Author: Hee-Koo MoonPublisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 424
Book Description
Modeling and Measurement of Heat Transfer on Turbine Blade Tips
Author: Hee-Koo MoonPublisher:
ISBN:
Category : Gas-turbines
Languages : en
Pages : 424
Book Description
Local Measurement and Numerical Modeling of Mass/heat Transfer from a Turbine Blade in a Linear Cascade with Tip Clearance
Author: Peitong JinLocal Heat Transfer and Effectiveness Measurements on Film Cooled Turbine Blade Tip Models
Author: Srinath Varadarajan EkkadPublisher:
ISBN:
Category : Heat
Languages : en
Pages : 248
Book Description
Measurements of Heat Transfer, Flow, and Pressures in a Simulated Turbine Blade Internal Cooling Passage
Author: Louis M. RussellPublisher:
ISBN:
Category : Flow visualization
Languages : en
Pages : 30
Book Description
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.
Gas Turbine Heat Transfer and Cooling Technology, Second Edition
Author: Je-Chin HanPublisher: CRC Press
ISBN: 1439855684
Category : Science
Languages : en
Pages : 892
Book Description
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.
Measurement and Analysis of Gas Turbine Blade Tip Heat Transfer and Film Cooling
Author: Jae Su KwakA Numerical Analysis of Heat Transfer and Effectiveness on Film Cooled Turbine Blade Tip Models
Author: Ali A. AmeriHeat Transfer Measurements and Predictions on a Power Generation Gas Turbine Blade
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 22
Book Description
Detailed heat transfer measurements and predictions are given for a power generation turbine rotor with 129 deg of nominal turning and an axial chord of 137 mm. Data were obtained for a set of four exit Reynolds numbers comprised of the design point of 628,000, -20%, +20%, and +40%. Three ideal exit pressure ratios were examined including the design point of 1.378, -10%, and +10%. Inlet incidence angles of 0 deg and +/-2 deg were also examined. Measurements were made in a linear cascade with highly three-dimensional blade passage flows that resulted from the high flow turning and thick inlet boundary layers. Inlet turbulence was generated with a blown square bar grid. The purpose of the work is the extension of three-dimensional predictive modeling capability for airfoil external heat transfer to engine specific conditions including blade shape, Reynolds numbers, and Mach numbers. Data were obtained by a steady-state technique using a thin-foil heater wrapped around a low thermal conductivity blade. Surface temperatures were measured using calibrated liquid crystals. The results show the effects of strong secondary vortical flows, laminar-to-turbulent transition, and also show good detail in the stagnation region.
Experimental Modeling and Measurement of Film Cooled Turbine Tip Shroud Heat Transfer Performance
Author: Louis William FlammPublisher:
ISBN:
Category : Heat
Languages : en
Pages : 334
Book Description
Author: