摘要
基于平行压气机原理,建立了进气畸变对大涵道比涡扇发动机稳定性影响的理论模型和计算分析方法,评估了总压畸变和总温畸变对某型大涵道比涡扇发动机稳定性的影响,获取了发动机的临界畸变指数和首发失稳级组。结果表明:总压畸变在风扇中衰减幅度最大,发动机在高转速下运行达到临界总压畸变值时,风扇率先失稳,在低转速下运行时为增压级率先失稳;总温畸变在高压压气机中衰减幅度最大,发动机在高转速运行达到临界总温畸变值时,高压压气机率先失稳,在低转速运行时为增压级率先失稳。
The theory model and calculation analysis method of the effect of inlet distortion on the high bypass ratio turbofan engine stability were built based on the parallel compressor conception. The influence of total pressure distortion and total temperature distortion on a high bypass ratio turbofan engine stability were evaluated. The critical distortion index and first-episode instability staging were obtained. The results show that the most attenuation occurs in the fan under a given total pressure distortion condition; when the total pressure distortion reaches the critical value, the fan first loses stability at high rotational speed while booster first loses stability at low rotational speed; the most attenuation occurs in the high pressure compressor under a given total temperature distortion condition; when the total temperature distortion reaches the critical value, the high pressure compressor first loses stability at high rotational speed while booster first loses stability at low rotational speed.
出处
《航空发动机》
2013年第6期6-12,共7页
Aeroengine
基金
总装基础研究项目资助
