Thermal protection of rocket nozzle by using film cooling technology - Effect of lateral curvature
(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.
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https://lup.lub.lu.se/record/1a08e1cb-d5ba-4a2a-9b2d-0c26d9f531bd
- author
- Guelailia, Ahmed ; Khorsi, Azzeddine ; Boudjemai, Abdelmadjid and Wang, Jin LU
- organization
- publishing date
- 2018-09-01
- 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
- 2022-03-17 18:46:47
@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}}, keywords = {{Computational fluid dynamics; Film cooling; Heat; Mass transfer; Propulsion; Rocket nozzle; Thermal protection}}, 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}}, }