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Thermal protection of rocket nozzle by using film cooling technology - Effect of lateral curvature

Guelailia, Ahmed ; Khorsi, Azzeddine ; Boudjemai, Abdelmadjid and Wang, Jin LU (2018) In International Journal of Heat and Technology 36(3). p.1070-1074
Abstract

The present paper aims to analyze the applicability of film cooling method to a rocket as a thermal protection. Lateral curvature effect on film cooling performance through a single row of cylindrical holes with different spanwise angles is investigated. Four different lateral curvature cases (C = ∞, 100, 60, 20) with four inclination angles of cooling injection holes (β= 35°, 45°, 55°, 65°) are considered. The ANSYS CFX has been used for this computational simulation. The turbulence is approximated by a shear stress transport model (SST). Detailed film effectiveness distributions are presented for several blowing ratios (0.5, 1 and 1.5). The numerical results are compared with experimental data.

Please use this url to cite or link to this publication:
author
; ; and
organization
publishing date
type
Contribution to journal
publication status
published
subject
keywords
Computational fluid dynamics, Film cooling, Heat, Mass transfer, Propulsion, Rocket nozzle, Thermal protection
in
International Journal of Heat and Technology
volume
36
issue
3
pages
5 pages
publisher
Edizioni E.T.S.
external identifiers
  • scopus:85054316023
ISSN
0392-8764
DOI
10.18280/ijht.360338
language
English
LU publication?
yes
id
1a08e1cb-d5ba-4a2a-9b2d-0c26d9f531bd
date added to LUP
2018-11-05 12:32:02
date last changed
2021-09-15 03:31:03
@article{1a08e1cb-d5ba-4a2a-9b2d-0c26d9f531bd,
  abstract     = {<p>The present paper aims to analyze the applicability of film cooling method to a rocket as a thermal protection. Lateral curvature effect on film cooling performance through a single row of cylindrical holes with different spanwise angles is investigated. Four different lateral curvature cases (C = ∞, 100, 60, 20) with four inclination angles of cooling injection holes (β= 35°, 45°, 55°, 65°) are considered. The ANSYS CFX has been used for this computational simulation. The turbulence is approximated by a shear stress transport model (SST). Detailed film effectiveness distributions are presented for several blowing ratios (0.5, 1 and 1.5). The numerical results are compared with experimental data.</p>},
  author       = {Guelailia, Ahmed and Khorsi, Azzeddine and Boudjemai, Abdelmadjid and Wang, Jin},
  issn         = {0392-8764},
  language     = {eng},
  month        = {09},
  number       = {3},
  pages        = {1070--1074},
  publisher    = {Edizioni E.T.S.},
  series       = {International Journal of Heat and Technology},
  title        = {Thermal protection of rocket nozzle by using film cooling technology - Effect of lateral curvature},
  url          = {http://dx.doi.org/10.18280/ijht.360338},
  doi          = {10.18280/ijht.360338},
  volume       = {36},
  year         = {2018},
}