Neck Structure Optimal Design of the Turbine Wheel for Containment Design of the Air Turbine Starter

Chen, Liqiang; Xuan, Haijun; Jia, Wenbin; Liu, Jianxin; Fang, Zehui; Zheng, Yao

doi:10.3390/aerospace10090802

Cited by 3 publications

(1 citation statement)

References 18 publications

(18 reference statements)

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“…Firstly, target parameters for optimizing the core ultra-stable structural framework are selected based on the index requirements, and their value ranges are determined while also clarifying the interdependent conditions among structural parameters [13]. The methods for selecting experimental points include full factorial design, orthogonal array, central composite design, Box-Behnken design, Latin hypercube design, and optimal Latin hypercube design [14].…”

Section: Optimization Process Designmentioning

confidence: 99%

Optimization Design of Core Ultra-Stable Structure for Space Gravitational Wave Detection Satellite Based on Response Surface Methodology

Liu,

Xu,

Han

et al. 2024

Aerospace

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In order to meet the urgent demand for novel zero-expansion materials and ultra-stable structures in space gravitational wave detection, it is necessary to develop an ultra-stable structural spacecraft system. This paper focuses on the research of the optimization of the core ultra-stable structure design of spacecraft, proposing a cross-scale parameterized model of structural deformation response and a multi-objective optimization method. By satisfying the prerequisites of mass and fundamental frequency, this paper breaks through the limitations of current linear analysis methods, and the overall thermal deformation of nonlinear material composite structures is optimized by modifying structural parameters.

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Section: Optimization Process Designmentioning

confidence: 99%

Optimization Design of Core Ultra-Stable Structure for Space Gravitational Wave Detection Satellite Based on Response Surface Methodology

Liu,

Xu,

Han

et al. 2024

Aerospace

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Outer casing structure design for the trisection turbine wheel burst of the air turbine starter

Tang,

Zhang,

Wang

et al. 2024

PLoS ONE

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The aviation regulations mandate that high-energy rotor components must possesses adequate containment capabilities. Ensuring the containment of the turbine wheel of the air turbine starter is of paramount importance. In this paper, the design thickness of the containment ring was determined and the containment ring deformation was given. Based on the design thickness and deformation of the containment ring, an outer casing structure design method was proposed by using FEM. Then, two containment tests were conducted for different distances between the containment ring and outer casing to validate the outer casing structure design method. The errors of the containment ring deformation are smaller than 7.5%, and the experimental results of the containment process are in accordance with the simulation, validating correctness of the outer casing structure design method. The containment ring deformation rate with the design thickness T = 10 mm is 115%. A safety margin of 1.05 is designed by considering the uniformity of containment ring deformation and the containment ring assembly error. The results illustrate that the deformed containment ring does not damage the outer casing, when the inner diameter of the outer casing is designed as 1.2 times the outer diameter of the containment ring.

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Simulation and Experimental Study of Gas Turbine Blade Tenon-Root Detachment on Spin Test

Yu,

Wang,

Xuan

et al. 2024

Aerospace

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This paper addresses the critical issue of turbine blade containment in aircraft engines, crucial for ensuring flight safety. Through a comprehensive approach integrating numerical simulations and experimental validations, the containment capabilities of gas turbine engine casings are thoroughly analyzed. The study investigates the impact dynamics, deformation characteristics, and energy absorption mechanisms during blade detachment events, shedding light on the containment process. Based on the multi-stage nature of gas turbines, two different blade structures were designed for turbine blades. Utilizing finite element simulation and the Johnson–Cook constitutive equation, this study accurately simulated single-blade and dual-blade containment scenarios. The simulation results of the single blade indicate that the process of a gas turbine blade impacting the casing primarily consists of three stages. The second stage, where the tenon root strikes the casing, is identified as the main cause of casing damage. Meanwhile, in the dual-blade simulation, the second blade, influenced by the first blade, directly impacts the casing after fracturing, resulting in greater damage. Then, eight corresponding containment tests were conducted based on the simulation results, validating the accuracy of the simulation parameters. Experimental verification of simulation results further confirms the validity of the proposed containment curves, providing essential insights for optimizing casing design and enhancing the safety and reliability of aircraft engines.

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Neck Structure Optimal Design of the Turbine Wheel for Containment Design of the Air Turbine Starter

Cited by 3 publications

References 18 publications

Optimization Design of Core Ultra-Stable Structure for Space Gravitational Wave Detection Satellite Based on Response Surface Methodology

Optimization Design of Core Ultra-Stable Structure for Space Gravitational Wave Detection Satellite Based on Response Surface Methodology

Outer casing structure design for the trisection turbine wheel burst of the air turbine starter

Simulation and Experimental Study of Gas Turbine Blade Tenon-Root Detachment on Spin Test

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