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- Title
Simulation and Experimental Study of Gas Turbine Blade Tenon-Root Detachment on Spin Test.
- Authors
Yu, Maoyu; Wang, Jianfang; Xuan, Haijun; Xiong, Wangjiao; He, Zekan; Qu, Mingmin
- Abstract
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.
- Subjects
TURBINE blades; GAS turbines; AIRPLANE motors; GAS turbine blades; COMPUTER simulation; ABSORPTION
- Publication
Aerospace (MDPI Publishing), 2024, Vol 11, Issue 8, p629
- ISSN
2226-4310
- Publication type
Article
- DOI
10.3390/aerospace11080629