Publication Date:
2019-06-28
Description:
A three-dimensional viscous computer code (VANS/MD) was employed to calculate the turbulent flow field at the end wall leading edge region of a 20 inch axial annular turbine cascade. The initial boundary layer roll-up and formation of the end wall vortices were computed at the vane leading edge. The calculated flow field was found to be periodic with a frequency of approximately 1600 Hz. The calculated size of the separation region for the hub endwall vortex compared favorably with measured endwall oil traces. In an effort to determine the effects of the turbulence model on the calculated unsteadiness, a laminar calculation was made. The periodic nature of the calculated flow field persisted with the frequency essentially unchanged.
Keywords:
AERODYNAMICS
Type:
NASA-CR-168275
,
NAS 1.26:168275
,
USAAVSCOM-TR-84-C-3
,
AD-A145641
Format:
application/pdf
