(19)
(11)EP 1 900 905 A3

(12)EUROPEAN PATENT APPLICATION

(88)Date of publication A3:
22.06.2011 Bulletin 2011/25

(43)Date of publication A2:
19.03.2008 Bulletin 2008/12

(21)Application number: 07253638.6

(22)Date of filing:  13.09.2007
(51)International Patent Classification (IPC): 
F01D 5/18(2006.01)
(84)Designated Contracting States:
AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC MT NL PL PT RO SE SI SK TR
Designated Extension States:
AL BA HR MK RS

(30)Priority: 13.09.2006 US 520374

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

(72)Inventors:
  • Cunha, Francisco J.
    Avon CT, 06001 (US)
  • Dahmer, Matthew T.
    Milford MA, 01757 (US)

(74)Representative: Leckey, David Herbert 
Dehns St Bride's House 10 Salisbury Square
London EC4Y 8JD
London EC4Y 8JD (GB)

  


(54)Airfoil thermal management with microcircuit cooling


(57) A turbine engine component (100), such as a turbine engine blade, has an airfoil portion (104) with a pressure side wall (106) and a suction side wall (108), a plurality of ribs (110) extending between the pressure side wall (106) and the suction side wall (108), and a plurality of supply cavities (120, 144, 150, 164) located between the ribs (110). The component further has an arrangement for cooling the airfoil portion (104). The cooling arrangement comprises a first cooling circuit (114, 117) embedded within the suction side wall (108) for convectively cooling the suction side wall (108), a second cooling circuit (124, 130) embedded within the pressure side wall (106) for cooling the pressure side wall (106), and a third passageway (122, 128) for increasing a temperature of at least one of the ribs (110) by conduction.







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