×

TURBINE AIRFOIL WITH VARIABLE AND COMPOUND FILLET

  • US 20060275112A1
  • Filed: 06/06/2005
  • Published: 12/07/2006
  • Est. Priority Date: 06/06/2005
  • Status: Active Grant
First Claim
Patent Images

1. An airfoil for a gas turbine engine, comprising:

  • an arcuate inner band having an inner platform; and

    an airfoil body extending outwardly from inner platform, said airfoil body having opposed pressure and suction sidewalls extending between a leading edge and a trailing edge thereof, said airfoil having an inner compound fillet, comprising;

    a concave first inner fillet disposed between said airfoil and said inner platform, said first inner fillet having a first radius and extending around the periphery of said airfoil; and

    a concave second inner fillet disposed between said airfoil and said inner platform, said second inner fillet extending from said leading edge aftward along said suction sidewall and terminating at a point axially forward of said trailing edge, said second fillet having a second radius greater than said first radius.

View all claims
  • 1 Assignment
Timeline View
Assignment View
    ×
    ×