๐”– Bobbio Scriptorium
โœฆ   LIBER   โœฆ

Heat transfer characteristics of a return-flow steam-cooled gas turbine blade

โœ Scribed by M. Obata; J. Yamaga; H. Taniguchi

Publisher
Elsevier Science
Year
1989
Tongue
English
Weight
733 KB
Volume
2
Category
Article
ISSN
0894-1777

No coin nor oath required. For personal study only.

๐Ÿ“œ SIMILAR VOLUMES

The interior heat transfer characteristi
The interior heat transfer characteristics of gas turbine blade due to sparse film cooling holes
โœ Zhang Jingyu; Chang Haiping ๐Ÿ“‚ Article ๐Ÿ“… 2005 ๐Ÿ› John Wiley and Sons ๐ŸŒ English โš– 213 KB

The film cooling technique is one of the most useful cooling methods. At present, the midchord region of gas turbine blades in an aeroengine often adopt a sparse film cooling technique and impingement cooling technique at the same time. So the interior heat transfer characteristics on the inner side

Three-dimensional flow and heat transfer
Three-dimensional flow and heat transfer calculations of film cooling at the leading edge of a symmetrical turbine blade model
โœ D. Lakehal; G.S. Theodoridis; W. Rodi ๐Ÿ“‚ Article ๐Ÿ“… 2001 ๐Ÿ› Elsevier Science ๐ŸŒ English โš– 1007 KB

Film cooling of a symmetrical turbine-blade model by lateral and non-lateral injection from one row of holes placed on each side near the leading edge is calculated with a 3D ยฎnite-volume method on multi-block grids. For various blowing rates, the ยฏow and temperature ยฎelds are predicted, and in part

Flow and heat transfer characteristics i
Flow and heat transfer characteristics in fuel cooling channels of a recooling cycle
โœ J. Qin; W. Bao; W.X. Zhou; D.R. Yu ๐Ÿ“‚ Article ๐Ÿ“… 2010 ๐Ÿ› Elsevier Science ๐ŸŒ English โš– 865 KB

Developing fuel with higher heat sink is widely carried out to meet the cooling requirement for an air breathing hypersonic vehicle. Especially, a recooling cycle has been newly proposed for an actively cooled scramjet to reduce the fuel flow for cooling. Fuel heat sink (cooling capacity) is repeate