Investigation of the Film-Cooling Performance of 2.5D Braided Ceramic Matrix Composite Plates with Preformed Hole

The film-cooling performance of a 2.5D braided ceramic matrix composite (CMC) plate with preformed holes was numerically studied. Four numerical models containing braided structures were established: one model with film-cooling holes preformed through fiber extrusion deformation (EP-Hole), one model...

Full description

Saved in:
Bibliographic Details
Published in:Aerospace 2021-04, Vol.8 (4), p.116
Main Authors: Zhao, Chenwei, Tu, Zecan, Mao, Junkui
Format: Article
Language:English
Subjects:
2.5D braided composite
anisotropic thermal conductivity
Braided composites
Braiding
Ceramic matrix composites
Composite materials
Composite structures
Cooling
Extrusion
film cooling
Heat conductivity
Heat resistance
Heat transfer
Investigations
Manufacturing
Mathematical models
Mechanical properties
Numerical models
Oxidation
preformed hole
R&D
Research & development
Stress concentration
Temperature
Temperature gradients
Yarn
Citations: Items that this one cites
Items that cite this one
Online Access:Get full text
Tags: Add Tag
No Tags, Be the first to tag this record!
Description
Summary:The film-cooling performance of a 2.5D braided ceramic matrix composite (CMC) plate with preformed holes was numerically studied. Four numerical models containing braided structures were established: one model with film-cooling holes preformed through fiber extrusion deformation (EP-Hole), one model with film-cooling holes directly woven through fibers (WP-Hole), and two models with directly drilled holes (DP-Hole1,2). Besides, the influence of the ratio between the equivalent thermal conductivities on the axial and radial directions of fiber Kr was investigated. The results show that the preformed holes have better performance in controlling the thermal gradient with the increase of Kr. The maximum thermal gradient around the DP-Hole is significantly higher than that of the WP-Hole and EP-Hole, and the maximum relative variation reaches 123.3%. With Kr increasing from 3.32 to 13.05, the overall cooling effectiveness on the hot-side wall decreases for all models, by about 10%. Compared with the traditional drill method, the new preformed film-cooling hole studied in this paper can reduce the temperature and the thermal gradient in the region around the holes.
ISSN:2226-4310
2226-4310
DOI:10.3390/aerospace8040116