航空发动机燃油阶跃试验供油规律  

Fuel supply law of aero-engine fuel spiking test

作　　者：赵红娇 韩文俊 李俊 ZHAO Hongjiao;HAN Wenjun;LI Jun(The Fifth Design Department,AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]中国航发沈阳发动机研究所总体五部,沈阳110015

出　　处：《沈阳航空航天大学学报》2024年第1期18-26,共9页Journal of Shenyang Aerospace University

基　　金：中国航发集团自立项目(项目编号:HFZL2018CXY021)。

摘　　要：为了分析燃油阶跃逼喘试验中供油规律对发动机的影响,以小涵道比混合排气涡扇发动机为研究对象,将发动机模化为典型的基本部件组成的系统,构建考虑转子动力学方程及容积效应的平衡方程。对发动机燃油阶跃逼喘过程进行仿真,理论计算结果与试验数据误差在4%以内,验证了计算方法的准确性。通过仿真获取了阶跃供油规律的关键影响因素,仿真结果能够为发动机燃油阶跃试验的试验提供理论基础,降低发动机在燃油阶跃逼喘过程中的超温、超转风险,具有一定的工程意义。In order to analyze the influence of fuel supply law of aero-engine in the fuel spiking surge test,a hybrid exhaust turbofan engine with a small bypass ratio was taken as the research object.The engine was modeled as a typical system composed of essential components and built an equilibrium equation considering the rotor dynamics equation and volume effect.The fuel spiking surge process of the engine was simulated.The error between the simulation result and experimental data was within 4%,which verifies the accuracy of the calculation method.The key influencing factors of the step fuel supply law were obtained through the simulation.The simulation results can provide a theoretical basis for the fuel spiking test of the engine and reduce the risk of overtemperature and overturning during the fuel spiking surge process,which has certain engineering significance.

关 键 词：航空发动机 喘振边界 过渡态仿真 燃油阶跃试验 供油规律 

分 类 号：V231[航空宇航科学与技术—航空宇航推进理论与工程]