Numerical analysis of heat transfer in typical turbine blade cooling configuration of ribbed passage and pin fin arrays

Jianxing Zhou; Zhi Tao; Hong Wu; Shuiting Ding

Numerical analysis of heat transfer in typical turbine blade cooling configuration of ribbed passage and pin fin arrays

Jianxing Zhou^*
, Zhi Tao
, Hong Wu
, Shuiting Ding

^*Corresponding author for this work

Research institute of Aero-Engine

Beihang University

Research output: Contribution to journal › Article › peer-review

2 Scopus citations

Abstract

Numerical simulation was used to investigate the heat transfer of a typical turbine blade cooling configuration of ribbed passage and staggered pin fin arrays. The results indicate that the distribution of heat transfer coefficient lacks of uniformity in the pin fin region. The calculating results show that blade top and root regions have much higher heat transfer coefficients and so is the areas near ejection holes, whereas much lower heat transfer coefficient is observed for the central region of the blade.

Original language	English
Pages (from-to)	147-151
Number of pages	5
Journal	Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics
Volume	30
Issue number	2
State	Published - Feb 2004

Keywords

Heat transfer
Pin fin arrays
Ribbed
Turbine
Turbine blade
Turbojet engines

Cite this

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title = "Numerical analysis of heat transfer in typical turbine blade cooling configuration of ribbed passage and pin fin arrays",

abstract = "Numerical simulation was used to investigate the heat transfer of a typical turbine blade cooling configuration of ribbed passage and staggered pin fin arrays. The results indicate that the distribution of heat transfer coefficient lacks of uniformity in the pin fin region. The calculating results show that blade top and root regions have much higher heat transfer coefficients and so is the areas near ejection holes, whereas much lower heat transfer coefficient is observed for the central region of the blade.",

keywords = "Heat transfer, Pin fin arrays, Ribbed, Turbine, Turbine blade, Turbojet engines",

author = "Jianxing Zhou and Zhi Tao and Hong Wu and Shuiting Ding",

year = "2004",

month = feb,

language = "英语",

volume = "30",

pages = "147--151",

journal = "Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics",

issn = "1001-5965",

publisher = "Beijing University of Aeronautics and Astronautics (BUAA)",

number = "2",

}

Numerical analysis of heat transfer in typical turbine blade cooling configuration of ribbed passage and pin fin arrays. / Zhou, Jianxing; Tao, Zhi; Wu, Hong et al.
In: Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics, Vol. 30, No. 2, 02.2004, p. 147-151.

Research output: Contribution to journal › Article › peer-review

TY - JOUR

T1 - Numerical analysis of heat transfer in typical turbine blade cooling configuration of ribbed passage and pin fin arrays

AU - Zhou, Jianxing

AU - Tao, Zhi

AU - Wu, Hong

AU - Ding, Shuiting

PY - 2004/2

Y1 - 2004/2

N2 - Numerical simulation was used to investigate the heat transfer of a typical turbine blade cooling configuration of ribbed passage and staggered pin fin arrays. The results indicate that the distribution of heat transfer coefficient lacks of uniformity in the pin fin region. The calculating results show that blade top and root regions have much higher heat transfer coefficients and so is the areas near ejection holes, whereas much lower heat transfer coefficient is observed for the central region of the blade.

AB - Numerical simulation was used to investigate the heat transfer of a typical turbine blade cooling configuration of ribbed passage and staggered pin fin arrays. The results indicate that the distribution of heat transfer coefficient lacks of uniformity in the pin fin region. The calculating results show that blade top and root regions have much higher heat transfer coefficients and so is the areas near ejection holes, whereas much lower heat transfer coefficient is observed for the central region of the blade.

KW - Heat transfer

KW - Pin fin arrays

KW - Ribbed

KW - Turbine

KW - Turbine blade

KW - Turbojet engines

UR - https://www.scopus.com/pages/publications/3042769687

M3 - 文章

AN - SCOPUS:3042769687

SN - 1001-5965

VL - 30

SP - 147

EP - 151

JO - Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics

JF - Beijing Hangkong Hangtian Daxue Xuebao/Journal of Beijing University of Aeronautics and Astronautics

IS - 2

ER -

Numerical analysis of heat transfer in typical turbine blade cooling configuration of ribbed passage and pin fin arrays

Abstract

Keywords

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