Bearing configuration for a rotational equipment assembly
AssigneeRtx Corporation
InventorPaul R. Hanrahan
Life of this patent
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Abstract
An assembly for rotational equipment includes a shaft, a first rolling-element bearing, a second rolling-element bearing, and a mid-shaft foil bearing. The shaft extends along a rotational axis between and to a first axial end and a second axial end. The shaft is configured for rotation about the rotational axis. The first rolling-element bearing is disposed at the first axial end. The second rolling-element bearing is disposed at the second axial end. The mid-shaft foil bearing is disposed axially between the first rolling-element bearing and the second rolling-element bearing.
Claims11
A gas turbine engine for an aircraft propulsion system, the gas turbine engine comprising:
- a bladed compressor rotor and a bladed turbine rotor;
- a combustor section disposed axially between the bladed compressor rotor and the bladed turbine rotor, the combustor section including a combustor and a diffuser case, the diffuser case disposed between the bladed compressor rotor and the combustor,
- a shaft extending along a rotational axis between and to a first axial end and a second axial end, the shaft configured for rotation about the rotational axis, and wherein the shaft interconnects the bladed compressor rotor and the bladed turbine rotor;
- a first rolling-element bearing disposed axially forward of the bladed compressor rotor;
- a second rolling-element bearing disposed axially aft of the bladed turbine rotor;
- and
- a mid-shaft foil bearing disposed axially between the bladed compressor rotor and the bladed turbine rotor, wherein the mid-shaft foil bearing is mounted to the diffuser case.
A gas turbine engine for an aircraft propulsion system, the gas turbine engine comprising:
- a bladed compressor rotor and a bladed turbine rotor;
- a combustor section disposed axially between the bladed compressor rotor and the bladed turbine rotor, the combustor section including a combustor and a diffuser case, the diffuser case disposed between the bladed compressor rotor and the combustor;
- a shaft extending along a rotational axis between and to a first axial end and a second axial end, the shaft configured for rotation about the rotational axis, and the shaft interconnecting the bladed compressor rotor and the bladed turbine rotor;
- a first liquid-lubricated bearing disposed at the first axial end;
- a second liquid-lubricated bearing disposed at the second axial end;
- and
- an unlubricated mid-shaft foil bearing disposed axially between the bladed compressor rotor and the bladed turbine rotor, wherein the mid-shaft foil bearing is mounted to the diffuser case.
Dependencies are inferred from the claim text.