空心风扇叶片抗近真实鸟体冲击响应特性研究

Research on anti near-real bird body impact response of hollow fan blades

摘要

航空发动机宽弦空心风扇叶片在高速旋转时容易产生明显的振动问题，且在运行阶段受到鸟体冲击时面临着更高的结构损伤风险。本研究基于鸟体姿态图片提出了真实鸟体结构模型构建方法，并构建了某航空发动机的两层空腔风扇叶片模型，采用流固耦合方法对叶片振动特性与抗真实鸟体冲击响应进行了研究。并通过鸟撞平板实验验证了所提出的近真实鸟体的有效性，对比传统简化鸟体可以更加真实有效地反映鸟撞载荷。结果表明:通过Campbell图的叶片共振裕度分析，确定了叶片合理的转速区间为2 900～3 800 r/min；真实形状鸟体以100 m/s正面撞击转速为3 344 r/min风扇叶片时，2号、3号和4号叶片轴向形变量较大，最大值达到了78.3 mm；在切割鸟体过程中，应力集中首先在叶片前缘位置处出现，达到2 000 MPa，随后扩散至整个叶片。研究结果可为风扇叶片的抗鸟撞设计和优化提供依据。

Abstract

Aeroengine wide-chord hollow fan blades are prone to significant vibration problems during high-speed rotation, and face a higher risk of structural damage when impacted by bird body structures during operation. This work proposes a method for constructing a real bird structure model based on bird posture images, and a two-layer cavity fan blade model of a certain aero-engine was constructed. The blade vibration characteristics and anti-real bird impact response were studied considering fluid-structure interaction. And the effectiveness of the proposed near real bird body was verified through bird strike flat plate experiments, which can more accurately and effectively reflect the bird strike load compared to traditional simplified bird bodies. The results showed that through blade resonance margin analysis of the Campbell diagram, the reasonable rotating speed range of the blade was determined to be 2 900 r/min-3 800 r/min. When the real-shaped bird body impacted the fan blade head-on at 100 m/s with a rotating speed of 3 344 r/min, the axial deformation of No. 2, No. 3, and No. 4 blades was relatively large, with the maximum value reaching 78.3 mm. During the process of cutting the bird, stress concentration first appeared at the leading edge of the blade, reaching 2 000 MPa, and then spread to the entire blade. The research results can provide basis for the anti-bird impact design and optimization of fan blades.

关键词

空心风扇叶片 / 振动特性 / 真实形状鸟体 / 冲击响应 / 流固耦合

Key words

hollow fan blade / vibration characteristic / real-shaped bird body / impact response / fluid structure interaction

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基金资助

国家自然科学基金资助项目(52206059)

河南省通用航空技术重点实验室开放基金(ZHKF-230202)

河南省通用航空技术重点实验室开放基金(ZHKF-240211)

河南省高等学校重点科研项目计划(25A590002)

河南省高等学校重点科研项目计划(24A130004)

郑州航院研究生教育创新计划基金项目(2024CX69)