Rotational effects on film cooling performance Simulation of a louver cooling scheme on a rotating turbine blade

C. X Z Zhang, Ibrahim Hassan

Research output: Contribution to journalArticle

8 Citations (Scopus)

Abstract

Purpose - Numerical simulations were carried out for two cooling schemes, a circular hole and a louver cooling scheme, at the leading edge of a rotor blade in a complete turbine stage. Design/methodology/approach - Two holes were positioned at the leading edge of a rotating blade, one on the pressure side and the other on the suction side. The methodology was validated with a circular hole case. Numerical results of cooling effectiveness for three blowing ratios at three rotational speeds were successfully obtained. Both blowing ratio and rotating speed of the rotor affect the cooling effectiveness level. Findings - It was shown that for the circular hole, the blowing ratio is the dominant factor at low blowing ratios and the rotational speed is the dominant factor at high blow ratios when jet is prone to lift off in determining the cooling effectiveness level. For the louver scheme, a higher rotational speed leads to a higher level of cooling effectiveness since jet liftoff is avoided. Originality/value - There are only a few studies of film cooling on a rotational turbine blade and very few studies of film cooling at the leading edge of a rotating turbine blade in the open literature. The present work presents a challenging CFD case. The analysis of film cooling at the leading edge of an airfoil was presented, which sheds light on the physics of film cooling and should prove helpful to the cooling designs of turbine blades.

Original languageEnglish
Pages (from-to)622-640
Number of pages19
JournalInternational Journal of Numerical Methods for Heat and Fluid Flow
Volume22
Issue number5
DOIs
Publication statusPublished - 2012
Externally publishedYes

Fingerprint

Film Cooling
Turbine Blade
Turbomachine blades
Cooling
Rotating
Turbines
Simulation
Blow molding
Blade
Rotor
Airfoil
Suction
Turbine
Rotors
Design Methodology
Physics
Numerical Simulation
Numerical Results
Airfoils
Methodology

Keywords

  • CFD
  • Cooling systems
  • Film cooling
  • Gas turbine
  • Leading edge
  • Louver scheme
  • Rotating blade
  • Turbines

ASJC Scopus subject areas

  • Mechanics of Materials
  • Mechanical Engineering
  • Computer Science Applications
  • Applied Mathematics

Cite this

@article{a50b86bf328f48e18b05a0c807a20fd7,
title = "Rotational effects on film cooling performance Simulation of a louver cooling scheme on a rotating turbine blade",
abstract = "Purpose - Numerical simulations were carried out for two cooling schemes, a circular hole and a louver cooling scheme, at the leading edge of a rotor blade in a complete turbine stage. Design/methodology/approach - Two holes were positioned at the leading edge of a rotating blade, one on the pressure side and the other on the suction side. The methodology was validated with a circular hole case. Numerical results of cooling effectiveness for three blowing ratios at three rotational speeds were successfully obtained. Both blowing ratio and rotating speed of the rotor affect the cooling effectiveness level. Findings - It was shown that for the circular hole, the blowing ratio is the dominant factor at low blowing ratios and the rotational speed is the dominant factor at high blow ratios when jet is prone to lift off in determining the cooling effectiveness level. For the louver scheme, a higher rotational speed leads to a higher level of cooling effectiveness since jet liftoff is avoided. Originality/value - There are only a few studies of film cooling on a rotational turbine blade and very few studies of film cooling at the leading edge of a rotating turbine blade in the open literature. The present work presents a challenging CFD case. The analysis of film cooling at the leading edge of an airfoil was presented, which sheds light on the physics of film cooling and should prove helpful to the cooling designs of turbine blades.",
keywords = "CFD, Cooling systems, Film cooling, Gas turbine, Leading edge, Louver scheme, Rotating blade, Turbines",
author = "Zhang, {C. X Z} and Ibrahim Hassan",
year = "2012",
doi = "10.1108/09615531211231271",
language = "English",
volume = "22",
pages = "622--640",
journal = "International Journal of Numerical Methods for Heat and Fluid Flow",
issn = "0961-5539",
publisher = "Emerald Group Publishing Ltd.",
number = "5",

}

TY - JOUR

T1 - Rotational effects on film cooling performance Simulation of a louver cooling scheme on a rotating turbine blade

AU - Zhang, C. X Z

AU - Hassan, Ibrahim

PY - 2012

Y1 - 2012

N2 - Purpose - Numerical simulations were carried out for two cooling schemes, a circular hole and a louver cooling scheme, at the leading edge of a rotor blade in a complete turbine stage. Design/methodology/approach - Two holes were positioned at the leading edge of a rotating blade, one on the pressure side and the other on the suction side. The methodology was validated with a circular hole case. Numerical results of cooling effectiveness for three blowing ratios at three rotational speeds were successfully obtained. Both blowing ratio and rotating speed of the rotor affect the cooling effectiveness level. Findings - It was shown that for the circular hole, the blowing ratio is the dominant factor at low blowing ratios and the rotational speed is the dominant factor at high blow ratios when jet is prone to lift off in determining the cooling effectiveness level. For the louver scheme, a higher rotational speed leads to a higher level of cooling effectiveness since jet liftoff is avoided. Originality/value - There are only a few studies of film cooling on a rotational turbine blade and very few studies of film cooling at the leading edge of a rotating turbine blade in the open literature. The present work presents a challenging CFD case. The analysis of film cooling at the leading edge of an airfoil was presented, which sheds light on the physics of film cooling and should prove helpful to the cooling designs of turbine blades.

AB - Purpose - Numerical simulations were carried out for two cooling schemes, a circular hole and a louver cooling scheme, at the leading edge of a rotor blade in a complete turbine stage. Design/methodology/approach - Two holes were positioned at the leading edge of a rotating blade, one on the pressure side and the other on the suction side. The methodology was validated with a circular hole case. Numerical results of cooling effectiveness for three blowing ratios at three rotational speeds were successfully obtained. Both blowing ratio and rotating speed of the rotor affect the cooling effectiveness level. Findings - It was shown that for the circular hole, the blowing ratio is the dominant factor at low blowing ratios and the rotational speed is the dominant factor at high blow ratios when jet is prone to lift off in determining the cooling effectiveness level. For the louver scheme, a higher rotational speed leads to a higher level of cooling effectiveness since jet liftoff is avoided. Originality/value - There are only a few studies of film cooling on a rotational turbine blade and very few studies of film cooling at the leading edge of a rotating turbine blade in the open literature. The present work presents a challenging CFD case. The analysis of film cooling at the leading edge of an airfoil was presented, which sheds light on the physics of film cooling and should prove helpful to the cooling designs of turbine blades.

KW - CFD

KW - Cooling systems

KW - Film cooling

KW - Gas turbine

KW - Leading edge

KW - Louver scheme

KW - Rotating blade

KW - Turbines

UR - http://www.scopus.com/inward/record.url?scp=84864867911&partnerID=8YFLogxK

UR - http://www.scopus.com/inward/citedby.url?scp=84864867911&partnerID=8YFLogxK

U2 - 10.1108/09615531211231271

DO - 10.1108/09615531211231271

M3 - Article

VL - 22

SP - 622

EP - 640

JO - International Journal of Numerical Methods for Heat and Fluid Flow

JF - International Journal of Numerical Methods for Heat and Fluid Flow

SN - 0961-5539

IS - 5

ER -