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Experimental And Computational Investigation Of Flow In Gas Turbine Blade Cooling Passages
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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:
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 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.
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 Computational and Experimental Investigation of Vortex Cooling of a Gas Turbine Blade Using 3-D Stereo-Particle Image Velocimetry and Liquid Crystals by : Daisy Galeana
Download or read book Computational and Experimental Investigation of Vortex Cooling of a Gas Turbine Blade Using 3-D Stereo-Particle Image Velocimetry and Liquid Crystals written by Daisy Galeana and published by . This book was released on 2022 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The limiting factor for most gas turbines has been the turbine inlet temperature. Furthermore, higher pressure ratios and turbine inlet temperatures improve the efficiencies on the gas turbine. A big focus has been on new schemes of internal cooling designs of turbine blades, using pressurized air from the engine compressor, and break-through in blade metallurgy, in order to achieve higher turbine inlet temperatures. Significant research has been ongoing for decades to design an internal cooling system for the first stage of the turbine blade consequently higher turbine inlet temperatures can be achieved. The challenging engineering intricacies related to improving the efficiency of a gas turbine engine come with the need to maximize the efficiency of the internal cooling of the turbine blade to withstand the high turbine inlet temperature. Understanding the fluid mechanics and heat transfer of internal blade cooling is therefore of paramount importance. This dissertation presents the impact of swirl flow cooling on the heat transfer of a gas turbine blade cooling passage to understand the mechanics of internal blade cooling. The focus is the continuous cooling flow that must be maintained via nonstop injection of tangential flow, whereby swirl flow is generated. The experimental investigation is presented first with three-dimensional (3-D) Stereo-Particle Image Velocimetry (Stereo-PIV) and second Thermochromic Liquid Crystal (TLC) of a swirl flow that models a gas turbine blade internal cooling configuration. The study is intended to provide an evaluation of the developments of swirl flow cooling methodology utilizing 3-D Stereo-PIV and liquid crystals. The objective of the experimental models is to determine the critical swirl number that has the potential to deliver the maximum axial velocity results with the highest heat transfer at three different Reynolds numbers, 7,000, 14,000, and 21,000. The swirl flow cooling methodology comprises of cooling air channeling through the blade's internal passages lowering the metal temperature, therefore the experimental cylindrical chamber is made of acrylic allowing detailed measurements and includes seven discrete tangential air inlets designed to create the swirl flow. Additionally, a 3D domain fluent setup employing a steady-state pressure-based solver with a standard k-epsilon turbulence model was applied. The energy equations were activated to handle the temperature effect; the gravitational acceleration is accounted for. Important variations of the swirl number are present near the air inlets and decrease with downstream distance as predicted since the second half of the chamber has no more inlets. The axial velocity reaches the maximum downstream in the second half of the chamber. The circumferential velocity decreases downstream distance and reaches the highest towards the center of the chamber. As part of the results relatively low heat transfer rates were observed near the upstream end of the cylindrical chamber, resulting from a low momentum swirl flow as well as crossflow effects. The TLC heat transfer results exemplify how the Nusselt Number (Nu) measured favorably at the midstream of the chamber and values decline downstream. Furthermore, experimental results when compared to the Computational Fluid Dynamics analysis are compatible with each other.
Book Synopsis Computational and Experimental Investigation of Internal Cooling Passages for Gas Turbine Applications by : Aditya Narayan Kulkarni
Download or read book Computational and Experimental Investigation of Internal Cooling Passages for Gas Turbine Applications written by Aditya Narayan Kulkarni and published by . This book was released on 2020 with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: In order to keep turbine blade surface temperature below melting point in gas turbine engines, internal passages in blades must be used to route cooler air through the blade. Design optimization of cooling passages necessitates an understanding of heat transfer patterns to minimize cooling mass flow. This project compares two approximations used to determine the heat transfer rate inside cooling channels in both computational and experimental investigations. The two approximations used in this project are constant surface temperature and transient heating. In an operating engine, the accuracy of both these conditions are not guaranteed. During steady state operation, the blade can cycle through many different flow paths which will impart different temperatures across the surface, and at no time will a blade be under completely uniform temperature except for the starting cycle. However, to make measurements of heat transfer easier, the two assumptions mentioned beforehand are utilized extensively. The constant surface temperature method uses a heater attached to the back of a thin copper plate to hold the surface temperature at a constant value in air flow. In the transient full-field method, thermochromic liquid crystals, which change colors with temperature, are applied to flat plate and turbulated geometries to capture the change in wall temperature during heating and cooling processes. Heat transfer rates are then derived from the transient temperature data using a semi-infinite solid model. The constant temperature approach is better established than the transient method and produces significantly higher Nusselt numbers, but the transient method provides better spatial resolution. A numerical conjugate heat transfer model is used to further investigate the discrepancy between the methods. The experimental geometry is replicated for both methods to gain an understanding of the fluid dynamics in each setup and how they differ.
Book Synopsis Fluid Mechanics and Heat Transfer Research Related to High Temperature Gas Turbines by :
Download or read book Fluid Mechanics and Heat Transfer Research Related to High Temperature Gas Turbines written by and published by . This book was released on 1995 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of the research was to enhance the understanding of airfoil passage transport processes and film cooling by conducting a coordinated experimental and computational study of flow behavior and airfoil and end-wall surface heat transfer as influenced by turbulence and more coherent structures in the passage flow, streamline curvature, and other effects. Computation is used to evaluate and develop film cooling schemes, as well as to extend by analysis the experience base beyond the experimental cases investigated. The outcome of the research will be improved physical understanding and computational models of these processes, both of which are of direct utility to the engine designers in the aircraft industry. The research project finds a number of innovative features. They include: (a) detailed local heat (mass) transfer measurements on turbine blade surfaces, (b) investigation of the mass transfer and turbulent characteristics in curved channel flows, (c) determination of local film cooling effectiveness in endwall film cooling and total-coverage discrete hole wall cooling, (d) evaluation of a fence for endwall flow control, and (e) accurate numerical modeling in film cooling.
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 Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1995 with total page 704 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of Air-cooled Turbine Blades in Turbojet Engine by : Herman H. Ellerbrock (Jr.)
Download or read book Experimental Investigation of Air-cooled Turbine Blades in Turbojet Engine written by Herman H. Ellerbrock (Jr.) and published by . This book was released on 1951 with total page 78 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of Air-cooled Turbine Blades in Turbojet Engine by : Vernon L. Arne
Download or read book Experimental Investigation of Air-cooled Turbine Blades in Turbojet Engine written by Vernon L. Arne and published by . This book was released on 1951 with total page 56 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Experimental Investigation of Air-cooled Turbine Blades in Turbojet Engine by : Gordon T. Smith
Download or read book Experimental Investigation of Air-cooled Turbine Blades in Turbojet Engine written by Gordon T. Smith and published by . This book was released on 1951 with total page 22 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 Analytical and Experimental Investigation of a Forced-convection Air-cooled Internal Strut-supported Turbine Blade by : Eugene F. Schum
Download or read book Analytical and Experimental Investigation of a Forced-convection Air-cooled Internal Strut-supported Turbine Blade written by Eugene F. Schum and published by . This book was released on 1954 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Numerical and Experimental Investigation of the Turbulent Flow in a Ribbed Serpentine Passage by : Gianluca Iaccarino
Download or read book Numerical and Experimental Investigation of the Turbulent Flow in a Ribbed Serpentine Passage written by Gianluca Iaccarino and published by . This book was released on 2003 with total page 9 pages. Available in PDF, EPUB and Kindle. Book excerpt: Modern gas turbine engines operate at high combustor outlet temperatures to achieve higher thermal efficiency and thrust. Turbine blades are exposed to these high-temperature gases and undergo severe thermal stress and fatigue. The design of highly efficient cooling systems for turbine blades has an enormous potential impact on engine development. Cooling devices are based on a secondary flow system built into each blade, as illustrated in Fig. 1. The secondary flow passages are extremely complicated consisting of one or multiple legs with turbulators (rib-roughened serpentines), holes connecting the secondary path to the external surface of the blade (film cooling), tube bundles, slots, etc. The geometrical complexity of these passages, however, is extremely challenging for the use of advanced simulation tools based on state-of-the-art three-dimensional CFD solvers. The generation of a computational grid (even using unstructured mesh technology) requires a considerable amount of time. As a result, the analysis of the cooling performance of the system is largely based on isolated sub-component simulations, simplified one-dimensional models and experimental correlations.
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.
