进气畸变条件下压气机转子叶片的 振动特性研究

航空发动机研制及适航要求中均明确提出发动机零部件的振动特性分析和测试要求,包括评估进气流场畸变对振动特性的影响。对某航空发动机压气机第1级转子叶片进行振动特性计算分析,开展自然进气和进气畸变条件下的叶片振动应力测试。计算分析和测试结果表明:计算分析结果与自然进气条件下测试的叶片共振转速及振动频率一致性好,其激振源主要是压气机结构因素;在进气畸变条件下激振源更丰富,与自然进气条件相比,叶片会被激起额外的振动,且在同一共振转速下振动幅值较大,进气畸变对转子叶片的振动特性产生重要影响。在发动机研制过程中,为提高叶片工作的可靠性,需要加强进气畸变条件下的叶片振动特性试验研究。

Study on Vibration Characteristics of Compressor Rotor Blade under Inlet Flow distortion

In the development and airworthiness requirements of aeroengine,the requirements of vibration characteristic analysis and test of engine parts were clearly put forward,including the evaluation of the effect of inlet flow distortion on vibration characteristics. The vibration characteristics of the first-stage rotor blade of an aeroengine compressor were calculated and analyzed,and the vibration stress of the blade under the condition of natural inlet and inlet flow distortion was tested. The calculated and tested results show that the calculated results are in good agreement with the resonant speed and vibration frequency of the blade tested under the natural inlet condition,and the main vibration source of excitation is the factor of compressor structure. Under the condition of inlet fiow distortion,the vibration source of excitation is more abundant. Compared with the natural inlet flow condition,the blade will be excited extra vibration,and the amplitude of vibration is larger at the same resonant speed. The inlet flow distortion has an important effect on the vibration characteristics of rotor blade. In order to improve the reliability of the blade in the process of engine development,it is necessary to strengthen the tested study on the vibration characteristics of the blade under the condition of inlet flow distortion.