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Numerical Analysis Of Blade Tip Leakage Flow And Shroud Heat Transfer In Gas Turbine Engines
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Book Synopsis Numerical Analysis of Blade Tip Leakage Flow and Shroud Heat Transfer in Gas Turbine Engines by : Md. Hamidur Rahman
Download or read book Numerical Analysis of Blade Tip Leakage Flow and Shroud Heat Transfer in Gas Turbine Engines written by Md. Hamidur Rahman and published by . This book was released on 2008 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: One of the most critical components of gas turbine engines, rotor blade tip and casing, is exposed to high thermal load. It is a significant challenge to the designer to protect the turbine material from this severe situation. Leakage flow over the blade tip is also one of the important issues to improve the turbine performance. To understand the detailed phenomena and natures of the heat transfer on the turbine blade tip and casing in association with the tip leakage flow under actual turbine operating conditions, both steady and unsteady simulations have been conducted. A single stage gas turbine engine was modeled and simulated using commercial CFD solver ANSYS CFX R.11. The modeled turbine stage has 30 vanes and 60 blades with a pressure ratio of 3.2 and a rotational speed of 9500 rpm. The predicted isentropic Mach number and adiabatic wall temperature on the casing showed good agreement with available experimental data under the close operating condition. Through the steady simulations, the typical tip leakage flow structures and heat transfer rate distributions were analyzed. The tip leakage flow separates and recirculates just around the pressure side edge of the blade tip. This coverage of the recirculating flow results in low heat transfer rates on the tip surface. The leakage flow then reattaches on the tip surface beyond the flow separation zone. This flow reattachment has shown enhanced heat transfer rates on the tip. The leakage flow interaction with the reverse cross flow, induced by relative casing motion, is found to have significant effect on the casing heat transfer rate distribution. Critical region of high heat transfer rate on the casing exists near the blade tip leading edge and along the pressure side edge. Whereas near the suction side the heat transfer rates are relatively low due to the coverage of the reverse cross flow. The effects of the tip clearance heights and rotor rotating speeds were also investigated. The region of recirculating flow increases with the increase of clearance heights. The flow incidence changes and the casing relative motion is enhanced with higher rotation speeds. As a result, the high heat transfer rate regions have been changed with these two parameters. Unsteady simulations have been performed to investigate time dependent behaviors of the leakage flow structures and heat transfer on the rotor casing and blade tip. The effects of different time steps, number of sub iteration and number of rotor vane passing were firstly examined. The periodicity of the tip leakage flow and heat transfer rate distribution is observed for each vane passing. The relative change in the position of the vane and the vane trailing edge shock alters the inlet flow conditions of the rotor part. It results in the periodic variations of the leakage flow structures and heat transfer rate distributions. The higher heat transfer rates were observed at the region where the trailing edge shock reached. The maximum amplitude of the pressure fluctuation in the tip region is about 20% of the averaged rotor inlet pressure. The maximum amplitude of the heat transfer rate fluctuation on the blade tip, caused by the unsteady leakage flow variations, reaches up to about 25% of the mean heat transfer rate. The effects of tip clearance heights and rotor speeds have also been analyzed and compared one with respect to others. Same typical patterns of leakage flow structures and heat transfer rate distribution can be obtained in both steady and unsteady simulations. However, steady simulation underpredicted the highest heat transfer rate. Because it couldn't capture the critical local high heat transfer phenomena caused by the unsteady stator-rotor interactions.
Book Synopsis Numerical Investigation of the Unsteady Aerodynamics of Blade Tip Leakage Flow Inside Gas Turbine Engines by : Patricia Phutthavong
Download or read book Numerical Investigation of the Unsteady Aerodynamics of Blade Tip Leakage Flow Inside Gas Turbine Engines written by Patricia Phutthavong and published by . This book was released on 2006 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Numerical Analysis of Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models by : Ali A. Ameri
Download or read book A Numerical Analysis of Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models written by Ali A. Ameri and published by . This book was released on 1999 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of Gas Turbine Rotor Blade Tip and Shroud Heat Transfer by : Ali A. Ameri
Download or read book Analysis of Gas Turbine Rotor Blade Tip and Shroud Heat Transfer written by Ali A. Ameri and published by . This book was released on 1996 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine and Aeroengine Congress &Exhibition Birmingham, UK - June 10-13, 1996.
Book Synopsis Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped with a Mean-Camberline Strip by :
Download or read book Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped with a Mean-Camberline Strip written by and published by . This book was released on 2001 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine by :
Download or read book Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine written by and published by . This book was released on 1999 with total page 18 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721189052 Total Pages :26 pages Book Rating :4.1/5 (89 download)
Book Synopsis A Numerical Analysis of Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models by : National Aeronautics and Space Administration (NASA)
Download or read book A Numerical Analysis of Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: A computational study has been performed to predict the distribution of convective heat transfer coefficient on a simulated blade tip with cooling holes. The purpose of the examination was to assess the ability of a three-dimensional Reynolds-averaged Navier-Stokes solver to predict the rate of tip heat transfer and the distribution of cooling effectiveness. To this end, the simulation of tip clearance flow with blowing of Kim and Metzger was used. The agreement of the computed effectiveness with the data was quite good. The agreement with the heat transfer coefficient was not as good but improved away from the cooling holes. Numerical flow visualization showed that the uniformity of wetting of the surface by the film cooling jet is helped by the reverse flow due to edge separation of the main flow. Ameri, A. A. and Rigby, D. L. Glenn Research Center NASA/CR-1999-209165, NAS 1.26:209165, E-11756
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721262274 Total Pages :26 pages Book Rating :4.2/5 (622 download)
Book Synopsis Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped with a Mean-Camberline Strip by : National Aeronautics and Space Administration (NASA)
Download or read book Heat Transfer and Flow on the Blade Tip of a Gas Turbine Equipped with a Mean-Camberline Strip written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-16 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721184934 Total Pages :28 pages Book Rating :4.1/5 (849 download)
Book Synopsis Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine. Part 1; Experimental Results by : National Aeronautics and Space Administration (NASA)
Download or read book Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine. Part 1; Experimental Results written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-15 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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
Book Synopsis Local Measurement and Numerical Modeling of Mass/heat Transfer from a Turbine Blade in a Linear Cascade with Tip Clearance by : Peitong Jin
Download or read book Local Measurement and Numerical Modeling of Mass/heat Transfer from a Turbine Blade in a Linear Cascade with Tip Clearance written by Peitong Jin and published by . This book was released on 2000 with total page 600 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Gas Turbine Tip Region Leakage Flow and Heat Transfer by :
Download or read book Gas Turbine Tip Region Leakage Flow and Heat Transfer written by and published by . This book was released on 2005 with total page 27 pages. Available in PDF, EPUB and Kindle. Book excerpt: New, detailed flow field measurements and high resolution Nusselt number (Nu) distributions are presented for a very large low-speed cascade representative of a high-pressure turbine rotor blade with turning of 110 degrees and blade chord of 1.0 m. Data was obtained for tip leakage and passage secondary flow at a Reynolds number of 4.0 x 1 %%, based on exit velocity and blade axial chord. Tip clearance levels ranged from 0% to 1.68% of blade span (0% to 3% of blade chord). The relative motion between the casing and the blade tip was simulated using a motor-driven moving belt system. Particle Image Velocimetry (PIV) was used to obtain flow field maps of several planes parallel and normal to the tip surface within the tip gap, and adjacent passage flow. Secondary flow was measured at planes normal to the blade exit angle at locations upstream and downstream of the trailing edge. An infrared camera made detailed temperature measurements on a constant heat flux tip surface. The interaction between the tip leakage vortex and passage vortex is clearly defined, revealing the dominant effect of the tip leakage flow on the tip endwall secondary flow. A reduction in the magnitude of the under-tip flow near the endwall due to the moving wall is observed and the effect on the tip leakage vortex examined. The moving belt endwall significantly shifts the region of high Nu distribution and reduces the overall averaged Nu on the tip surface by up to 13.3%. The addition of a suction side squealer tip significantly reduced local tip heat transfer and resulted in a 32% reduction in averaged Nu.
Book Synopsis Turbine Tip and Shroud Heat Transfer by : Darryl E. Metzger
Download or read book Turbine Tip and Shroud Heat Transfer written by Darryl E. Metzger and published by . This book was released on 1990 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Unshrouded blades of axial turbine stages move in close proximity to the stationary outer seal, or shroud, of the turbine housing. The pressure difference between the concave and convex sides of the blade drives a leakage flow through the gap between the moving blade tip and adjacent wall. This clearance leakage flow and accompanying heat transfer are of interest because of long obvious effects on aerodynamic performance and structural durability, but understanding of its nature and influences has been elusive. Previous studies indicate that the leakage through the gap is mainly a pressure-driven flow whose magnitude is related strongly to the airfoil pressure loading distribution and only weakly, if at all, to the relative motion between blade tip and shroud. A simple flow and heat transfer model incorporating these features can be used to estimate both tip and shroud heat transfer provided that reasonable estimates of the clearance gap size and clearance leakage flow can be made. The present work uses a numerical computation of the leakage flow to link the model to a specific turbine geometry and operating point for which a unique set of measured local tip and shroud heat fluxes is available. The resulting comparisons between the model estimates and measured heat transfer are good. The model should thus prove useful in the understanding and interpretation of future measurements, and should additionally prove useful for providing early design estimates of the levels of tip and shroud heat transfer that need to be compensated for by active turbine cooling.
Book Synopsis Prediction of Unshsrouded Rotor Blade Tip Heat Transfer by :
Download or read book Prediction of Unshsrouded Rotor Blade Tip Heat Transfer written by and published by . This book was released on 1994 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Gas Turbine Blade Cooling by : Chaitanya D Ghodke
Download or read book Gas Turbine Blade Cooling written by Chaitanya D Ghodke and published by SAE International. This book was released on 2018-12-10 with total page 238 pages. Available in PDF, EPUB and Kindle. Book excerpt: Gas turbines play an extremely important role in fulfilling a variety of power needs and are mainly used for power generation and propulsion applications. The performance and efficiency of gas turbine engines are to a large extent dependent on turbine rotor inlet temperatures: typically, the hotter the better. In gas turbines, the combustion temperature and the fuel efficiency are limited by the heat transfer properties of the turbine blades. However, in pushing the limits of hot gas temperatures while preventing the melting of blade components in high-pressure turbines, the use of effective cooling technologies is critical. Increasing the turbine inlet temperature also increases heat transferred to the turbine blade, and it is possible that the operating temperature could reach far above permissible metal temperature. In such cases, insufficient cooling of turbine blades results in excessive thermal stress on the blades causing premature blade failure. This may bring hazards to the engine's safe operation. Gas Turbine Blade Cooling, edited by Dr. Chaitanya D. Ghodke, offers 10 handpicked SAE International's technical papers, which identify key aspects of turbine blade cooling and help readers understand how this process can improve the performance of turbine hardware.
Book Synopsis Effect of Chord Size on Weight and Cooling Characteristics of Air-cooled Turbine Blades by : Jack B. Esgar
Download or read book Effect of Chord Size on Weight and Cooling Characteristics of Air-cooled Turbine Blades written by Jack B. Esgar and published by . This book was released on 1957 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analysis has been made to determine the effect of chord size on the weight and cooling characteristics of shell-supported, air-cooled gas-turbine blades. In uncooled turbines with solid blades, the general practice has been to design turbines with high aspect ratio (small blade chord) to achieve substantial turbine weight reduction. With air-cooled blades, this study shows that turbine blade weight is affected to a much smaller degree by the size of the blade chord.
Book Synopsis Gas Turbine Tip Leakage Flow and Heat Transfer by : Md Hamidur Rahman
Download or read book Gas Turbine Tip Leakage Flow and Heat Transfer written by Md Hamidur Rahman and published by . This book was released on 2011-06 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine by : Ali A. Ameri
Download or read book Heat Transfer and Flow on the First Stage Blade Tip of a Power Generation Gas Turbine written by Ali A. Ameri and published by . This book was released on 1999 with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt:
