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US 10,240,529 B2Granted
Gas turbine engine aft bearing arrangement
AssigneeUnited Technologies Corporation
InventorGregory M. Savela
Life of this patent
Estimating the term…
Abstract
An example gas turbine engine includes a turbine and first and second spools coaxial with one another. The first spool is arranged within the second spool and extends between forward and aft ends. The aft end extends axially beyond the second spool and supports the turbine. A housing is arranged downstream from the turbine. First and second bearings are mounted to the aft end of the first spool and supported by the housing portion.
Claims19
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;
- a spring arm connected to the apex for connecting the bearing hub to a canted annular flange, the spring arm including a plurality of angled flex points.
1 more element
A gas turbine engine comprising:
- a fan;
- a compressor section fluidly connected to the fan, the compressor section comprising a first compressor section and a second compressor section;
- a combustor fluidly connected to the compressor section;
- a turbine section fluidly connected to the combustor, the turbine section comprising:
- a first turbine section coupled to the first compressor section via a shaft;
- a second turbine section;
- 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 annular apex of the unitary structure;
- a translation flange extending outward from said radial to axial translation flange arm;
- turbine exhaust case arranged downstream from the second turbine section and supporting the annular apex;
- and
- a spring arm connecting the annular apex to a canted annular flange of the turbine exhaust case, the spring arm including a plurality of angled flex points.
9 more elements
A method for damping vibrations in a bearing hub comprising the steps of:
- converting radial vibrations in said bearing hub to axial vibrations using a spring arm and a radial to axial vibration translation flange, wherein the spring arm includes a plurality of angled flex points;
- damping axial vibrations of said radial to axial vibration translation flange using an axial vibration damper.
Dependencies are inferred from the claim text.