Author: R. C. KingcombePublisher:
ISBN:
Category : Heat
Languages : en
Pages :
Book Description
Aerodynamic and Heat Transfer Measurements on Blading for a High Rim-speed Transonic Turbine
Author: R. C. KingcombeHandbook of Turbomachinery
Author: Earl Logan, Jr.Publisher: CRC Press
ISBN: 0203911997
Category : Technology & Engineering
Languages : en
Pages : 927
Book Description
Building on the success of its predecessor, Handbook of Turbomachinery, Second Edition presents new material on advances in fluid mechanics of turbomachinery, high-speed, rotating, and transient experiments, cooling challenges for constantly increasing gas temperatures, advanced experimental heat transfer and cooling effectiveness techniques, and propagation of wake and pressure disturbances. Completely revised and updated, it offers updated chapters on compressor design, rotor dynamics, and hydraulic turbines and features six new chapters on topics such as aerodynamic instability, flutter prediction, blade modeling in steam turbines, multidisciplinary design optimization.
Scientific and Technical Aerospace Reports
Author: ASME Technical Papers
Author: Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 438
Book Description
NASA SP.
Author: Aeronautical Engineering: A Cumulative Index to a Continuing Bibliography (supplement 261)
Author: Government Reports Annual Index
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1316
Book Description
Paper
Author: Publisher:
ISBN:
Category : Mechanical engineering
Languages : en
Pages : 452
Book Description
Blade Heat Transfer Measurements and Prediction in a Transonic Turbine Cascade
Author: Studies on Transonic Turbines with Film-Cooled Blades
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 109
Book Description
In the third year of the contract, further advances were made towards the goal of gathering the heat transfer and aerodynamics flow data necessary for a good understanding of the performance of film-cooled, highly-loaded, transonic turbine blading. The MIT cascade blowdown facility now fully operational was used in evaluating the heat transfer performance of the four blade profiles designed in the first year of the program. The results show that the level of turbulence is an important parameter in determining heat transfer in transonic cascades. It also shows that the heat transfer to the trailing edge of the blades is very high being about 75% of the heat transfer to the leading edge. A comparison of the Nusselt number calculated from heat transfer measurements with the Nusselt number obtained by a prediction method using the pressure distribution shows good correspondence. The variation of average Stanton number over a range of Mach numbers shows that the reference blade has the most superior heat transfer performance. Preliminary data has been obtained on the off-design performance of the blades and full scale tests are underway. Comparative studies show that about 21% less heat needs to be taken out by internal cooling if one stage of a transonic turbine is used to replace two moderately loaded subsonic stages which produce the same output, have the same inlet stagnation conditions, have the same mass flow and the same tip speed. This demonstrates one of the potential advantages of transonic turbines.