Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721262274
Category :
Languages : en
Pages : 26
Book Description
Experimental and computational studies have been performed to investigate the detailed distribution of convective heat transfer coefficients on the first-stage blade tip surface for a geometry typical of large power generation turbines (greater than 100 MW) In a previous work the numerical heat transfer results for a sharp edge blade tip and a radiused blade tip were presented. More recently several other tip treatments have been considered for which the tip heat transfer has been measured and documented. This paper is concerned with the numerical prediction of the tip surface heat transfer for radiused blade tip equipped with mean-camberline strip (or "squealer" as it is often called). The heat transfer results are compared with the experimental results and discussed. The effectiveness of the mean-camberline strip in reducing the tip leakage and the tip heat transfer as compared to a radiused edge tip and sharp edge tip was studied. The calculations show that the sharp edge tip works best (among the cases considered) in reducing the tip leakage flow and the tip heat transfer. Ameri, A.A. Glenn Research Center NASA/CR-2001-210764, NAS 1.26:210764, E-12693, Rept-2001-GT-0156
Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped with a Mean-Camberline Strip
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721262274
Category :
Languages : en
Pages : 26
Book Description
Experimental and computational studies have been performed to investigate the detailed distribution of convective heat transfer coefficients on the first-stage blade tip surface for a geometry typical of large power generation turbines (greater than 100 MW) In a previous work the numerical heat transfer results for a sharp edge blade tip and a radiused blade tip were presented. More recently several other tip treatments have been considered for which the tip heat transfer has been measured and documented. This paper is concerned with the numerical prediction of the tip surface heat transfer for radiused blade tip equipped with mean-camberline strip (or "squealer" as it is often called). The heat transfer results are compared with the experimental results and discussed. The effectiveness of the mean-camberline strip in reducing the tip leakage and the tip heat transfer as compared to a radiused edge tip and sharp edge tip was studied. The calculations show that the sharp edge tip works best (among the cases considered) in reducing the tip leakage flow and the tip heat transfer. Ameri, A.A. Glenn Research Center NASA/CR-2001-210764, NAS 1.26:210764, E-12693, Rept-2001-GT-0156
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721262274
Category :
Languages : en
Pages : 26
Book Description
Experimental and computational studies have been performed to investigate the detailed distribution of convective heat transfer coefficients on the first-stage blade tip surface for a geometry typical of large power generation turbines (greater than 100 MW) In a previous work the numerical heat transfer results for a sharp edge blade tip and a radiused blade tip were presented. More recently several other tip treatments have been considered for which the tip heat transfer has been measured and documented. This paper is concerned with the numerical prediction of the tip surface heat transfer for radiused blade tip equipped with mean-camberline strip (or "squealer" as it is often called). The heat transfer results are compared with the experimental results and discussed. The effectiveness of the mean-camberline strip in reducing the tip leakage and the tip heat transfer as compared to a radiused edge tip and sharp edge tip was studied. The calculations show that the sharp edge tip works best (among the cases considered) in reducing the tip leakage flow and the tip heat transfer. Ameri, A.A. Glenn Research Center NASA/CR-2001-210764, NAS 1.26:210764, E-12693, Rept-2001-GT-0156
Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped with a Mean-Camberline Strip
Monthly Catalog of United States Government Publications
Author:
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 808
Book Description
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 808
Book Description
Proceedings of the ASME Turbo Expo ...
Author:
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 684
Book Description
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 684
Book Description
Proceedings of the ASME Turbo Expo 2002
Author:
Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 590
Book Description
Annotation Volumes 3A and 3B are part of a five-volume set comprising the proceedings of the June 2002 conference held in the Netherlands. Approximately 125 articles address heat transfer, and manufacturing materials and metallurgy. A sampling of topics: the effect of freestream turbulence on film cooling adiabatic effectiveness; the influence of periodic unsteady inflow conditions on leading edge film cooling; and fluid dynamcis of a pre-swirl rotor-stator system. No subject index. Annotation c. Book News, Inc., Portland, OR (booknews.com).
Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 590
Book Description
Annotation Volumes 3A and 3B are part of a five-volume set comprising the proceedings of the June 2002 conference held in the Netherlands. Approximately 125 articles address heat transfer, and manufacturing materials and metallurgy. A sampling of topics: the effect of freestream turbulence on film cooling adiabatic effectiveness; the influence of periodic unsteady inflow conditions on leading edge film cooling; and fluid dynamcis of a pre-swirl rotor-stator system. No subject index. Annotation c. Book News, Inc., Portland, OR (booknews.com).
Journal of Heat Transfer
Determination of Gas-to-blade Convection Heat-transfer Coefficients on a Forced-convection, Water-cooled Single-stage Aluminum Turbine
Author: John C. Freche
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 22
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 22
Book Description
Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine. Part 1; Experimental Results
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721184934
Category :
Languages : en
Pages : 28
Book Description
A combined computational and experimental study has been performed to investigate the detailed distribution of convective heat transfer coefficients on the first stage blade tip surface for a geometry typical of large power generation turbines(>100MW). This paper is concerned with the design and execution of the experimental portion of the study. A stationary blade cascade experiment has been run consisting of three airfoils, the center airfoil having a variable tip gap clearance. The airfoil models the aerodynamic tip section of a high pressure turbine blade with inlet Mach number of 0.30, exit Mach number of 0.75, pressure ratio of 1.45, exit Reynolds number based on axial chord of 2.57 x 10(exp 6), and total turning of about 110 degrees. A hue detection based liquid crystal method is used to obtain the detailed heat transfer coefficient distribution on the blade tip surface for flat, smooth tip surfaces with both sharp and rounded edges. The cascade inlet turbulence intensity level took on values of either 5% or 9%. The cascade also models the casing recess in the shroud surface ahead of the blade. Experimental results are shown for the pressure distribution measurements on the airfoil near the tip gap, on the blade tip surface, and on the opposite shroud surface. Tip surface heat transfer coefficient distributions are shown for sharp-edge and rounded-edge tip geometries at each of the inlet turbulence intensity levels. Bunker, Ronald S. and Bailey, Jeremy C. and Ameri, Ali A. Glenn Research Center NASA/CR-1999-209152, NAS 1.26:209152, E-11660, ASME-99-GT-169
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721184934
Category :
Languages : en
Pages : 28
Book Description
A combined computational and experimental study has been performed to investigate the detailed distribution of convective heat transfer coefficients on the first stage blade tip surface for a geometry typical of large power generation turbines(>100MW). This paper is concerned with the design and execution of the experimental portion of the study. A stationary blade cascade experiment has been run consisting of three airfoils, the center airfoil having a variable tip gap clearance. The airfoil models the aerodynamic tip section of a high pressure turbine blade with inlet Mach number of 0.30, exit Mach number of 0.75, pressure ratio of 1.45, exit Reynolds number based on axial chord of 2.57 x 10(exp 6), and total turning of about 110 degrees. A hue detection based liquid crystal method is used to obtain the detailed heat transfer coefficient distribution on the blade tip surface for flat, smooth tip surfaces with both sharp and rounded edges. The cascade inlet turbulence intensity level took on values of either 5% or 9%. The cascade also models the casing recess in the shroud surface ahead of the blade. Experimental results are shown for the pressure distribution measurements on the airfoil near the tip gap, on the blade tip surface, and on the opposite shroud surface. Tip surface heat transfer coefficient distributions are shown for sharp-edge and rounded-edge tip geometries at each of the inlet turbulence intensity levels. Bunker, Ronald S. and Bailey, Jeremy C. and Ameri, Ali A. Glenn Research Center NASA/CR-1999-209152, NAS 1.26:209152, E-11660, ASME-99-GT-169
Analysis of Gas Turbine Rotor Blade Tip and Shroud Heat Transfer
Author: Ali A. Ameri
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 14
Book Description
Presented at the International Gas Turbine and Aeroengine Congress &Exhibition Birmingham, UK - June 10-13, 1996.
Publisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 14
Book Description
Presented at the International Gas Turbine and Aeroengine Congress &Exhibition Birmingham, UK - June 10-13, 1996.
Blade-to-coolant Heat-transfer Results and Operating Data from a Natural-convection Water-cooled Single-stage Turbine
Author: Anthony J. Diaguila
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 28
Book Description
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 28
Book Description