EP 2469035 B1 20200401 - TURBINE ENGINE COMPONENT COMPRISING A LEADING EDGE AIRFOIL-TO-PLATFORM FILLET COOLING TUBE
Title (en)
TURBINE ENGINE COMPONENT COMPRISING A LEADING EDGE AIRFOIL-TO-PLATFORM FILLET COOLING TUBE
Title (de)
GASTURBINENKOMPONENTE MIT EINER LEITKANTENKÜHLUNG
Title (fr)
REFROIDISSEMENT DU BORD D'ATTAQUE D'UN COMPOSANT DE TURBINE À GAZ
Publication
Application
Priority
US 97741810 A 20101223
Abstract (en)
[origin: EP2469035A2] A turbine engine component (10) includes an airfoil portion having a leading edge (18), a platform (14), a leading edge airfoil to platform fillet (16), and a cooling tube (30) located within said fillet (16). The cooling tube (30) has a flared entrance (31) end and a flared exit end (33). The invention also extends to a core used to form the turbine engine component.
IPC 8 full level
CPC (source: EP US)
B22C 9/10 (2013.01 - EP US); F01D 5/186 (2013.01 - EP US); F01D 5/187 (2013.01 - EP US); F01D 9/041 (2013.01 - US); F01D 9/065 (2013.01 - EP); F05D 2240/121 (2013.01 - EP US); F05D 2240/81 (2013.01 - EP US); F05D 2250/11 (2013.01 - EP US); F05D 2250/23 (2013.01 - EP US); F05D 2250/27 (2013.01 - EP); F05D 2250/323 (2013.01 - EP); F05D 2250/324 (2013.01 - EP)
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)
EP 2469035 A2 20120627; EP 2469035 A3 20171213; EP 2469035 B1 20200401; US 2012163993 A1 20120628
DOCDB simple family (application)
EP 11250867 A 20111021; US 97741810 A 20101223