Aero-engine accessory reliability analysis method

Abstract

The application belongs to the technical field of reliability analysis of aero-engine accessories, and particularly relates to a reliability analysis method of aero-engine accessories, which is designed on the basis of accessory failure modes, models are established from the component level and the product level, threshold values and influence factors are studied, and finally a reliability model between the failure modes and design variables is established to calculate the reliability of the accessories, has high analysis efficiency and high precision, can be parallel and integrated with design, and can provide effective support for the design and improvement of the accessories.

Description

Technical Field

[0001] This application belongs to the field of reliability analysis technology for aero-engine components, and specifically relates to a reliability analysis method for aero-engine components. Background Technology

[0002] There are numerous components on an aero-engine, especially mechanical components. These components operate in complex and harsh environments and are subject to random variations in manufacturing processes and assembly, making them highly susceptible to malfunctions and failures, resulting in low reliability.

[0003] Currently, most reliable analyses of aero-engine components are conducted using traditional fault tree analysis, failure mode, effects and hazard analysis, or failure mode and effects analysis. This approach is inefficient and inaccurate, making it difficult to integrate with the design process and provide effective support for the design and improvement of components.

[0004] This application is made in view of the aforementioned technical deficiencies.

[0005] It should be noted that the above background information is only used to assist in understanding the inventive concept and technical solution of this application, and it does not necessarily belong to the prior art of this patent application. In the absence of clear evidence that the above information was disclosed on the filing date of this application, the above background information should not be used to evaluate the novelty and inventiveness of this application. Summary of the Invention

[0006] The purpose of this application is to provide a reliability analysis method for aircraft engine components to overcome or mitigate at least one known technical defect.

[0007] The technical solution of this application is:

[0008] A method for reliability analysis of aero-engine components includes:

[0009] Conduct failure mode and effect analysis of components, identify failure modes of components, propose failure mode characterization parameters, conduct component-level damage analysis, obtain influencing factors, and their impact on component-level failure modes;

[0010] Conduct component-level quantitative model design to obtain the quantitative relationship between component failure mode characterization parameters and influencing factors, and construct a high-precision component-level surrogate model.

[0011] Based on a high-precision component-level proxy model, the correlation between product reliability and influencing factors is identified, a regression model between product reliability and influencing factors is constructed, and a high-precision product-level proxy model is formed.

[0012] The failure threshold of the failure mode characterization parameter is determined as an appendix, and the distribution type and distribution parameters of the influencing factors are obtained;

[0013] Based on the high-precision product-level proxy model, the failure threshold of the failure mode characterization parameter and the distribution type and distribution parameters of its influencing factors are established. According to the characteristics of the failure model, the reliability model of the component is established.

[0014] The reliability level of the attachments is calculated using the attachment reliability model.

[0015] According to at least one embodiment of this application, in the above-described aero-engine component reliability analysis method, component-level quantitative model design is carried out, specifically as follows:

[0016] By designing similarity calculation methods, a fault physics model method is used in the low similarity range to design a component-level quantization model; or,

[0017] By combining high similarity ranges with experimental data and expert scoring methods, a component-level quantitative model can be designed; or,

[0018] By combining intermediate range data with experimental data, a component-level quantization model was designed using machine learning methods.

[0019] According to at least one embodiment of this application, in the above-described method for reliability analysis of aero-engine components, the failure threshold of the component failure mode characterization parameter is determined specifically through statistical analysis of experimental data, finite element simulation, and experimental measurement methods.

[0020] The distribution types and parameters of influencing factors are obtained by analyzing the randomness of factors such as the geometric dimensions, fit clearance, material properties, contact characteristics, working load, and environmental load of the components.

[0021] According to at least one embodiment of this application, the above-described method for reliability analysis of aero-engine accessories further includes:

[0022] Based on the statistical information of failure data from similar product tests of the assembly, maximum likelihood analysis was performed to revise the assembly reliability model.

[0023] According to at least one embodiment of this application, in the above-described aero-engine component reliability analysis method, the component reliability level is calculated using a component reliability model, specifically as follows:

[0024] By employing the functional sensitivity and reliability sensitivity analysis methods for influencing factors and utilizing the component reliability model, the importance ranking of the influencing factors on product function is obtained, the key design parameters that need to be considered for product reliability analysis are determined, and then the component reliability level is calculated.

[0025] This application has at least the following beneficial technical effects:

[0026] This paper presents a reliability analysis method for aero-engine components. The design is based on the failure modes of components, and models are established at the component level and product level. Thresholds and influencing factors are studied, and finally a reliability model between failure modes and design variables is established to calculate the reliability of components. It has high analysis efficiency and high accuracy, and can be integrated with the design process, providing effective support for the design and improvement of components. Attached Figure Description

[0027] Figure 1 This is a schematic diagram of the reliability analysis method for aero-engine components provided in the embodiments of this application. Detailed Implementation

[0028] To make the technical solution and advantages of this application clearer, the technical solution of this application will be described in a clearer and more complete manner below with reference to the accompanying drawings. It should be understood that the specific embodiments described herein are only some embodiments of this application, and are only used to explain this application, not to limit this application. It should be noted that, for ease of description, only the parts related to this application are shown in the accompanying drawings. Other related parts can be referred to the general design. In the absence of conflict, the embodiments and technical features in the embodiments of this application can be combined with each other to obtain new embodiments.

[0029] Furthermore, unless otherwise defined, the technical or scientific terms used in this application description shall have the ordinary meaning understood by one of ordinary skill in the art to which this application pertains. The terms "first," "second," "third," and similar expressions used in this application description are for descriptive purposes only, to distinguish different components, and should not be construed as indicating or implying relative importance. The words "an," "a," or "the," etc., used in this application description should not be construed as an absolute limitation on quantity, but rather as indicating the presence of at least one. The words "comprising," "including," or similar expressions used in this application description mean that the element or object preceding the word encompasses the elements or objects listed following the word and their equivalents, without excluding other elements or objects.

[0030] The following is in conjunction with the appendix Figure 1 This application provides a further detailed explanation of the reliability analysis method for aircraft engine accessories.

[0031] Step 1: Analyze the failure modes of attachments and their components.

[0032] The composition, functional principles, environmental and load characteristics of the components and accessories are clearly defined. Failure mode and effect analysis is carried out. The main failure modes of the components and accessories are identified by combining experimental data. Based on the characteristics of the components and accessories, failure mode characterization parameters are proposed.

[0033] Taking the components corresponding to the main failure modes as the objects, we conduct component-level damage analysis to obtain their damage locations and mechanisms, and clarify the influence of factors such as geometric parameters, mechanical parameters and damage parameters on component-level failure modes.

[0034] Step 2: Establish a component-level model

[0035] Based on principles of mechanics and the similarity between component design parameters and existing products, three approaches are used to conduct component-level quantitative model design:

[0036] By designing similarity calculation methods, a fault physics model method is adopted in the low similarity range to design a component-level quantization model;

[0037] A component-level quantification model was designed by combining high similarity range with experimental data and expert scoring methods;

[0038] By combining intermediate range data with experimental data, a component-level quantization model was designed using machine learning methods.

[0039] By using a component-level quantification model, the quantitative relationship between component failure mode characterization parameters and influencing factors is obtained.

[0040] Using a component-level quantization model, a sampling strategy is employed to conduct multi-sample simulation experiments. Furthermore, methods such as RSM and Kriging are used to construct a high-precision component-level proxy model.

[0041] Step 3: Establish a product-level model

[0042] Driven by experimental data, and based on a high-precision component-level surrogate model, the correlation between product reliability and influencing factors is identified. Using methods such as RSM or Kriging, a regression model between product reliability and influencing factors is constructed, forming a high-precision product-level surrogate model.

[0043] Step 4: Determine the threshold values ​​for characterization parameters and the distribution of influencing factors.

[0044] The failure threshold of the failure mode characterization parameter was determined by methods such as experimental data statistics, finite element simulation, and experimental measurement.

[0045] The randomness of factors such as the geometric dimensions, fit clearance, material properties, contact characteristics, working load, and environmental load of the accessories is analyzed to obtain the distribution type and distribution parameters of the influencing factors.

[0046] Step 5: Establish an attachment reliability model

[0047] By applying a high-precision product-level proxy model, the failure threshold of the failure mode characterization parameter and the distribution type and distribution parameters of its influencing factors are established. Based on the characteristics of the failure model, such as linear explicit model, nonlinear explicit model, implicit model, simulation model, etc., numerical simulation methods or function substitution methods such as improved first-order second-moment approximation analytical method, Monte Carlo method, and importance sampling method are adopted to establish the reliability model of the failure mode.

[0048] Based on the statistical information of failure data from similar product tests of the assembly, maximum likelihood analysis was performed to revise the assembly reliability model.

[0049] Step Six: Calculate the reliability level of the attachments.

[0050] By employing the functional sensitivity and reliability sensitivity analysis methods for influencing factors and utilizing the component reliability model, the importance ranking of the influencing factors on product function is obtained, the key design parameters that need to be considered for product reliability analysis are determined, and then the component reliability level is calculated.

[0051] Those skilled in the art will understand that the reliability analysis method for aero-engine components disclosed in the above embodiments, based on the failure modes of components, establishes models at the component level and product level, studies thresholds and influencing factors, and finally establishes a reliability model between failure modes and design variables to calculate the reliability of components. It has high analysis efficiency and high accuracy, can be integrated with design, and can provide effective support for the design and improvement of components.

[0052] The various embodiments in the specification are described in a progressive manner, with each embodiment focusing on the differences from other embodiments. The same or similar parts between the various embodiments can be referred to each other.

[0053] The technical solution of this application has been described in conjunction with the preferred embodiments shown in the accompanying drawings. Those skilled in the art should understand that the scope of protection of this application is obviously not limited to these specific embodiments. Without departing from the principles of this application, those skilled in the art can make equivalent changes or substitutions to the relevant technical features, and the technical solutions after these changes or substitutions will all fall within the scope of protection of this application.

Claims

1. A reliability analysis method for aero-engine components, characterized in that, include: Conduct failure mode and effect analysis of components, identify failure modes of components, propose failure mode characterization parameters, conduct component-level damage analysis, obtain influencing factors, and their impact on component-level failure modes; Conduct component-level quantitative model design, obtain the quantitative relationship between component failure mode characterization parameters and influencing factors, and construct a high-precision component-level surrogate model; Based on a high-precision component-level proxy model, the correlation between product reliability and influencing factors is identified, a regression model between product reliability and influencing factors is constructed, and a high-precision product-level proxy model is formed. The failure threshold of the failure mode characterization parameter is determined as an appendix, and the distribution type and distribution parameters of the influencing factors are obtained; Based on the high-precision product-level proxy model, the failure threshold of the failure mode characterization parameter and the distribution type and distribution parameters of its influencing factors are established. According to the characteristics of the failure model, the reliability model of the component is established. The reliability level of the components is calculated using the component reliability model; The design of a component-level quantization model is carried out, specifically as follows: By designing similarity calculation methods, a fault physics model method is used in the low similarity range to design a component-level quantization model; or, A component-level quantification model was designed by combining high similarity range with experimental data and expert scoring methods; or, By combining intermediate ranges with experimental data, machine learning methods are used to design a component-level quantization model; The distribution types and parameters of influencing factors are obtained by analyzing the randomness of factors such as the geometric dimensions, fit clearance, material properties, contact characteristics, working load, and environmental load of the components. The reliability level of the attachments is calculated using the attachment reliability model, specifically as follows: By employing the functional sensitivity and reliability sensitivity analysis methods for influencing factors and utilizing the component reliability model, the importance ranking of the influencing factors on product function is obtained, the key design parameters that need to be considered for product reliability analysis are determined, and then the component reliability level is calculated.

2. The reliability analysis method for aero-engine components according to claim 1, characterized in that, The failure threshold for the failure mode characterization parameter is determined by statistical analysis of experimental data, finite element simulation, and experimental measurement methods.

3. The reliability analysis method for aero-engine components according to claim 1, characterized in that, Also includes: Based on the statistical information of failure data from similar product tests of the assembly, maximum likelihood analysis was performed to revise the assembly reliability model.

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