US 8,087,885 B2 · Stacked annular components for turbine engines

Abstract

Improved annular components and improved methods for assembling annular components into a turbine engine are described with respect to an axial compressor having a plurality of annular compressor rotor airfoil assemblies (120) as an example. Each compressor rotor airfoil assembly comprises an annular rotor portion (122), a spacer portion (124) extending axially therefrom and a plurality of airfoils (52) extending radially therefrom. The plurality of airfoils may be integrally formed with the annular portion. The compressor rotor airfoil assemblies are stacked sequentially on a center-tie (134) or outer circumferential tie. The spacer portion of one compressor rotor airfoil assembly (120a) abuts the annular rotor portion of the adjacent compressor rotor airfoil assembly (120b) to retain one another on the center-tied outer circumferential tie. By stacking the compressor rotor airfoil assemblies sequentially and then retaining them, the typical split cases, flanges and rotor bolts may be eliminated.

Claims35

Dependent claims

An airfoil assembly for a turbine engine comprising:

an annular portion disposed about an axis, the annular portion having an interlocking recess disposed in an axially forward end of the annular portion sized to receive a corresponding interlocking axial projection;
a spacer portion extending from the annular portion, wherein the spacer portion extends axially from the annular portion and has an annular inner surface that is not parallel to an annular inner surface of the annular portion;
and
a plurality of airfoils extending radially from the annular portion, the plurality of airfoils integrally formed with the annular portion.

1 more element

Dependencies are inferred from the claim text.

Stacked annular components for turbine engines

Life of this patent

Stacked annular components for turbine engines

Life of this patent

Abstract

Claims35