航空发动机燃油阶跃试验供油规律
Fuel supply law of aero-engine fuel spiking test
赵红娇 1韩文俊 1李俊1
作者信息
- 1. 中国航发沈阳发动机研究所 总体五部,沈阳 110015
- 折叠
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.
Abstract
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Key words
aero-engine/surge margin/transient simulation/fuel spiking test/fuel supply law引用本文复制引用
基金项目
中国航发集团自立项目(HFZL2018CXY021)
出版年
2024
国家科技期刊平台
NSTL
万方数据