Effect of hole configurations on film cooling performance
(2019) In Numerical Heat Transfer; Part A: Applications 75(11). p.725-738- Abstract
This study aims to investigate the cooling performance of various film cooling holes, including combined hole, cylinder hole, conical hole, and fan-shaped hole. For film cooling technology, a novel combined hole configuration is first proposed to improve the cooling protection for gas turbine engines. This combined hole consists of a central cylinder hole (an inclination angle of 35°) and two additional side holes (a lateral diffusion angle of 30°). Film holes for four-hole configurations have the same inlet diameter of 8 mm. The adiabatic film cooling effectiveness for each hole configuration is analyzed for varying blowing ratios (M = 0.25, 0.5, 0.75, and 1.0). Results show that the best cooling performance for the conical and... (More)
This study aims to investigate the cooling performance of various film cooling holes, including combined hole, cylinder hole, conical hole, and fan-shaped hole. For film cooling technology, a novel combined hole configuration is first proposed to improve the cooling protection for gas turbine engines. This combined hole consists of a central cylinder hole (an inclination angle of 35°) and two additional side holes (a lateral diffusion angle of 30°). Film holes for four-hole configurations have the same inlet diameter of 8 mm. The adiabatic film cooling effectiveness for each hole configuration is analyzed for varying blowing ratios (M = 0.25, 0.5, 0.75, and 1.0). Results show that the best cooling performance for the conical and fan-shaped holes is obtained at the blowing ratio of 0.75. In addition, the combined hole configuration provides a more uniform cooling protection and a better cooling performance than the other hole configurations.
(Less)
- author
- Wang, Jin LU ; Tian, Ke ; Luo, Jing and Sundén, Bengt LU
- organization
- publishing date
- 2019
- type
- Contribution to journal
- publication status
- published
- subject
- in
- Numerical Heat Transfer; Part A: Applications
- volume
- 75
- issue
- 11
- pages
- 14 pages
- publisher
- Taylor & Francis
- external identifiers
-
- scopus:85074838599
- ISSN
- 1040-7782
- DOI
- 10.1080/10407782.2019.1608762
- language
- English
- LU publication?
- yes
- id
- a6d18086-9e63-4534-b381-0005bdf8b6f7
- date added to LUP
- 2019-12-02 13:38:07
- date last changed
- 2022-04-18 19:07:09
@article{a6d18086-9e63-4534-b381-0005bdf8b6f7,
abstract = {{<p>This study aims to investigate the cooling performance of various film cooling holes, including combined hole, cylinder hole, conical hole, and fan-shaped hole. For film cooling technology, a novel combined hole configuration is first proposed to improve the cooling protection for gas turbine engines. This combined hole consists of a central cylinder hole (an inclination angle of 35°) and two additional side holes (a lateral diffusion angle of 30°). Film holes for four-hole configurations have the same inlet diameter of 8 mm. The adiabatic film cooling effectiveness for each hole configuration is analyzed for varying blowing ratios (M = 0.25, 0.5, 0.75, and 1.0). Results show that the best cooling performance for the conical and fan-shaped holes is obtained at the blowing ratio of 0.75. In addition, the combined hole configuration provides a more uniform cooling protection and a better cooling performance than the other hole configurations.</p>}},
author = {{Wang, Jin and Tian, Ke and Luo, Jing and Sundén, Bengt}},
issn = {{1040-7782}},
language = {{eng}},
number = {{11}},
pages = {{725--738}},
publisher = {{Taylor & Francis}},
series = {{Numerical Heat Transfer; Part A: Applications}},
title = {{Effect of hole configurations on film cooling performance}},
url = {{http://dx.doi.org/10.1080/10407782.2019.1608762}},
doi = {{10.1080/10407782.2019.1608762}},
volume = {{75}},
year = {{2019}},
}