航空发动机气动失稳检测管路设计研究

Design and Research of Aero-Engine Aerodynamic Instability Detection Pipeline

中文关键词:  航空发动机  失稳检测  管路  频率响应  设计流程

英文关键词:aero-engine  instability detection  pipeline  frequency response  design process

中文摘要:

      为满足航空发动机旋转失速和喘振失稳信号的实时监测需求，探讨了试验测量和机载测量失稳判别信号测量方法，两种使用场景均须考虑测压管路响应频率。分析了喘振和旋转失速过程中的压力脉动特征，喘振信号频率与发动机容腔大小相关，旋转失速信号频率与转子转速及叶片构型有关。提出了失稳测量频率响应需求，建立了由管路和传感器容腔构成的测压系统单自由度二阶模型，研究了管路气动耦合频率与声速、管路长度、管路内径、传感器容腔的关系，根据工程经验给出了管路规格设计流程,提出的“四分之一波长法”对管路频率响应精度可控制在2%范围内，可在工程上实现快速估计。当管路频率响应不满能足要求时，可通过减少管路长度的方式显著提升失稳测压系统频率。

英文摘要:

      In order to meet the real-time monitoring requirements of the rotating stall and surge instability signals of aero-engine,the measurement methods of test measurement and airborne measurement instability discrimination signals are discussed.The response frequency of the pressure measuring pipeline must be considered in both use scenarios.The characteristics of pressure pulsation in the process of surge and rotating stall are analyzed.The frequency of surge signal is related to the size of engine chamber,and the frequency of rotating stall signal is related to rotor speed and blade configuration.The requirements for frequency response of instability measurement are put forward.A single degree of freedom second-order model of pressure measurement system consisting of pipeline and sensor chamber is established.The relationship between the pipeline aerodynamic coupling frequency and sound velocity,pipeline length,pipeline inner diameter,sensor chamber is studied.The pipeline specification design process is given according to engineering experience.The proposed “quarter wavelength method” can control the accuracy of pipeline frequency response within 2%,it can realize fast estimation in engineering.When the frequency response of the pipeline is not sufficient,the frequency of the unstable pressure measurement system can be significantly increased by reducing the length of the pipeline.