EP 1869291 B1 20140730 - CONVECTIVELY COOLED GAS TURBINE BLADE
Title (en)
CONVECTIVELY COOLED GAS TURBINE BLADE
Title (de)
KONVEKTIV GEKÜHLTE GASTURBINENSCHAUFEL
Title (fr)
AUBE DE TURBINE A GAZ A REFROIDISSEMENT PAR CONVECTION
Publication
Application
Priority
- EP 2006061163 W 20060330
- RU 2005110990 A 20050414
Abstract (en)
[origin: WO2006108764A1] The invention relates to a gas turbine blade comprising a cooling air channel (609) which extends along the front edge (604) of the blade and has an outlet (611) arranged in the region of the blade head. The contour of the outlet is geometrically similar to the cross-section of the cooling air channel, enabling flow inhomogeneities of the cooling air flow, which locally negatively influence the heat transfer and thus the cooling efficiency, to be eliminated.
IPC 8 full level
F01D 5/18 (2006.01)
CPC (source: EP US)
F01D 5/187 (2013.01 - EP US); F05D 2250/70 (2013.01 - EP US); F05D 2260/201 (2013.01 - EP US)
Designated contracting state (EPC)
AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR
DOCDB simple family (publication)
WO 2006108764 A1 20061019; EP 1869291 A1 20071226; EP 1869291 B1 20140730; RU 2005110990 A 20061020; RU 2425982 C2 20110810; US 2008181784 A1 20080731; US 7766619 B2 20100803
DOCDB simple family (application)
EP 2006061163 W 20060330; EP 06725419 A 20060330; RU 2005110990 A 20050414; US 90742007 A 20071012