发动机热力循环参数对流路参数的影响  

Influence of engine thermodynamic cycle parameters on flow path parameters

作　　者：李瑞军 计自飞 LI Rui-jun;JI Zi-fei(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,沈阳110015

出　　处：《沈阳航空航天大学学报》2022年第5期30-36,共7页Journal of Shenyang Aerospace University

基　　金：航空发动机集团联合基金(项目编号:******)。

摘　　要：为了研究航空发动机热力循环参数与流路参数之间的相互影响关系,基于航空发动机稳态性能计算模型和涡扇发动机流路参数计算模型,建立航空发动机热力循环参数与流路参数之间的迭代模型。利用该计算模型研究了军用小涵道比涡扇发动机总增压比、涡轮前温度和涵道比等热力循环参数变化对发动机流路参数、涡轮AN 2值等参数的影响。研究结果表明,总增压比、涡轮前温度、涵道比对发动机流路参数和AN 2值等有非常大的影响。在尺寸和级数不变的情况下,增加总增压比会带来核心机部件气动负荷和机械应力的增加;涡轮前温度增加有利于降低涡轮AN 2值;涵道比增加导致核心机部件尺寸减小,低压涡轮尺寸增加。该计算模型能够实现在开展航空发动机热力循环参数分析时,兼顾考虑部件流路尺寸、叶轮机负荷系数和涡轮AN 2值等参数,在航空发动机总体性能概念设计阶段具有较好的工程实用价值。To study the interaction between the thermodynamic cycle parameters and flow path parameters of the aero-engine,an iterative model between the thermodynamic cycle parameters and flow path parameters of the aero-engine was established based on the steady-state performance calculation model of aero-engine and the flow path parameters modeling method of the turbofan engine.Based on the calculation model,the effects of the thermodynamic cycle parameters such as total supercharging ratio,turbine front temperature,and bypass ratio on the flow path parameters and turbine AN 2 values of the military turbofan engine with a small bypass ratio were studied.The calculation results show that there is a strong influence of the total pressure ratio,turbine front temperature,and bypass ratio on the flow path size of the engine and the turbine AN 2 value.When the size and the series remain unchanged,the increase of the total supercharging ratio leads to the increase of the aerodynamic load and mechanical stress of the core components.The increase of the turbine front temperature is conducive to the decrease of the AN 2 value of the turbine,and the increase of bypass ratio leads to the decrease of the size of the core components and the increase of the size of the low-pressure turbine.The calculation model can take into account the parameters such as component flow path size,turbine load factor and turbine AN 2 value ect when analyzing the thermodynamic cycle parameters of aero-engine.It has good engineering application value in the conceptual design stage of aero-engine overall performance.

关 键 词：涡扇发动机 总增压比 涵道比 循环参数 流路参数 

分 类 号：V235.13[航空宇航科学与技术—航空宇航推进理论与工程]