篦齿封严对核心机瞬态叶尖间隙仿真的影响  

Influence of Labyrinth Seal on Transient Tip Clearance Simulation of Core Engine

作　　者：郭纳贤 毛军逵[1,2] 张宏宇 付鹏哲 王飞龙 GUO Na-xian;MAO Jun-kui;ZHANG Hong-yu;FU Peng-zhe;WANG Fei-long(College of Energy and Power Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing 210016,China;Jiangsu Province Key Laboratory of Aerospace Power System,Nanjing 210016,China;AECC Shenyang Engine Research Institute,Shenyang 110015,China)

机构地区：[1]南京航空航天大学能源与动力学院,南京210016 [2]江苏省航空动力系统重点实验室,南京210016 [3]中国航发沈阳发动机研究所,沈阳110015

出　　处：《航空发动机》2025年第1期124-132,共9页Aeroengine

基　　金：国家级研究项目资助。

摘　　要：针对核心机瞬态叶尖间隙仿真中存在多物理场耦合的问题,综合1维流体网络法、2维轴对称有限元法、温度与位移的工程算法,在空气系统计算与轮盘机匣温度场计算间双向传递热流;使轮盘机匣温度场为位移计算提供材料物性的参考温度与热载荷,位移计算反向提供气固换热面积;同时使位移计算为空气系统计算提供篦齿间隙值,建立基于气热固双向耦合的瞬态间隙预估方法,并以核心机为模型,重点研究了篦齿间隙对叶尖间隙的影响。结果表明:在慢车状态下篦齿间隙对叶尖间隙的影响微弱;而在起飞状态下,未耦合篦齿间隙将造成对应叶尖间隙值最大0.125 mm的计算误差,相对其间隙变化量达22.4%;但当篦齿间隙变化量小于初值的44.9%,或目标叶尖间隙未与该篦齿所在空气系统支路相关时,上述影响将变得很小。对于起飞工况,当篦齿间隙初值增大25%后,相应叶尖间隙变化量将增大15.7%。In order to solve the problem of multiple physical fields coupling in the simulation of transient tip clearance about core engine,a 1D fluid network method,2D axisymmetric finite element method,and the engineering calculation of temperature and displacement were integrated in this paper to enable bidirectional heat transfer between air system calculation and temperature field calculation of disc and casing;The temperature field of disc and casing provide a reference temperature of material properties and thermal load for displacement calculation,while displacement calculation provides the air-solid heat transfer area in reverse;At the same time,displacement calculation provides the seal clearance for air system calculation,finally,a transient clearance prediction method was established based on aero-thermo-structural two-way coupling,with a core engine as the model,the influence of the seal clearance on the tip clearance was emphatically studied.The results show that the seal clearance has a slight effect on tip clearance in idle state.In take-off state,without coupling seal clearance will cause the maximum calculation error of the corresponding tip clearance by 0.125mm,and it is up to 22.4%about the change of its tip clearance.However,when the seal clearance change is less than 44.9%of its initial value,or the target tip clearance is not related to the flow path where the seal is located,the above influence will be slight.When the initial seal clearance value increases by 25%,the corresponding tip clearance variation will increase by 15.7%in the take-off state.

关 键 词：瞬态叶尖间隙 篦齿间隙 气热固双向耦合 核心机 

分 类 号：V231.1[航空宇航科学与技术—航空宇航推进理论与工程]