Download or read book Measurement of Aerodynamic Losses and Internal Heat Transfer for a Gas Turbine Vane with a Gill Slot Cooled Trailing Edge written by Jake Duane Johnson and published by . This book was released on 2006 with total page 334 pages. Available in PDF, EPUB and Kindle. Book excerpt:

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.

Download or read book Comparison of Heat Transfer and Aerodynamics for Gill Slot and Letterbox Trailing Edge Turbine Vane Configurations with Variable Coolant Discharge written by Nathan James Fiala and published by . This book was released on 2007 with total page 462 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Infrared Low Temperature Turbine Vane Rough Surface Heat Transfer Measurements written by and published by . This book was released on 2000 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Losses and Heat Transfer for a Covered Trailing Edge Turbine Vane with a High Solidity Low Pressure Drop Predestal Pin Fin Array and Variable Coolant Ejection written by Indrajit Jaswal and published by . This book was released on 2008 with total page 346 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Comparison of Cooling Effectiveness of Turbine Vanes with and Without Film Cooling written by and published by . This book was released on 1974 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Effect of Diameter of Closed end Coolant Passages on Natural convection Water Cooling of Gas turbine Blades written by Arthur N. Curren and published by . This book was released on 1956 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental investigation on a water-cooled gas turbine with blade coolant-passage diameters ranging from 0.100 to 0.500 inch, corresponding to length-to-diameter ratios of 25.5 to 5.1, in various quadrants of the turbine. The investigation was conducted to determine (1) whether coolant-passage length-to-ratio has a significant effect on natural-convection heat-transfer correlation, and (2) whether turbine blade temperatures could be calculated with reasonable accuracy from a theoretical natural-convection heat-transfer correlation.

Download or read book Secondary Flow and Heat Transfer Control in Gas Turbine Inlet Nozzle Guide Vanes written by Steven Wayne Burd and published by . This book was released on 1998 with total page 604 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Measurements of Heat Transfer Flow and Pressures in a Simulated Turbine Blade Internal Cooling Passage written by Louis M. Russell and published by . This book was released on 1997 with total page 30 pages. Available in PDF, EPUB and Kindle. Book excerpt: An experimental study was made to obtain quantitative information on heat transfer, flow, and pressure distribution in a branched duct test section that had several significant features of an internal cooling passage of a turbine blade. The objective of this study was to generate a set of experimental data that could be used for validation of computer codes that would be used to model internal cooling. Surface heat transfer coefficients and entrance flow conditions were measured at nominal entrance Reynolds numbers of 45 000, 335 000, and 726 000. Heat transfer data were obtained by using a steady-state technique in which an Inconel heater sheet is attached to the surface and coated with liquid crystals. Visual and quantitative flow-field data from particle image velocimetry measurements for a plane at midchannel height for a Reynolds number of 45 000 were also obtained. The flow was seeded with polystyrene particles and illuminated by a laser light sheet. Pressure distribution measurements were made both on the surface with discrete holes and in the flow field with a total pressure probe. The flow-field measurements yielded flow-field velocities at selected locations. A relatively new method, pressure sensitive paint, was also used to measure surface pressure distribution. The pressure paint data obtained at Reynolds numbers of 335 000 and 726 000 compared well with the more standard method of measuring pressures by using discrete holes.

Download or read book Radiation Heat Transfer Characteristics of Turbine Vane Airfoils in a Water cooled Cascade written by and published by . This book was released on 1971 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Turbulent Coolant Dispersion in the Wake of a Turbine Vane Trailing Edge written by Sayuri D. Yapa and published by . This book was released on 2015 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: Magnetic resonance-based velocity (MRV) and concentration (MRC) measurements were performed to measure the time-averaged, three-dimensional, three-component velocity and scalar concentration fields in a double passage vane cascade representative of a high pressure turbine vane from a gas turbine engine. The understanding and prediction of the highly three-dimensional flow and heat transfer in modern gas turbine engines is a problem that has not been solved over many years of turbomachinery research. Turbine vanes and blades are both internally and externally cooled to withstand the hot gas environment. The external film cooling is generally fed by discrete holes on the vane surface, except for at the trailing edge, which is cooled by slots that are cut into the pressure side of the vane. Hot streaks from the combustor and cool streaks from the vane film cooling impose strong inlet temperature variations on the turbine blades, which can lead to local hot or cold spots, high thermal stresses, and fatigue failures. Furthermore, the complex three dimensional flows around the vane may act to concentrate cool or hot fluid exiting the vane row. Experiments were performed to show the validity of the application of the scalar transport analogy to the study of turbulent thermal energy transport using turbulent passive scalar transport studies. These experiments were conducted in a three-dimensional mixing layer in the wake of a blunt splitter plate built into two identical test sections. One test section was magnetic resonance-compatible and used water as the working fluid and the other was adapted for high subsonic Mach number air flows and allowed physical access for a thermocouple probe to take temperature profiles. In the water-based MRV/MRC experiments, the mainstream flow was water and the secondary flow was a copper sulfate solution. In the air experiments, the main flow was room temperature air and the secondary flow was heated. The energy separation effect due to coherent vortex structures in the compressible flow experiments affected the measured temperature profile because of the small difference in stagnation temperature between the two flows. This effect is expected to be negligible in the high temperature difference flows found in real engine conditions. This effect is easily corrected in the temperature profiles extracted from this experiment. The agreement between the corrected temperature and the concentration data was found to be excellent, validating the application of MRC for quantitative measurement of thermal transport in turbomachinery components via the scalar transport analogy. The MRV/MRC experimental technique was applied to the study of turbulent dispersion of coolant injected through trailing edge cooling slots, with the focus on dispersion in the vane wake. A new high concentration MRC technique was developed to provide accurate measurements in the far wake of the turbine vane. Three component velocity data showed the development of the passage vortex, a key element of the vane secondary flows. This mean flow structure is the dominant mechanism for turbulent mixing near the cascade endwalls. However, strong variations in coolant concentration remained in the wake downstream of the center span region. Asymmetric dispersion in this region indicated that longitudinal vortices shed from the coolant injection structures played a dominant role in the wake spreading. A separate experiment was performed to evaluate the behavior of the dispersion of combustor hot streaks in the turbine vane cascade. The velocity and concentration distributions were evaluated using the MRV/MRC experimental technique. Streamtubes and concentration isosurfaces reveal that the streaks spread slowly as they pass through the cascade. This suggests that turbulence suppression by strong acceleration plays a significant role in maintaining the streaks. It is important to note that coherent hot streaks still exist at the exit of the test section in the far wake of the vane. The concluding message from these experiments is that the temperature distribution of the gases impacting the blades downstream of the turbine vanes remains significantly non-uniform and that accurate prediction of the temperature distribution downstream of the vanes is critical for advanced turbine cooling design.

Download or read book A Three Dimensional Coupled Internal External Simulation of a Film Cooled Turbine Vane written by James D. Heidmann and published by . This book was released on 1999 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Coolant Pressure and Flow Distribution Through an Air cooled Vane for a High Temperature Gas Turbine written by and published by . This book was released on 1970 with total page 52 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Turbine Vane Coolant Flow Variations and Calculated Effects on Metal Temperatures written by Frederick C. Yeh and published by . This book was released on 1975 with total page 22 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book Aerodynamic Loss Reduction in a Vane Cascade with Leading Edge Fillet and Upstream Endwall Film Cooling written by Keenesh Arnachellan and published by . This book was released on 2017 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt: Secondary flow structures account for nearly 50% of aerodynamic losses experienced in the turbine blade passages. The adverse effects of these vortex structures transport the hot mainstream fluid towards the endwall blade surfaces, which enhances thermal stresses and leads to blade failure. The effects of leading-edge fillets and film-cooling with flush slots located upstream near the leading-edge region were investigated experimentally in the study in a large-scale linear vane cascade in which the aerodynamic flow field was considered. The introduction of slot film flow and fillet aimed to reduce the effects of the secondary flow structures from the leading edge through the passage towards the exit in an effort to decrease the pressure losses, improve film-cooling coverage and flow field uniformity for the next blade row. The two-dimensional vane profile was obtained from the hub-side airfoil of the GE-E3 engine nozzle guide vane. The slots were configured for two experimental cases to evaluate the influence of coolant flow rate and momentum; first, the effects of slot film injection from all four slots were observed and then compared with the second case injecting coolant only through the two central slots. Further effects were investigated by combining slot film-cooling with the leading-edge fillets employed on the endwall blade junction. The flow field measurements were quantified with spatial distributions of axial vorticity, total pressure loss, endwall static pressure and flow angle deviations taken across the cascade passage. The measurements were obtained at a Reynolds number of 2.0E+05 based on the cascade inlet velocity and vane chord length. Film-cooling inlet blowing ratios between 1.1 and 2.3 were investigated with the supply of coolant provided by a secondary channel. Film-cooling results were compared with the baseline case without slot film flow and fillet. The results indicated substantial improvement in the passage and exit planes with high inlet blowing ratios. The introduction of high momentum coolant flow from the central slots was seen to create laterally reversed axial vorticity, thereby counteracting the cross-flow tendency in the passage. The effects at the passage exit showed suppressed vortex structures with slot film injection from the two central slots only, with further improvements in the flow angle deviations. The leading-edge slots were seen to contribute positive axial vorticity, which enhanced the passage vortex that was pushed away from the endwall at the exit. When the fillet was introduced, it had favourable effects in reducing the pitchwise pressure gradients along the endwall. Filleted film-cooling then resulted in a faint passage vortex system (50-80% size and 20-50% strength reduction) with a restored endwall boundary layer at high film flow rates. The leading-edge fillet was highly effective at the inlet of the blade passage because it weakened the horseshoe vortex formation. Thus, upstream slot film-cooling has great potential to decrease the aerodynamic losses and is further compounded with the leading-edge fillet.

Download or read book Metal Temperatures and Coolant Flow in a Wire cloth Transpiration cooled Turbine Vane written by Herbert J. Gladden and published by . This book was released on 1975 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:

Download or read book The Influence of Film Cooling and Inlet Temperature Profile on Heat Transfer for the Vane Row of a 1 1 2 Stage Transonic High pressure Turbine written by Harika Senem Kahveci and published by . This book was released on 2010 with total page 269 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: The goal of this research was to establish an extensive database for typical engine hardware with a film-cooled first stage vane, which represents the foundation for future turbomachinery film cooling modeling and component heat transfer studies. Until this time, such a database was not available within the gas turbine industry. Accordingly, the study focuses on determination of the local heat flux for the airfoil and endwall surfaces of the vane row of a fully-cooled turbine stage. The measurements were performed at the Ohio State University Gas Turbine Laboratory using the Turbine Test Facility. The full-scale rotating 1 and 1/2 turbine stage is operated at the proper corrected engine design conditions: Flow Function (FF), corrected speed, stage Pressure Ratio (PR), and temperature ratios of gas to wall and gas to coolant. The primary measurements of temperature, pressure, and heat flux are repeated for different vane inlet temperature profiles and different vane cooling flows to establish an understanding of the influence of film cooling on local heat transfer. Double-sided Kapton heat-flux gauges are used for heat-flux measurements at different span locations along the airfoil surfaces and along the inner endwall. The cooling scheme consists of numerous cooling holes located on the endwalls, at the airfoil leading edge, on the airfoil pressure and suction surfaces, and at the trailing edge, resulting in a fully cooled first stage vane. The unique film-cooled endwall heat transfer data demonstrated in contour plots reveals insight to the complex flow behavior that is dominant in this region, which becomes even more complicated with the addition of coolant. Varying profile shapes resulted in significant heat transfer variations in a growing fashion towards the trailing edge region, which increased in magnitude when there is no coolant supply. The largest cooling effect is observed on 5% span pressure surface and at the inner endwall region. Heat transfer decreases from tip towards hub with addition of cooling. However, a similar decrease is not observed at the inner endwall region by doing so, which suggests excess coolant once beyond an optimum blowing ratio. Cooling flow rate and temperature profile shape affect the distributions on the airfoil surface very similarly, the latter observed more clearly at the endwall region. The vane outer cooling effect is comparable to the combined coolant effect at all surfaces, while no impact of purge flow is observed. Aligning the hot streaks with the vane leading edge lowered heat transfer compared to mid-passage alignment at the mid-span suction surface and through the endwall passage, and increased it at the endwall exit, while the pressure surface is found to be insensitive to this switch. Comparison with a previous research program with the un-cooled version of the vane gave good agreement on the pressure surface and at the endwall, but significantly lower heat transfer on the suction surface due to ingestion of the hot flow through the cooling holes when there is no cooling.