Author: Goldman, Louis J.Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 38
Book Description
Cold-air Annular-cascade Investigation of Aerodynamic Performance of Cooled Turbine Vanes
Author: Goldman, Louis J.Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 38
Book Description
Cold-air Annular-cascade Investigation of Aerodynamic Performance of Cooled Turbine Vanes: Trailing-edge ejection, film cooling, and transpiration cooling
Author: Goldman, Louis J.Publisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 40
Book Description
Cold-air Annular-cascade Investigation of Aerodynamic Performance of Core-engine-cooled Turbine Vanes
Author: Kerry L. McLallinPublisher:
ISBN:
Category : Turbines
Languages : en
Pages : 28
Book Description
Cold-air Performance of Compressor-drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine. 1: Volute-manifold and Stator Performance
Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 24
Book Description
The aerodynamic performance of the inlet manifold and stator assembly of the compressor-drive turbine was experimentally determined with cold air as the working fluid. The investigation included measurements of mass flow and stator-exit fluid torque as well as radial surveys of total pressure and flow angle at the stator inlet and annulus surveys of total pressure and flow angle at the stator exit. The stator-exit aftermixed flow conditions and overall stator efficiency were obtained and compared with their design values and the experimental results from three other stators. In addition, an analysis was made to determine the constituent aerodynamic losses that made up the stator kinetic energy loss. (Author).
Gas Turbine Blade Cooling
Author: Chaitanya D GhodkePublisher: SAE International
ISBN: 0768095026
Category : Technology & Engineering
Languages : en
Pages : 238
Book Description
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.
Scientific and Technical Aerospace Reports
Author: NASA Technical Paper
Author: NASA Technical Memorandum
Author: Monthly Catalog of United States Government Publications, Cumulative Index
Author: United States. Superintendent of DocumentsPublisher:
ISBN:
Category : United States
Languages : en
Pages : 1408
Book Description
Monthly Catalog of United States Government Publications
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1932
Book Description