| Author Name | Affiliation | | Yongliang Wang | Naval Architecture and Ocean Engineering College, Dalian Maritime University, Dalian 116026, China | | Shihao Li | Naval Architecture and Ocean Engineering College, Dalian Maritime University, Dalian 116026, China | | Longkai Zheng | Naval Architecture and Ocean Engineering College, Dalian Maritime University, Dalian 116026, China | | Da Kang | Naval Architecture and Ocean Engineering College, Dalian Maritime University, Dalian 116026, China |
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| Abstract: |
| A cold compressor blade deforms elastically under aerodynamic and centrifugal loads during operation, transforming into a hot blade configuration. Blade deformation has a significant effect on the performance of compressor. A nonlinear pre-deformation method for compressor rotor blade was developed with consideration of the nonlinear features of blade stiffness and load which varies with blade configuration. In the blade profile design phase, the method can be used to compensate the aeroelastic deformation of the blade during operation. The adverse effects of blade deflection on compressor performance and structure can be avoided by the pre-deformation method. Due to the fact that the nonlinear method is sensitive to initial value, a load incremental method was applied to calculate initial blade deformation to stabilize and accelerate the pre-deformation method. The developed method was used to predict the manufactured configuration of the Stage 37 rotor blade. The variation rules of aerodynamic and structure parameters of the pre-deformed blade were analyzed under off-design conditions. Results show that the developed method ensures that under the design condition there was a good match between the actual blade configuration during operation and the intended design blade profile. The blade untwist angle of pre-deformed blade could be 0° at design point. Meanwhile, the tip clearance only decreased 0.2%. When the working speed was faster than 80% design speed, the performance of the pre-deformed blade agreed with that of the design blade. However, the mass flow rate and the total pressure ratio of the pre-deformed blade were lower at low speeds. |
| Key words: compressor blade pre-deformation blade reconstruction fluid-structure interaction blade deformation |
| DOI：10.11916/j.issn.1005-9113.19093 |
| Clc Number:V232.4 |
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| Descriptions in Chinese: |
| 压气机转子叶片非线性预变形方法 王永亮，李世豪，郑龙凯，康达 （大连海事大学 船舶与海洋工程学院，大连 116026） 中文说明：本文综合考虑气动力和离心力对叶片变形的作用，基于载荷增量法，对Stage 37的转子叶片进行了预变形设计。在此基础上，考虑叶片变形过程中的载荷及刚度非线性，对预变形叶片在非设计工况下进行叶型重构，分析了非设计工况下不同叶片构型气动性能及结构参数的变化规律。本方法可为压气机非设计工况气动和气动弹性的强迫响应、颤振等问题的分析提供准确的叶片构型，有助于提高高负荷压气机气动及强度特性分析和检验的精度。 关键词：压气机叶片；预变形；叶型重构；流固耦合；叶片变形 |
