Investigation for the improvement of film cooling effectiveness on a high pressure Turbine aerofoil with shaped film holes

Batchu Suresh, Palvadi Sai Abhilash, N. Yagnesh Sharma, V. Kesavan, D. Kishore Prasad

Research output: Contribution to journalConference article

Abstract

Modern day gas turbines are operating at gas temperatures which are close to melting temperature of the turbine aerofoil materials. It is essential to cool High Pressure Turbine (HPT) aerofoils such as Nozzle guide vane (NGV) and Rotor blades to improve their creep life to achieve safe life and reliability. Film cooling protects the blade surface from hot gas by providing a cool insulating layer between hot gas stream and the airfoil metal surface. Film cooling effectiveness is a measure of how well the metal surface is protected from the hot gas stream by the layer of cool secondary air. Cooling hole geometry is one of the key parameters which influences the film cooling coverage. Earlier aerofoils were with cylindrical holes, whereas current advanced aero engines are using shaped holes to achive higher effectiveness and better spanwise coverage. The current study is carried out with one of the shaped hole configuration namely, laid back fan shaped hole configuration on HPT turbine rotor blade without rotation. The advantage of using shaped hole over cylindrical hole is brought out in this paper. CFD analysis is carried out using FloEFD software for prediction of film cooling effectiveness for the film holes at one of the peak operating condition. The CFD analysis is validated with measured film cooling effectiveness data. The advantage of using laid back fan shaped hole is brought out from cooling effectiveness point of view. Parametric analysis is carried out for film cooling effectiveness at different blowing ratio (BR) = 1.0 to 2.5, turbulence intensity (Tu) = 5%, 7%, 9 % and fan angle (γ) = 10 ͦ & 12 ͦ of shaped film hole.

Original languageEnglish
Pages (from-to)860-864
Number of pages5
JournalInternational Conference on Computational Methods for Thermal Problems
Issue number223309
Publication statusPublished - 01-01-2018
Event5th International Conference on Computational Methods for Thermal Problems, THERMACOMP 2018 - Bengaluru, India
Duration: 09-07-201811-07-2018

Fingerprint

Film Cooling
Turbine
Airfoils
Turbines
Cooling
Gases
Fans
Blade
Turbomachine blades
Computational fluid dynamics
Rotors
Metals
Rotor
Coverage
Blow molding
Parametric Analysis
Aeroengine
Configuration
Gas Turbine
Gas turbines

All Science Journal Classification (ASJC) codes

  • Fluid Flow and Transfer Processes
  • Computational Mathematics
  • Numerical Analysis

Cite this

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title = "Investigation for the improvement of film cooling effectiveness on a high pressure Turbine aerofoil with shaped film holes",
abstract = "Modern day gas turbines are operating at gas temperatures which are close to melting temperature of the turbine aerofoil materials. It is essential to cool High Pressure Turbine (HPT) aerofoils such as Nozzle guide vane (NGV) and Rotor blades to improve their creep life to achieve safe life and reliability. Film cooling protects the blade surface from hot gas by providing a cool insulating layer between hot gas stream and the airfoil metal surface. Film cooling effectiveness is a measure of how well the metal surface is protected from the hot gas stream by the layer of cool secondary air. Cooling hole geometry is one of the key parameters which influences the film cooling coverage. Earlier aerofoils were with cylindrical holes, whereas current advanced aero engines are using shaped holes to achive higher effectiveness and better spanwise coverage. The current study is carried out with one of the shaped hole configuration namely, laid back fan shaped hole configuration on HPT turbine rotor blade without rotation. The advantage of using shaped hole over cylindrical hole is brought out in this paper. CFD analysis is carried out using FloEFD software for prediction of film cooling effectiveness for the film holes at one of the peak operating condition. The CFD analysis is validated with measured film cooling effectiveness data. The advantage of using laid back fan shaped hole is brought out from cooling effectiveness point of view. Parametric analysis is carried out for film cooling effectiveness at different blowing ratio (BR) = 1.0 to 2.5, turbulence intensity (Tu) = 5{\%}, 7{\%}, 9 {\%} and fan angle (γ) = 10 ͦ & 12 ͦ of shaped film hole.",
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Investigation for the improvement of film cooling effectiveness on a high pressure Turbine aerofoil with shaped film holes. / Suresh, Batchu; Abhilash, Palvadi Sai; Yagnesh Sharma, N.; Kesavan, V.; Kishore Prasad, D.

In: International Conference on Computational Methods for Thermal Problems, No. 223309, 01.01.2018, p. 860-864.

Research output: Contribution to journalConference article

TY - JOUR

T1 - Investigation for the improvement of film cooling effectiveness on a high pressure Turbine aerofoil with shaped film holes

AU - Suresh, Batchu

AU - Abhilash, Palvadi Sai

AU - Yagnesh Sharma, N.

AU - Kesavan, V.

AU - Kishore Prasad, D.

PY - 2018/1/1

Y1 - 2018/1/1

N2 - Modern day gas turbines are operating at gas temperatures which are close to melting temperature of the turbine aerofoil materials. It is essential to cool High Pressure Turbine (HPT) aerofoils such as Nozzle guide vane (NGV) and Rotor blades to improve their creep life to achieve safe life and reliability. Film cooling protects the blade surface from hot gas by providing a cool insulating layer between hot gas stream and the airfoil metal surface. Film cooling effectiveness is a measure of how well the metal surface is protected from the hot gas stream by the layer of cool secondary air. Cooling hole geometry is one of the key parameters which influences the film cooling coverage. Earlier aerofoils were with cylindrical holes, whereas current advanced aero engines are using shaped holes to achive higher effectiveness and better spanwise coverage. The current study is carried out with one of the shaped hole configuration namely, laid back fan shaped hole configuration on HPT turbine rotor blade without rotation. The advantage of using shaped hole over cylindrical hole is brought out in this paper. CFD analysis is carried out using FloEFD software for prediction of film cooling effectiveness for the film holes at one of the peak operating condition. The CFD analysis is validated with measured film cooling effectiveness data. The advantage of using laid back fan shaped hole is brought out from cooling effectiveness point of view. Parametric analysis is carried out for film cooling effectiveness at different blowing ratio (BR) = 1.0 to 2.5, turbulence intensity (Tu) = 5%, 7%, 9 % and fan angle (γ) = 10 ͦ & 12 ͦ of shaped film hole.

AB - Modern day gas turbines are operating at gas temperatures which are close to melting temperature of the turbine aerofoil materials. It is essential to cool High Pressure Turbine (HPT) aerofoils such as Nozzle guide vane (NGV) and Rotor blades to improve their creep life to achieve safe life and reliability. Film cooling protects the blade surface from hot gas by providing a cool insulating layer between hot gas stream and the airfoil metal surface. Film cooling effectiveness is a measure of how well the metal surface is protected from the hot gas stream by the layer of cool secondary air. Cooling hole geometry is one of the key parameters which influences the film cooling coverage. Earlier aerofoils were with cylindrical holes, whereas current advanced aero engines are using shaped holes to achive higher effectiveness and better spanwise coverage. The current study is carried out with one of the shaped hole configuration namely, laid back fan shaped hole configuration on HPT turbine rotor blade without rotation. The advantage of using shaped hole over cylindrical hole is brought out in this paper. CFD analysis is carried out using FloEFD software for prediction of film cooling effectiveness for the film holes at one of the peak operating condition. The CFD analysis is validated with measured film cooling effectiveness data. The advantage of using laid back fan shaped hole is brought out from cooling effectiveness point of view. Parametric analysis is carried out for film cooling effectiveness at different blowing ratio (BR) = 1.0 to 2.5, turbulence intensity (Tu) = 5%, 7%, 9 % and fan angle (γ) = 10 ͦ & 12 ͦ of shaped film hole.

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M3 - Conference article

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JO - International Conference on Computational Methods for Thermal Problems

JF - International Conference on Computational Methods for Thermal Problems

SN - 2305-5995

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