GAS TURBINE ENGINE INTEGRALLY BLADED ROTOR

摘要

A rotor disk includes a web that extends from a rim radially inward to a bore. A spacer is integral with and extending generally axially from the rim. The spacer includes a flow path surface adjacent to an end wall of the rim. An inner surface is spaced radially inwardly from the flow path surface and extends between first and second axial locations. A fillet interconnects the inner surface and the web. The inner surface is tangent to the fillet at the first axial location. The second axial location axially aligns beneath vanes and surrounded by the inner surface. The spacer has first and second radial thicknesses respectively disposed at the first and second axial locations. The first and second radial thicknesses are different than one another. The spacer is at least partially tapering axially between the first and second axial locations.

主权项

1. A gas turbine engine rotor stack comprising:
a rotor disk including:
a web extending from a rim radially inward to a bore, anda spacer integral with and extending generally axially from the rim, the spacer including:
a flow path surface adjacent to an end wall of the rim,an inner surface spaced radially inwardly from the flow path surface and extending between first and second axial locations, the flow path surface configured to seal relative to a fixed stage of vanes,a fillet interconnecting the inner surface and the web, the inner surface tangent to the fillet at the first axial location, and the second axial location axially aligning beneath the vanes and surrounded by the inner surface,the spacer having first and second radial thicknesses respectively disposed at the first and second axial locations, the first and second radial thicknesses different than one another, andthe spacer at least partially tapering axially between the first and second axial locations.