Patent ID: 9657594
Date: 2017-05-23
CPC Classifications: F01D,F04D,F05D,F16C

Claim:
1. A gas turbine engine, comprising: a compressor; a turbine; a static structure having a bearing pilot feature configured to pilot a bearing system; and a self-aligning foil bearing system operative to transmit rotor loads from at least one of the compressor and the turbine to the static structure, wherein the foil bearing system includes: a foil bearing; a housing configured to receive the foil bearing and configured to be at least partially received within the bearing pilot feature; a fulcrum extending outward from the housing toward the bearing pilot feature; and an axial spring configured to impart an axial load on the housing and to generate a predetermined radial frictional damping characteristic of the housing, wherein the self-aligning foil bearing system is operative to align the foil bearing with an axis of rotation of the at least one of the compressor and the turbine.