Patent ID: 9476320
Filing Date: 2016-10-25
CPC Classification: F01D,F02C,F02K,F05D,Y02T

Claim Text:
1. A bearing hub for a gas turbine engine comprising: first and second hub walls integrally formed with one another to provide a unitary structure; a radial to axial translation flange arm extending outward from an apex of the unitary structure; a translation flange extending outward from said radial to axial translation flange arm and angled relative to said radial to axial translation flange arm; a spring arm connected to the apex for connecting the bearing hub to a canted annular flange, the spring arm including at least a first flex point, a second flex point, and a third flex point, and wherein a stiffness of each of said flex points is configured to determine an amount of radial vibrations translated to axial vibrations by said bearing hub; and wherein each of said first, second, and third flex point is an angled corner of said spring arm.