涡轮盘腔层流流动与传热相似研究  

Study on the similarity criteria of laminar flow and heat transfer for the turbine disc cavity

作　　者：兰昌明 赵国昌[1] 李静[2] 宋丽萍[1] 曹磊[1] 路天栋[1] 杜霞[1] 

机构地区：[1]沈阳航空航天大学航空航天工程学部院,沈阳110136 [2]沈阳航空航天大学高等教育研究所,沈阳110136 [3]辽宁省航空推进系统先进测试技术重点实验室,沈阳110136

出　　处：《沈阳航空航天大学学报》2014年第6期1-6,共6页Journal of Shenyang Aerospace University

基　　金：国家自然科学基金(项目编号:51376133);航空科学基金(项目编号:20131954004)

摘　　要：对描述转-静盘腔流体层流流动与传热的控制方程进行无量纲变换得到相似准则,获得了层流条件下流动与传热相似需满足的准则条件:Re,Ro(或Reω),Pr和Grωi(i=1,2,3)对应相等。分别对高温和低温条件下涡轮盘腔内流动和传热进行数值模拟,在满足对应准则数相等和单值性条件相似时,两个盘腔模型的无量纲速度和无量纲温度等值线分布都吻合,高温和低温模型的流场和温度场相似,从而证明了通过低温涡轮盘腔实验定量模拟高温条件下涡轮盘腔流动与传热的可行性。The governing equations of flow and heat transfer for rotor-stator disc cavity systems are carried out with dimensionless transformation, and then the similarity criteria are established for flow and heat transfer under different temperature conditions： the corresponding equality of the dimensionless numbers Re, Ro （ or Reo, ）, Pr and Gro,i （ i = 1,2,3 ）. Numerical simulation is implemented on the flow and heat transfer of two disc cavity models under high and low temperatures respectively, and the results indicate that dimensionless velocity contours distribution and dimensionless temperature contours distri- bution of the two disk cavities coincide very well, and the velocity field and temperature field are simi- lar under high and low temperature models. It is proved theoretically the feasibility of the experimental quantitative simulation of the flow and heat transfer in the turbine disc cavity under high temperature through turbine disc cavity under low temperature.

关 键 词：转-静盘腔 相似准则 数值模拟 高温实验 

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]