Efficient Probabilistic Risk Assessment for Aeroengine Turbine Disks Using Probability Density Evolution

Liu, Yang; Ding, Shuiting; Wang, Ziyao; Guo, Li

doi:10.2514/1.j055237

Cited by 18 publications

(4 citation statements)

References 15 publications

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“…Simultaneously, the probability failure risk is calculated by combining the crack growth rate equation and stress intensity factor equation. In this study, via an integral-based method called the fast NI method [27,36], the probability of disk failure is computed while taking multiple variables into consideration, e.g., the initial defect size, the load, the crack growth velocity, and the fracture toughness. Since the research method in this study connects the manufacturing plan directly with the engineering plan, the analysis of random variables can be ignored here.…”

Section: Linear Elastic Fracture Mechanicsmentioning

confidence: 99%

Modified Method for Surface Probabilistic Risk Assessment of Aero Engine Compressor Disks Considering Shot Peening

2023

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Aero engine compressor disks are typically life-limited parts and it is necessary to secure them through the implementation of an engineering plan and a manufacturing plan. Specifically, the engineering plan recommends the quantification of the safety of life-limited parts on the basis of probabilistic risk assessment (PRA). However, the direct correlation between plans is limited, and the effect of manufacturing parameters on the safety of life-limited parts remains to be investigated. Shot peening, as a typical method of surface manufacturing, can significantly improve the safety of life-limited parts. Therefore, a modified mathematical surface PRA method considering shot peening parameters is developed in this paper to further bridge the design and manufacturing processes. Additionally, a general database is established using the response surface method to overcome the simulation complexity. On the basis of this method and the general database, an innovative direct and efficient determination of key shot peening parameters through failure risk in the design stage is proposed. The results indicate that failure risk decreased by 3.26%, 11.31%, and 9.71%, respectively, with increasing number, diameter, and velocity of shots, with the effect of diameter being the greatest. In addition, the method improves the efficiency of determining the key parameters by 75.80%, thus satisfying the requirements of abundant and efficient iterations during the design stage.

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Section: Linear Elastic Fracture Mechanicsmentioning

confidence: 99%

Modified Method for Surface Probabilistic Risk Assessment of Aero Engine Compressor Disks Considering Shot Peening

2023

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“…The initial unbalance will bring an additional force and torque, which may lead to the rotor vibration and even cause the nonlinear vibration accident (Cui et al, 2017). For aircraft engine and gas turbines, the response levels caused by the initial unbalance of final assembly out of specification limits, under dynamic loading, can be 100 or 1,000 times greater than the levels resulting from static loading of the same magnitude (Ewins, 2010;Wang et al, 2017;Yang et al, 2017).…”

Section: Introductionmentioning

confidence: 99%

A novel constrained optimization-build method for precision assembly of aircraft engine

Sun

Chen

et al. 2019

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Purpose This paper aims to provide a precision assembly method to improve the aircraft engine quality of initial unbalance with the purpose of founding the process for mass eccentricity propagation and demonstration of assembly process. The proposed method can be used for assembly guidance, tolerance allocation and so on, especially for the assembly with a large number of rotors and the assembly requirements of initial unbalance and coaxiality in high precision. Design/methodology/approach This paper proposes a constrained optimization-build method to minimize initial unbalance of aircraft engine assembly, which takes amount of unbalance and concentricity of each rotor into account. A constrained nonlinear programming model is extracted by choosing the initial unbalance as the objective function, and choosing the coaxiality and assembly orientations as the nonlinear constraints. The initial unbalance is reduced stage-by-stage by controlling the assembly angle of each rotor. Findings The validity and accuracy of the proposed method is verified by the multistage rotors assembly through experiments run with the measuring instruments. Compared with the direct-build method, the initial unbalance of final assembly using proposed method is reduced by 22.2% in four rotors assembly. Originality/value Different from the geometric eccentricity propagation control methods to reduce the initial unbalance indirectly, this paper establishes mass eccentric propagation model in multistage rotors assembly of aircraft engine for the first time. It provides a new idea to establish the relationship between the amount of unbalance of each rotor and the initial unbalance of multistage rotors.

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“…3,4 For aero-engine and gas turbines, the response levels caused by the amount of unbalance of final assembly out of specification limits, under dynamic loading, can be 100 or 1000 times greater than the levels resulting from static loading of the same magnitude. 5,6…”

Section: Introductionmentioning

confidence: 99%

A method to control the amount of unbalance propagation in precise cylindrical components assembly

Sun

Liu

et al. 2019

Proceedings of the Institution of Mechanical Engineers, Part B:

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The article provides a novel method to control the amount of unbalance propagation in precise cylindrical components assembly, which takes the machining error, the measurement error, and the assembly error into account. The coefficient and the correction factor matrices of mass eccentric deviations are defined to analyze the amount of unbalance propagation by building the connective assembly model. The influence of the machining error, the measurement error, and the assembly error on the mass center is analyzed in the assembly. The cumulative mass eccentric deviation can be reduced stage by stage in the assembly, and the amount of unbalance of final assembly can be minimized by controlling the assembly angle of each component. The effectiveness of the proposed method is verified by the assembly of the real aero-engine using the optimal assembly strategy. Compared to the worst assembly strategy, the values of the amount of unbalance using the optimal assembly strategy are reduced by 20%, 76%, and 79% for two, three, and four components assembly, respectively. Besides, the reasonable tolerance design area for each component is obtained with the proposed method for the real aero-engine assembly with four components. The proposed method can improve the assembly accuracy of cylindrical components and can be used for assembly guidance and tolerance design, especially for the assembly of multistage precise cylindrical components.

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Efficient Probabilistic Risk Assessment for Aeroengine Turbine Disks Using Probability Density Evolution

Cited by 18 publications

References 15 publications

Modified Method for Surface Probabilistic Risk Assessment of Aero Engine Compressor Disks Considering Shot Peening

Modified Method for Surface Probabilistic Risk Assessment of Aero Engine Compressor Disks Considering Shot Peening

A novel constrained optimization-build method for precision assembly of aircraft engine

A method to control the amount of unbalance propagation in precise cylindrical components assembly

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