EP 3408501 B1 20210317 - FILM COOLING HOLE IN GAS TURBINE COMPONENTS
Title (en)
FILM COOLING HOLE IN GAS TURBINE COMPONENTS
Title (de)
FILMKÜHLLOCH IN GASTURBINEN BAUTEILEN
Title (fr)
TROU POUR FILM D'AIR DE REFROIDISSEMENT DANS DES PIÈCES DE TURBINE À GAZ
Publication
Application
Priority
- DE 102016204824 A 20160323
- EP 2017056834 W 20170322
Abstract (en)
[origin: WO2017162743A1] The invention relates to a film cooling hole (20) of gas turbine components to be cooled, having an inflow section (26) with a constant flow area, to which a diffuser section (28) with a variable flow area is connected. The aim of the invention is to provide a particularly efficient film cooling. To this end, the diffuser region (26) is simply widened in the direction perpendicular to the flow direction of the hotter medium MH.
IPC 8 full level
F01D 5/18 (2006.01)
CPC (source: EP US)
F01D 5/186 (2013.01 - EP US); F05D 2250/324 (2013.01 - US); F05D 2250/52 (2013.01 - US); F05D 2260/202 (2013.01 - EP US); F23R 2900/03042 (2013.01 - US)
Designated contracting state (EPC)
AL AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HR HU IE IS IT LI LT LU LV MC MK MT NL NO PL PT RO RS SE SI SK SM TR
DOCDB simple family (publication)
WO 2017162743 A1 20170928; DE 102016204824 A1 20170928; EP 3408501 A1 20181205; EP 3408501 B1 20210317; US 2019078443 A1 20190314
DOCDB simple family (application)
EP 2017056834 W 20170322; DE 102016204824 A 20160323; EP 17715064 A 20170322; US 201716085176 A 20170322