed data, etc.) involved in this application are all information and data authorized by the user or fully authorized by all parties, and the collection, use and processing of relevant data must comply with relevant regulations.

[0153] Those skilled in the art can understand that all or part of the processes in the above-mentioned embodiment methods can be completed by instructing the relevant hardware through a computer program, and the computer program can be stored in a non-volatile computer-readable storage medium. When the computer program is executed, it can include the processes of the embodiments of the above-mentioned methods. Among them, any reference to the memory, database or other medium used in the embodiments provided in this application can include at least one of non-volatile and volatile memory. Non-volatile memory can include read-only memory (ROM), magnetic tape, floppy disk, flash memory, optical memory, high-density embedded non-volatile memory, resistive random access memory (ReRAM), magnetoresistive random access memory (MRAM), ferroelectric random access memory (FRAM), phase change memory (PCM), graphene memory, etc. Volatile memory can include random access memory (RAM) or external cache memory, etc. By way of illustration and not limitation, RAM may be in various forms, such as Static Random Access Memory (SRAM) or Dynamic Random Access Memory (DRAM).

[0154] The database involved in each embodiment provided in this application may include at least one of a relational database and a non-relational database. The non-relational database may include a distributed database based on blockchain, etc., but is not limited thereto. The processor involved in each embodiment provided in this application may be a general-purpose processor, a central processing unit, a graphics processor, a digital signal processor, a programmable logic device, a data processing logic device based on quantum computing, etc., but is not limited thereto.

[0155] The technical features of the above embodiments may be combined arbitrarily. To make the description concise, not all possible combinations of the technical features in the above embodiments are described. However, as long as there is no contradiction in the combination of these technical features, they should be considered to be within the scope of this specification.

[0156] This article uses specific examples to illustrate the principles and implementation methods of this application. The description of the above embodiments is only used to help understand the method and core ideas of this application. At the same time, for those skilled in the art, according to the ideas of this application, there will be changes in the specific implementation methods and application scope. In summary, the content of this specification should not be understood as limiting this application.

Claims

1. A method for calculating the contribution of technical solutions for aircraft engine components, characterized in that: The method for calculating the contribution of the technical solution of the aircraft engine component includes: Obtaining an overall design process of an overall technical solution of an aircraft engine; the overall technical solution includes technical solutions of various components; the overall design process includes multiple design processes; Obtaining the overall aerodynamic and thermal performance indicators of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine in the overall technical solution during multiple design processes; A scar model is established according to the overall aerodynamic and thermal performance index of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine; the scar model includes: an overall one-dimensional simulation model of the aircraft engine and a three-dimensional simulation model of each component in the aircraft engine; The improvement degree of the technical solutions of each component on the overall aerodynamic and thermal performance of the aircraft engine is obtained based on the scar model, specifically including: based on the scar model, solving the aerodynamic and thermodynamic conservation equations of the overall aerodynamic and thermal performance index and the aerodynamic and thermodynamic conservation equations of the aerodynamic and thermal performance parameters of each component to obtain the change amount of the aerodynamic and thermal performance parameters of each component of the aircraft engine; Based on the changes in the aerodynamic and thermal performance parameters of each component of the aircraft engine, the improvement of different overall aerodynamic and thermal performance indicators is obtained; Based on the improvement of different overall aerodynamic and thermal performance indicators, the improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of each component is obtained; Based on Bayesian and complex network theories, a double-layer complex network is established according to the overall aerodynamic and thermal performance index-technical solution-time-space coupling relationship; the upper layer of the double-layer complex network is the overall technical solution layer, and the lower layer of the double-layer complex network is the technical solution layer of each component; the nodes in the overall technical solution layer represent the overall technical solution; the nodes in the technical solution layer of each component represent the technical solution of each component; Calculating the contribution of the technical solutions of each component based on the lift and the double-layer complex network, specifically including: calculating the importance of the technical solutions of each component based on the importance calculation formula of the nodes of the double-layer complex network; the importance of the nodes includes degree centrality, core number, betweenness and eigenvector centrality; Based on a two-layer complex network, the conditional probability of the associated technical solution under the technical solution of the current component is calculated; the associated technical solution is the technical solution of other components associated with the technical solution of the current component; Based on the conditional probability and the improvement of the overall aerodynamic and thermal performance of the aircraft engine, calculate the comprehensive improvement of the technical solutions of each component on the overall aerodynamic and thermal performance of the aircraft engine; Based on the comprehensive improvement of the technical solutions of each component to the overall aerodynamic and thermal performance of the aircraft engine and the importance of the technical solutions of each component, the contribution of the technical solutions of each component is calculated.

2. The method for calculating the contribution of the technical solution of an aircraft engine component according to claim 1, characterized in that: The calculation formula for the degree of improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of the above components is: ； ； in, For the The degree to which the technical solution of each component improves the overall aerodynamic and thermal performance of the aircraft engine; For the The technical solutions of each component have different overall aerodynamic and thermal performance indicators The degree of improvement; The overall aerodynamic and thermal performance index The weight parameter of .

3. The method for calculating the contribution of the technical solution of an aircraft engine component according to claim 1, characterized in that: The calculation formula for the importance of the technical solutions of the components is: ； in, For the The importance of the node The node is Technical solutions for each component; Based on the analytic hierarchy process , , , The relative weight of For the The centrality of each node; For the The number of cores per node; For the The betweenness of nodes; For the The eigenvector centrality of each node.

4. The method for calculating the contribution of the technical solution of an aircraft engine component according to claim 1, characterized in that: The calculation formula for the comprehensive improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of the above components is: ； in, For the The comprehensive improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of each component; For the The degree to which the technical solution of each component improves the overall aerodynamic and thermal performance of the aircraft engine; For the j The degree to which the technical solution of each component improves the overall aerodynamic and thermal performance of the aircraft engine; For the j The technical solution of each component is in The conditional probability of the technical solution of each component; j The technical solution for each component is Other technical solutions associated with the technical solution of a component.

5. The method for calculating the contribution of the technical solution of an aircraft engine component according to claim 4, characterized in that: The calculation formula of the conditional probability is: ； in, Representative j The technical solution of each component is The number of times the technical solutions of the components are connected, among which the j The technical solution of each component is the related technical solution. The technical solution of a component is the technical solution of the current component; For the The degree centrality of the nodes.

6. The method for calculating the contribution of the technical solution of an aircraft engine component according to claim 1, characterized in that: The calculation formula of the contribution of the technical solutions of each component is: ； in, For the The contribution of the technical solution of each component; For the The importance of the technical solution for each component; For the The technical solutions of each component can comprehensively improve the overall aerodynamic and thermal performance of the aircraft engine.

7. A system for calculating the contribution of technical solutions for aircraft engine components, characterized in that: The method for calculating the contribution of a technical solution of an aero-engine component according to any one of claims 1 to 6, wherein the system for calculating the contribution of a technical solution of an aero-engine component comprises: A design process acquisition module, used to acquire an overall design process of an overall technical solution of an aircraft engine; the overall technical solution includes technical solutions of various components; the overall design process includes multiple design processes; A statistical quantity acquisition module is used to obtain the overall aerodynamic and thermal performance index of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine in the overall technical solution in multiple design processes; A scar model generation module is used to establish a scar model according to the overall aerodynamic and thermal performance index of the aircraft engine and the aerodynamic and thermal performance parameters of each component of the aircraft engine; the scar model includes: an overall one-dimensional simulation model of the aircraft engine and a three-dimensional simulation model of each component in the aircraft engine; The comprehensive improvement calculation module is used to obtain the improvement of the technical solutions of each component on the overall aerodynamic and thermal performance of the aircraft engine based on the scar model, specifically including: based on the scar model, solving the aerodynamic and thermodynamic conservation equations of the overall aerodynamic and thermal performance index and the aerodynamic and thermodynamic conservation equations of the aerodynamic and thermal performance parameters of each component to obtain the change in the aerodynamic and thermal performance parameters of each component of the aircraft engine; Based on the changes in the aerodynamic and thermal performance parameters of each component of the aircraft engine, the improvement of different overall aerodynamic and thermal performance indicators is obtained; Based on the improvement of different overall aerodynamic and thermal performance indicators, the improvement of the overall aerodynamic and thermal performance of the aircraft engine by the technical solutions of each component is obtained; A double-layer complex network generation module is used to establish a double-layer complex network based on Bayesian and complex network theories according to the overall aerodynamic and thermal performance index-technical solution-time-space coupling relationship; the upper layer of the double-layer complex network is the overall technical solution layer, and the lower layer of the double-layer complex network is the technical solution layer of each component; the nodes in the overall technical solution layer represent the overall technical solution; the nodes in the technical solution layer of each component represent the technical solution of each component; A contribution calculation module is used to calculate the contribution of the technical solution of each component based on the lifting degree and the double-layer complex network, specifically including: calculating the importance of the technical solution of each component based on the importance calculation formula of the node of the double-layer complex network; the importance of the node includes degree centrality, core number, betweenness and eigenvector centrality; Based on a two-layer complex network, the conditional probability of the associated technical solution under the technical solution of the current component is calculated; the associated technical solution is the technical solution of other components associated with the technical solution of the current component; Based on the conditional probability and the improvement of the overall aerodynamic and thermal performance of the aircraft engine, calculate the comprehensive improvement of the technical solutions of each component on the overall aerodynamic and thermal performance of the aircraft engine; Based on the comprehensive improvement of the technical solutions of each component to the overall aerodynamic and thermal performance of the aircraft engine and the importance of the technical solutions of each component, the contribution of the technical solutions of each component is calculated.

8. A computer device comprising: A memory, a processor, and a computer program stored in the memory and executable on the processor, wherein the processor executes the computer program to implement the method for calculating the contribution of the technical solution of an aircraft engine component according to any one of claims 1 to 6.

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