Read Books Online and Download eBooks, EPub, PDF, Mobi, Kindle, Text Full Free.
Computational Study Of Turbine Blade Trailing Edge Internal Cooling
Download Computational Study Of Turbine Blade Trailing Edge Internal Cooling full books in PDF, epub, and Kindle. Read online Computational Study Of Turbine Blade Trailing Edge Internal Cooling ebook anywhere anytime directly on your device. Fast Download speed and no annoying ads. We cannot guarantee that every ebooks is available!
Book Synopsis Computational Study of Turbine Blade Trailing Edge Internal Cooling by : Nadim Reza
Download or read book Computational Study of Turbine Blade Trailing Edge Internal Cooling written by Nadim Reza and published by . This book was released on 2017 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Modern gas turbine efficiency is improved by active cooling of the turbine blade trailing edge. The research seeks to improve turbine efficiency by increasing the cooling performance. For some time, pin fins have been used as the most common means of heat transfer enhancement. Among different types of pin fins, circular cross-section or cylindrical pin fins are the most popular and studied pin fins. A state-of-the-art design passes cooling air through a high-solidity pin array in a cavity in the trailing edge. A novel configuration with split cylindrical pin fins in which each pin has a centered slot in the mean flow direction are considered in this study. Computational simulations of flow with the proposed design reveal a significant improvement in cooling ability as compared to the currently used solid pin arrays.
Book Synopsis Computational Analysis of a Trailing Edge Cooling Passage in a Gas Turbine Blade by : Srikrishna Mahadevan
Download or read book Computational Analysis of a Trailing Edge Cooling Passage in a Gas Turbine Blade written by Srikrishna Mahadevan and published by . This book was released on 2009 with total page 188 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Parametric Study of Turbine Blade Internal Cooling and Film Cooling by : Akhilesh P. Rallabandi
Download or read book Parametric Study of Turbine Blade Internal Cooling and Film Cooling written by Akhilesh P. Rallabandi and published by . This book was released on 2010 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Gas turbine engines are extensively used in the aviation and power generation industries. They are used as topping cycles in combined cycle power plants, or as stand alone power generation units. Gains in thermodynamic efficiency can be realized by increasing the turbine inlet temperatures. Since modern turbine inlet temperatures exceed the melting point of the constituent superalloys, it is necessary to provide an aggressive cooling system. Relatively cool air, ducted from the compressor of the engine is used to remove heat from the hot turbine blade. This air flows through passages in the hollow blade (internal cooling), and is also ejected onto the surface of the blade to form an insulating film (film cooling). Modern land-based gas turbine engines use high Reynolds number internal flow to cool their internal passages. The first part of this study focuses on experiments pertaining to passages with Reynolds numbers of up to 400,000. Common turbulator designs (45degree parallel sharp-edged and round-edged) ribs are studied. Older correlations are found to require corrections in order to be valid in the high Reynolds number parameter space. The effect of rotation on heat transfer in a typical three-pass serpentine channel is studied using a computational model with near-wall refinement. Results from this computational study indicate that the hub experiences abnormally high heat transfer under rotation. An experimental study is conducted at Buoyancy numbers similar to an actual engine on a wedge shaped model trailing edge, roughened with pin-fins and equipped with slot ejection. Results show an asymmetery between the leading and trailing surfaces due to rotation - a difference which is subdued due to the provision of pin-fins. Film cooling effectiveness is measured by the PSP mass transfer analogy technique in two different configurations: a flat plate and a typical high pressure turbine blade. Parameters studied include a step immediately upstream of a row of holes; the Strouhal number (quantifying rotor-stator interaction) and coolant to mainstream density ratio. Results show a deterioration in film cooling effectiveness with on increasing the Strouhal number. Using a coolant with a higher density results in higher film cooling effectiveness.
Book Synopsis Combined Experimental/computational Study of Flow in Turbine Blade Cooling Passage: Part II - Numerical Simulations by : Diane M. McGrath
Download or read book Combined Experimental/computational Study of Flow in Turbine Blade Cooling Passage: Part II - Numerical Simulations written by Diane M. McGrath and published by . This book was released on 1995 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine and Aeroengine Congress and Exposition, Houston, Texas - June 5-8, 1995.
Book Synopsis A Combined Experimental, Computational Study of Flow in Turbine Blade Cooling Passage by : D. G. N. Tse
Download or read book A Combined Experimental, Computational Study of Flow in Turbine Blade Cooling Passage written by D. G. N. Tse and published by . This book was released on 1994 with total page 187 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Gas Turbine Heat Transfer and Cooling Technology, Second Edition by : Je-Chin Han
Download or read book Gas Turbine Heat Transfer and Cooling Technology, Second Edition written by Je-Chin Han and published by CRC Press. This book was released on 2012-11-27 with total page 892 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive reference for engineers and researchers, Gas Turbine Heat Transfer and Cooling Technology, Second Edition has been completely revised and updated to reflect advances in the field made during the past ten years. The second edition retains the format that made the first edition so popular and adds new information mainly based on selected published papers in the open literature. See What’s New in the Second Edition: State-of-the-art cooling technologies such as advanced turbine blade film cooling and internal cooling Modern experimental methods for gas turbine heat transfer and cooling research Advanced computational models for gas turbine heat transfer and cooling performance predictions Suggestions for future research in this critical technology The book discusses the need for turbine cooling, gas turbine heat-transfer problems, and cooling methodology and covers turbine rotor and stator heat-transfer issues, including endwall and blade tip regions under engine conditions, as well as under simulated engine conditions. It then examines turbine rotor and stator blade film cooling and discusses the unsteady high free-stream turbulence effect on simulated cascade airfoils. From here, the book explores impingement cooling, rib-turbulent cooling, pin-fin cooling, and compound and new cooling techniques. It also highlights the effect of rotation on rotor coolant passage heat transfer. Coverage of experimental methods includes heat-transfer and mass-transfer techniques, liquid crystal thermography, optical techniques, as well as flow and thermal measurement techniques. The book concludes with discussions of governing equations and turbulence models and their applications for predicting turbine blade heat transfer and film cooling, and turbine blade internal cooling.
Book Synopsis Combined Experimental/computational Study of Flow in Turbine Blade Cooling Passage: Part I - Experimental Study by : D. G. N. Tse
Download or read book Combined Experimental/computational Study of Flow in Turbine Blade Cooling Passage: Part I - Experimental Study written by D. G. N. Tse and published by . This book was released on 1995 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine and Aeroengine Congress and Exposition, Houston, Texas - June 5-8, 1995.
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781722891886 Total Pages :190 pages Book Rating :4.8/5 (918 download)
Book Synopsis A Combined Experimental/Computational Study of Flow in Turbine Blade Cooling Passage by : National Aeronautics and Space Administration (NASA)
Download or read book A Combined Experimental/Computational Study of Flow in Turbine Blade Cooling Passage written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-07-17 with total page 190 pages. Available in PDF, EPUB and Kindle. Book excerpt: Laser velocimetry was utilized to map the velocity field in a serpentine turbine blade cooling passage at Reynolds and Rotation numbers of up to 25.000 and 0.48. These results were used to assess the combined influence of passage curvature and Coriolis force on the secondary velocity field generated. A Navier-Stokes code (NASTAR) was validated against incompressible test data and then used to simulate the effect of buoyancy. The measurements show a net convection from the low pressure surface to high pressure surface. The interaction of the secondary flows induced by the turns and rotation produces swirl at the turns, which persisted beyond 2 hydraulic diameters downstream of the turns. The incompressible flow field predictions agree well with the measured velocities. With radially outward flow, the buoyancy force causes a further increase in velocity on the high pressure surface and a reduction on the low pressure surface. The results were analyzed in relation to the heat transfer measurements of Wagner et al. (1991). Predicted heat transfer is enhanced on the high pressure surfaces and in turns. The incompressible flow simulation underpredicts heat transfer in these locations. Improvements observed in compressible flow simulation indicate that the buoyancy force may be important. Tse, D. G. N. and Kreskovsky, J. P. and Shamroth, S. J. and Mcgrath, D. B. Unspecified Center BUOYANCY; CHANNEL FLOW; CONVECTIVE HEAT TRANSFER; COOLING; FLOW DISTRIBUTION; FLOW VELOCITY; TURBINE BLADES; COMPRESSIBLE FLOW; CORIOLIS EFFECT; INCOMPRESSIBLE FLOW; LASER DOPPLER VELOCIMETERS; NAVIER-STOKES EQUATION; REYNOLDS NUMBER; SECONDARY FLOW; VELOCITY DISTRIBUTION...
Book Synopsis A Combined Experimental/computational Study of Flow in Turbine Blade Cooling Passage by :
Download or read book A Combined Experimental/computational Study of Flow in Turbine Blade Cooling Passage written by and published by . This book was released on 1994 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Combined Experiment/computational Study of Flow in Turbine Blade Cooling Passage by :
Download or read book A Combined Experiment/computational Study of Flow in Turbine Blade Cooling Passage written by and published by . This book was released on 1994 with total page 194 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Measurements and Computational Analysis of Heat Transfer and Flow in a Simulated Turbine Blade Internal Cooling Passage by : Louis M. Russell
Download or read book Measurements and Computational Analysis of Heat Transfer and Flow in a Simulated Turbine Blade Internal Cooling Passage written by Louis M. Russell and published by . This book was released on 1993 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical Simulation of a Film Cooled Turbine Blade Leading Edge Including Heat Transfer Effects by : Laurene D. Dobrowolski
Download or read book Numerical Simulation of a Film Cooled Turbine Blade Leading Edge Including Heat Transfer Effects written by Laurene D. Dobrowolski and published by . This book was released on 2009 with total page 436 pages. Available in PDF, EPUB and Kindle. Book excerpt: Computations and experiments were run to study heat transfer and overall effectiveness for a simulated turbine blade leading edge. Computational predictions were run for a film cooled leading edge model using a conjugate numerical method to predict the normalized "metal" temperatures for the model. This computational study was done in conjunction with a parallel effort to experimentally determine normalized metal temperatures, i.e. overall effectiveness, using a specially designed high conductivity model. Predictions of overall effectiveness were higher than experimentally measured values in the stagnation region, but lower along the downstream section of the leading edge. Reasons for the differences between computational predictions and experimental measurements were examined. Also of interest was the validity of Taw as the driving temperature for heat transfer into the blade, and this was examined via computations. Overall, this assumption gave reasonable results except near the stagnation line. Experiments were also conducted on a leading edge with no film cooling to gain a better understanding of the additional cooling provided by film cooling. Heat flux was also measured and external and internal heat transfer coefficients were determined. The results showed roughly constant overall effectiveness on the external surface.
Book Synopsis Multiobjective Design Optimization of Gas Turbine Blade with Emphasis on Internal Cooling by : Narasimha R. Nagaiah
Download or read book Multiobjective Design Optimization of Gas Turbine Blade with Emphasis on Internal Cooling written by Narasimha R. Nagaiah and published by . This book was released on 2012 with total page 165 pages. Available in PDF, EPUB and Kindle. Book excerpt: This test application is quite relevant as gas turbine engines serve a critical role in the design of the next-generation power generation facilities around the world. Furthermore, turbine blades require better cooling techniques to increase their cooling effectiveness to cope with the increase in engine operating temperatures extending the useful life of the blades. The performance of the proposed framework is evaluated via a computational study, where a set of common, real-world design objectives and a set of design variables that directly influence the set of objectives are considered. Specifically, three objectives are considered in this study: (1) cooling channel heat transfer coefficient, which measures the rate of heat transfer and the goal is to maximize this value; (2) cooling channel air pressure drop, where the goal is to minimize this value; and (3) cooling channel geometry, specifically the cooling channel cavity area, where the goal is to maximize this value. These objectives, which are conflicting, directly influence the cooling effectiveness of a gas turbine blade and the material usage in its design. The computational results show the proposed optimization framework is able to generate, evaluate and identify thousands of competitive tradeoff designs in a fraction of the time that it would take designers using the traditional simulation tools and experimental methods commonly used for mechanical component design generation. This is a significant step beyond the current research and applications of design optimization to gas turbine blades, specifically, and to mechanical components, in general.
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 Computational Simulation and Analysis of Film Cooling for the Leading-edge Model of a Turbine Blade by :
Download or read book Computational Simulation and Analysis of Film Cooling for the Leading-edge Model of a Turbine Blade written by and published by . This book was released on 2007 with total page 147 pages. Available in PDF, EPUB and Kindle. Book excerpt: The application of interest is the cooling of turbine blades in large gas combustion engines where hot gases from the combustor cause thermal deterioration of the metal turbine blades. A thin-film of coolant flow buffers the hottest parts of the blade surface. Heat transfer on a bluff body and, subsequently, a single-hole cooling problem is solved numerically in two-dimensions. The flow is assumed to be incompressible, and the laminar, steady Navier-Stokes equations are used to obtain the flow solution. Results for the bluff-body heat transfer agree very well with experimental data up to the separation point, and are within 20% of the data thereafter. The film-cooling simulation yielded higher cooling effectiveness due in large part to the use of the two-dimensional model, which treats the hole as a slot with higher coolant mass. Results from the simulations indicate that the Cobalt flow solver is capable of solving complex heat transfer problems.
Book Synopsis Computational Study of Turbine Blade Film Cooling Performance Using Anisotropic Turbulence Models by : Chandran Sundaraj
Download or read book Computational Study of Turbine Blade Film Cooling Performance Using Anisotropic Turbulence Models written by Chandran Sundaraj and published by . This book was released on 2006 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental and Computational Investigation of Flow in Gas Turbine Blade Cooling Passages by : Harald Roclawski
Download or read book Experimental and Computational Investigation of Flow in Gas Turbine Blade Cooling Passages written by Harald Roclawski and published by . This book was released on 2001 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
