航空发动机低压涡轮轴结构参数建模与分析  

Modeling and Analysis on Structure Parameters of Low Pressure Turbine Shaft for Aeroengine

作　　者：田大可[1] 徐雪[1] 刘旭阳[1] 张德志[1] 

机构地区：[1]中航工业沈阳发动机设计研究所,沈阳110015

出　　处：《航空发动机》2015年第5期49-52,共4页Aeroengine

基　　金：国家重大基础研究项目资助

摘　　要：为研究成熟核心机的衍生发展能力,基于流体力学原理及强度理论,提出了1种低压涡轮轴结构参数的建模方法。根据涡扇发动机基本原理,建立了风扇叶尖直径、风扇角速度和低压涡轮轴输出扭矩的数学模型,并根据扭转强度、破坏扭矩和扭转稳定性等强度理论,建立了1种低压涡轮轴结构参数的数学模型。运用该模型讨论了某型核心机的衍生发展能力,分析了涵道比、低压涡轮轴壁厚与其外径及质量间的影响规律。结果表明:当涵道比一定时,低压涡轮轴外径与壁厚成反比,质量与壁厚成正比;当壁厚一定时,低压涡轮轴外径和质量均与涵道比成正比。In order to study the derivative development capacity of a mature core engine, a modeling method of structure parameters for LPT shaft was proposed based on the fluid mechanics basic principles and strength theory. According to the basic principles of turbofan engine ,mathematical models of diameter of fan tip, angular velocity of fan and output torque of LPT shaft were established. A mathematical model of structure parameters for LPT was built according to yield safety factor （YSF） and ultimate safety factor （USF）. The derivative development of a core engine was discussed by the model, and the influence law of the bypass ratio,wall thickness of LPT shaft on outer diameter and quality were analyzed. The results show that when the bypass ratio is constant,the outer diameter of LPT shaft is inversely proportional to the wall thickness,and the quality is proportional to the wall thickness. When the wall thickness is constant,the outer diameter and quality of LPT shaft are all proportional to the bypass ratio.

关 键 词：核心机 低压涡轮轴 涵道比 强度理论 建模 航空发动机 

分 类 号：V232.2[航空宇航科学与技术—航空宇航推进理论与工程]