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Effect of hole configurations on film cooling performance

Wang, Jin LU ; Tian, Ke ; Luo, Jing and Sundén, Bengt LU (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.

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author
organization
publishing date
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
2020-04-02 02:45:21
@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},
}