(19)
(11) EP 2 565 383 A3

(12) EUROPEAN PATENT APPLICATION

(88) Date of publication A3:
07.09.2016 Bulletin 2016/36

(43) Date of publication A2:
06.03.2013 Bulletin 2013/10

(21) Application number: 12182433.8

(22) Date of filing: 30.08.2012
(51) International Patent Classification (IPC): 
F01D 5/18(2006.01)
(84) Designated Contracting States:
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
Designated Extension States:
BA ME

(30) Priority: 31.08.2011 US 201113222490

(71) Applicant: United Technologies Corporation
Hartford, CT 06101 (US)

(72) Inventors:
  • Abdel-Messeh, William
    Middletown, CT Connecticut 06457 (US)
  • Piggush, Justin D.
    LaCrosse, WI Wisconsin 54601 (US)

(74) Representative: Hull, James Edward 
Dehns St. Bride's House 10 Salisbury Square
London EC4Y 8JD
London EC4Y 8JD (GB)

   


(54) Airfoil with nonlinear cooling passage


(57) An example method of manufacturing an airfoil (30) includes providing a ceramic core (64) corresponding to an interior cooling channel (42). A refractory metal core (66) is provided that corresponds to a cooling passage (46). The cores are arranged in a mold (60). An airfoil structure (30) is cast about the cores to provide a turbine engine airfoil. The turbine engine airfoil (30) includes a wall (44) providing the interior cooling channel (42) and an exterior airfoil surface (34). The cooling passage (46) is provided in the wall (44) and fluidly connects the interior cooling channel (42) to the exterior airfoil surface (34). The cooling passage (46) includes multiple inlets (48) and multiple outlets (50) respectively adjoining the interior cooling channel (42) and the exterior airfoil surface (34). At least one of a first inlet (48) and outlet (50) has a different structural flow characteristic than at least one of a second inlet and outlet (48,50).







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