(19)
(11) EP 2 204 542 A3

(12) EUROPEAN PATENT APPLICATION

(88) Date of publication A3:
03.04.2013 Bulletin 2013/14

(43) Date of publication A2:
07.07.2010 Bulletin 2010/27

(21) Application number: 09178822.4

(22) Date of filing: 11.12.2009
(51) International Patent Classification (IPC): 
F01D 5/30(2006.01)
(84) Designated Contracting States:
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 SE SI SK SM TR
Designated Extension States:
AL BA RS

(30) Priority: 30.12.2008 US 346301

(71) Applicant: General Electric Company
Schenectady, NY 12345 (US)

(72) Inventor:
  • Boyer, Bradley T.
    Greenville, SC 29607 (US)

(74) Representative: Cleary, Fidelma et al
GE International Inc. Global Patent Operation-Europe 15 John Adam Street
London WC2N 6LU
London WC2N 6LU (GB)

   


(54) Tilted turbine blade root configuration


(57) A rotor blade (120), (126) for use in a turbine engine, the rotor blade (120), (126) comprising a root (138) and, extending in a radial direction from the root (138), an airfoil (136), wherein the root (138) includes at least one root aligned surface (178) that is tilted. Tilted may comprise a non-radial orientation. The root aligned surfaces (178) may comprise the surfaces along the root (138) that are configured to align with and be relatively closely spaced from or in contact with the root aligned surfaces (178) of the root (138) of a neighboring rotor blade (120), (126). The rotor blade (120), (126) may comprise at least two root aligned surfaces (178), one of which resides on a pressure side (143) of the rotor blade (120), (126) and the other of which resides on a suction side (144) of the rotor blade (120), (126). The root aligned surfaces (178) may be tilted.







Search report









Search report