Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 18
Book Description
Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine
Author: 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
Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine
Author: Ali A. AmeriPublisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 14
Book Description
Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine. Part 2; Simulation Results
Author: National Aeronautics and Space Administration (NASA)Publisher: Createspace Independent Publishing Platform
ISBN: 9781721183678
Category :
Languages : en
Pages : 26
Book Description
A combined experimental and computational 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 (>1OOMW). This paper is concerned with the numerical prediction of the tip surface heat transfer. Good comparison with the experimental measured distribution was achieved through accurate modeling of the most important features of the blade passage and heating arrangement as well as the details of experimental rig likely to affect the tip heat transfer. A sharp edge and a radiused edge tip were considered. The results using the radiused edge tip agreed better with the experimental data. This improved agreement was attributed to the absence of edge separation on the tip of the radiused edge blade. Ameri, A. A. and Bunker, R. S. Glenn Research Center NASA/CR-1999-209151/PT2, NAS 1.26:209151/PT2, E-11656/PT2, ASME 99-GT-283/PT2
Heat transfer and flow on the first stage blade tip of a power generation gas turbine, Part 1: Experimental results, ASME 99-GT-169
Author: Ronald S. BunkerPublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-10, 1999.
Heat transfer and flow on the first stage blade tip of a power generation gas turbine, Part 2: Simulation results, ASME 99-GT-283
Author: A. A. AmeriPublisher:
ISBN:
Category :
Languages : en
Pages : 0
Book Description
Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, June 7-June 10, 1999.
Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine
Author: Ronald S. BunkerHeat 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
Gas Turbine Heat Transfer and Cooling Technology
Author: Je-Chin HanPublisher: Taylor & Francis
ISBN: 1466564903
Category : Science
Languages : en
Pages : 865
Book Description
A comprehensive reference for engineers and researchers, this second edition focuses on gas turbine heat transfer issues and their associated cooling technologies for aircraft and land-based gas turbines. It provides information on state-of-the-art cooling technologies such as advanced turbine blade film cooling and internal cooling schemes. The book also offers updated experimental methods for gas turbine heat transfer and cooling research, as well as advanced computational models for gas turbine heat transfer and cooling performance predictions. The authors provide suggestions for future research within this technology and includes 800 illustrations to help clarify concepts and instruction.
Author: