Article ID | Journal | Published Year | Pages | File Type |
---|---|---|---|---|
7153670 | Chinese Journal of Aeronautics | 2018 | 14 Pages |
Abstract
The swirl generator is widely used in lean-burn combustor to guarantee flame stability and reduce NOx emissions. Thus, the non-uniformities induced by the swirler would affect and damage film-cooling effectiveness on the turbine components, even blow-off coolant coverage, to some certain extent. The arrangement of film-cooling holes was normally designed to be perpendicular to the axial direction and in standard straight row. In this work we experimentally studied the effects of inlet swirl and mass flow ratio on traditional film cooling holes arrangement and a new arrangement pattern whose holes are located along the isobars. Results indicated that the swirl perturbation would damage film coverage. The film-cooling effect of endwall on which the holes are along the isobars, is invariably more promising than that of endwall on which hole arrangement is perpendicular to axial with the same mass flow of coolant, whether the inlet conditions is uniform or not.
Keywords
Related Topics
Physical Sciences and Engineering
Engineering
Aerospace Engineering
Authors
Yang ZHOU, Yang ZHANG, Xinrong SU, Xin YUAN,