| 基于Campbell理论的航空发动机涡轮叶片共振裕度分析 |
| Analysis of resonance margin of aero⁃engine turbine blade based on campbell theory |
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| 中文摘要: |
| 针对航空发动机涡轮叶片的共振特性会导致叶片发生疲劳断裂、振动失效等问题，本文以某型号航空发动机涡轮叶片为研究对象，开展共振裕度分析研究。首先基于试验自锤击法和有限元物理仿真计算两种方法同步分析叶片的振动特性，通过提取叶片在两种工作状态下前6阶的模态分析结果，验证了该模型的正确性与实用性。其次在已有模型基础上，通过绘制不同工作转速下的Campbell共振曲线图，结合该型号发动机的实际工况参数，进行了转速共振裕度的校核分析，对叶片上可能发生共振的工作转速进行了解析并提出优化及改进方案。本方法主要是为叶片的前期设计制造及共振安全性检验问题提供了充足的科学依据和方法。 |
| 英文摘要: |
| Aiming at the problems that the resonance characteristics of aero?engine turbine blades may lead to fatigue fracture and vibration failure of the blades, this paper takes a certain type of aero?engine turbine blade as the research object to carry out resonance margin analysis research. Firstly, the vibration characteristics of the blade are analyzed simultaneously based on the test self?hammering method and the finite element physical simulation calculation method, and the correctness and practicability of the model are verified by extracting the modal analysis results of the first six orders of the blade under the two working states. Secondly, on the basis of the existing model, by drawing the Campbell resonance curves at different working speeds and combining with the actual working parameters of this type of engine, the check and analysis of the speed resonance margin is carried out. The rotational speeds at which resonance may occur on the blades are analyzed and the optimization and improvement plan is proposed. This method mainly provides sufficient scientific basis and methods for the preliminary design and manufacture of the blade and the resonance safety inspection. |
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| 中文关键词: 涡轮叶片 模态分析 共振裕度 有限元 |
| 英文关键词:turbine blade modal analysis resonance margin finite element |
| 基金项目: |
| DOI：10.11823/j.issn.1674-5795.2022.04.06 |
| 引用本文：田森, 吴娅辉, 贾志婷, 张大治, 谢兴娟, 姜延欢.基于Campbell理论的航空发动机涡轮叶片共振裕度分析[J].计测技术,2022,(4):. |
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