TY - GEN
T1 - Numerical analysis on the flow characteristics of rotating axial orifices under non-rotation method
AU - Niu, Jiajia
AU - Liu, Gaowen
AU - Feng, Qing
AU - Liu, Cunliang
AU - Zhou, Li
AU - Wu, Heng
N1 - Publisher Copyright:
© 2018 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.
PY - 2018
Y1 - 2018
N2 - As an important throttling component in the engine internal cooling system, rotating orifices are widely used in rotating parts like turbine disks, drums, shafts and so on. Considering the difficulty in carrying out the experiment and measurement, a non-rotation method to measure the discharge coefficient of an rotating axial orifice was presented in this paper. Numerical simulation was conducted to study the difference of flow characteristics between rotation method and non-rotation method as well as the influence of the incidence angle in the range of 0°-70°. Results show that: within the range of parameters studied, the distributions of relative total velocity and relative total pressure using non-rotation method are quite similar to those under rotation method. The deviation of relative total velocity between the two methods is less than 5%. The deviation of relative total pressure is less than 0.5%, and that of discharge coefficient is less than 3.54%.
AB - As an important throttling component in the engine internal cooling system, rotating orifices are widely used in rotating parts like turbine disks, drums, shafts and so on. Considering the difficulty in carrying out the experiment and measurement, a non-rotation method to measure the discharge coefficient of an rotating axial orifice was presented in this paper. Numerical simulation was conducted to study the difference of flow characteristics between rotation method and non-rotation method as well as the influence of the incidence angle in the range of 0°-70°. Results show that: within the range of parameters studied, the distributions of relative total velocity and relative total pressure using non-rotation method are quite similar to those under rotation method. The deviation of relative total velocity between the two methods is less than 5%. The deviation of relative total pressure is less than 0.5%, and that of discharge coefficient is less than 3.54%.
UR - http://www.scopus.com/inward/record.url?scp=85066495473&partnerID=8YFLogxK
U2 - 10.2514/6.2018-4735
DO - 10.2514/6.2018-4735
M3 - 会议稿件
AN - SCOPUS:85066495473
SN - 9781624105708
T3 - 2018 Joint Propulsion Conference
BT - 2018 Joint Propulsion Conference
PB - American Institute of Aeronautics and Astronautics Inc, AIAA
T2 - 54th AIAA/SAE/ASEE Joint Propulsion Conference, 2018
Y2 - 9 July 2018 through 11 July 2018
ER -