Variable stator vane undercut button
A variable stator vane includes airfoil mounted to a button centered about a rotational axis and having cylindrical portion supporting airfoil and a button undercut extending away from cylindrical portion and radially inwardly from circumference of cylindrical portion. Conical portion of button circumscribed about conical axis of revolution extends away from cylindrical portion. Conical axis of revolution may be tilted with respect to and may intersect rotational axis. Airfoil may include airfoil overhang extending radially outwardly beyond circular trailing edge of button. Variable stator vane may include airfoil disposed between spaced apart outer and inner buttons centered about a rotational axis, inner button having a cylindrical portion supporting airfoil and circumscribed about rotational axis, and button undercut extending away from cylindrical portion and radially inwardly from a circumference of cylindrical portion with respect to rotational axis. Outer and inner spindles extend from outer and inner buttons and airfoil.
1. A gas turbine engine variable vane assembly comprising:
at least one circular row of variable stator vanes,
the variable stator vanes including airfoils disposed between spaced apart outer and inner buttons centered about rotational axes,
the inner buttons having cylindrical portions supporting the airfoils and circumscribed about the rotational axes,
button undercuts extending away from the cylindrical portions and radially inwardly from circumferences of the cylindrical portions with respect to the rotational axes,
the inner buttons rotatably disposed in inner circular recesses in an inner ring and connecting recesses in the inner ring circumferentially connecting adjacent ones of the inner circular recesses; and
the button undercuts including conical portions extending away from the cylindrical portions and being circumscribed about conical axes of revolution of the variable stator vanes.
2. An assembly as claimed in claim 1 , further comprising the conical axes of revolution tilted with respect to the rotational axes.
3. An assembly as claimed in claim 2 , further comprising the conical axes of revolution intersecting the rotational axes.
4. An assembly as claimed in claim 2 , further comprising:
the airfoils including airfoil overhangs extending radially outwardly beyond circular trailing edges of the inner buttons,
outer spindles extending away from the outer buttons and the airfoils, and
inner spindles extending away from the inner buttons and the airfoils.
5. An assembly as claimed in claim 4 , further comprising the inner spindles disposed through inner openings in the inner ring.
6. An assembly as claimed in claim 4 , further comprising the airfoils extending from bases of the airfoils on the inner buttons and fillets between the airfoils and the inner buttons extending around the bases and the airfoils extend and the airfoils.
7. An assembly as claimed in claim 5 , further comprising the outer spindles disposed through outer openings in a casing supporting the variable stator vanes.