Author: Roy G. StabePublisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 20
Book Description
Aerodynamic Performance of a Ceramic-coated Core Turbine Vane Tested with Cold Air in a Two-dimensional Cascade
Author: Roy G. StabePublisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 20
Book Description
Aerodynamic Performance of a Ceramic-coated Core Turbine Vane Tested with Cold Air in a Two-dimensional Cascade
Author: Roy G. StabePublisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 20
Book Description
Aerodynamic Performance of a Fully Film Cooled Core Turbine Vane Tested with Cold Air in a Two-dimensional Cascade
Author: Roy G. StabePublisher:
ISBN:
Category : Aircraft gas-turbines
Languages : en
Pages : 24
Book Description
The aerodynamic performance of a fully film cooled core turbine vane was investigated experimentally in a two-dimensional cascade of 10 vanes. Three of the 10 vanes were cooled; the others were solid (uncooled) vanes. Cold air was used for both the primary and coolant flows. The cascade test covered a range of pressure ratios corresponding to ideal exit critical velocity ratios of 0.6 to 0.95 and a range of coolant flow rates to 7.5 percent of the primary flow. The coolant flow was varied by changing the coolant supply pressure. The principal measurements were cross-channel surveys of exit total pressure, static pressure, and flow angle. The results presented include exit survey data and overall performance in terms of loss, flow angle, and weight flow for the range of exit velocity ratios and coolant flows investigated. The performance of the cooled vane is compared with the performance of an uncooled vane of the same profile and also with the performance obtained with a single cooled vane in the 10-vane cascade.
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.
NASA Technical Memorandum
Author: Monthly Catalog of United States Government Publications
Author: Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 2834
Book Description
Scientific and Technical Aerospace Reports
Author: Government Reports Annual Index
Author: Publisher:
ISBN:
Category : Government reports announcements & index
Languages : en
Pages : 882
Book Description
Author: 
Author: