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Proc. ASME. GT2022, Volume 6A: Heat Transfer — Combustors; Film Cooling, V06AT12A045, June 13–17, 2022
Paper No: GT2022-83961
... Abstract Due to the high demand for the output power and thermal efficiency, the turbine inlet temperature is extremely high which has significantly exceeded the melting point of the blade material. Therefore, the turbine blade cooling system plays a pivotal role in the entire engine...
Proc. ASME. GT2021, Volume 9B: Structures and Dynamics — Fatigue, Fracture, and Life Prediction; Probabilistic Methods; Rotordynamics; Structural Mechanics and Vibration, V09BT29A004, June 7–11, 2021
Paper No: GT2021-58445
...Abstract Abstract Turbine blades are used under increasingly severe conditions in order to increase the thermal efficiency of the gas turbines in operation. Friction dampers are often used to reduce the vibration of the blade and improve the plant reliability. Under platform dampers designed...
Proc. ASME. GT2020, Volume 10B: Structures and Dynamics, V10BT26A005, September 21–25, 2020
Paper No: GT2020-14477
...Application of Spectral Method for Vibration-Induced High-Cycle Fatigue Evaluation of an HP Turbine Blade Iroizan Ubulom1 1Center for Power and Propulsion, School of Aerospace, Transport and Manufacturing (SATM), Cranfield University, Bedford, MK430AL, United Kingdom ABSTRACT A method of fluid...
Proc. ASME. GT2020, Volume 11: Structures and Dynamics: Structural Mechanics, Vibration, and Damping; Supercritical CO2, V011T30A015, September 21–25, 2020
Paper No: GT2020-14757
...Abstract Abstract Turbine blades are now being used under increasingly severe conditions in order to increase the thermal efficiency of gas turbines. Friction dampers are often used to reduce the vibration of the blade and improve the plant reliability. This is a general study dealing...
Proc. ASME. GT2020, Volume 8: Industrial and Cogeneration; Manufacturing Materials and Metallurgy; Marine; Microturbines, Turbochargers, and Small Turbomachines, V008T18A004, September 21–25, 2020
Paper No: GT2020-14449
..., a refractory abrasive tip material was developed and applied to a plain turbine blade tip to work in conjunction with an abradable coating on the tip-shoe. Process development efforts resulted in abrasive material that could be as much as 2mm thick. Further, the abrasive media included imbedded grits...
Proc. ASME. GT2020, Volume 7A: Heat Transfer, V07AT15A015, September 21–25, 2020
Paper No: GT2020-14847
...Abstract Abstract Convective cooling inside the internal passage of a turbine blade trailing edge is often insufficient at the sharp corner, when cutback slot cooling is not present. This study investigates the convective heat transfer and pressure drop in a simplified trailing edge internal...
Proc. ASME. GT2020, Volume 7A: Heat Transfer, V07AT15A034, September 21–25, 2020
Paper No: GT2020-16115
.... The turning internal radius has stronger effect than turning angle. With higher jet Reynolds number, both the heat transfer and total pressure loss increase dramatically, and the effects of geometrical parameters are clearer. turbine blade internal cooling Reynolds number Nusselt number total...
Proc. ASME. GT2020, Volume 7B: Heat Transfer, V07BT12A045, September 21–25, 2020
Paper No: GT2020-15110
...EXPERIMENTAL STUDY OF FULL COVERAGE FILM COOLING EFFECTIVENESS FOR A TURBINE BLADE WITH COMPOUND SHAPED HOLES Shuai-qi Zhang1, Cun-liang Liu1,2, Qi-ling Guo3, Da-peng Liang1, Fan Zhang1 1Northwestern Polytechnical University, Xi an, P. R. China 2 Shaanxi Key Laboratory of Thermal Sciences in Aero...
Proc. ASME. GT2020, Volume 7B: Heat Transfer, V07BT12A034, September 21–25, 2020
Paper No: GT2020-14836
...FILM COOLING PERFORMANCE ON TURBINE BLADE SUCTION SIDE WITH VARIOUS FILM COOLING HOLE ARRANGEMENTS Zhiyu Zhou1,2, Haiwang Li1,2, Gang Xie1,2, Ruquan You1,2 1 National Key Laboratory of Science and Technology on Aero Engines Aero-thermodynamics 2 School of Energy and Power Engineering, Beihang...
Proc. ASME. GT2019, Volume 5A: Heat Transfer, V05AT11A005, June 17–21, 2019
Paper No: GT2019-90421
... when the orifice width falls or channel Reynolds increases, but the wall jet impingement distance appears to be less influential. Key Words: Turbine blade; Internal cooling; Reynolds number; Nusselt number; Total pressure loss; Nomenclature Symbols Ac area of cooling structure surface, m2 Atar area...
Proc. ASME. GT2011, Volume 5: Heat Transfer, Parts A and B, 1653-1664, June 6–10, 2011
Paper No: GT2011-46427
... but nevertheless engine relevant turbine blade cooling design. The system has been investigated with ribbed walls in both passages for cooling enhancement as well as with smooth walls as a reference version in order to identify the effects induced by ribs. The rib orientation on the walls is 45 deg. With a rib...
Proc. ASME. GT2011, Volume 5: Heat Transfer, Parts A and B, 1155-1164, June 6–10, 2011
Paper No: GT2011-45287
... turbine blade. The effects of various parameters, such as the arrays of impinging nozzles, the jet Reynolds number, the jet-to-jet distance, the ratio of nozzle-to-surface spacing to jet diameter H/d, and the radius of curvature of the target surface, on the flow and heat transfer characteristics...
Proc. ASME. GT2005, Volume 2: Turbo Expo 2005, 821-834, June 6–9, 2005
Paper No: GT2005-68112
... 03 11 2008 Recent advances in virtually all areas of industrial Computed Tomography (CT) now allow faster, higher resolution, and increasingly economic CT inspection of turbine blades than ever before. CT is now used for a wide range of Non Destructive Testing and Evaluation (NDT&E...