Invention Grant
- Patent Title: Gas turbine engine shaft bearing configuration
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Application No.: US17213725Application Date: 2021-03-26
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Publication No.: US11566586B2Publication Date: 2023-01-31
- Inventor: Brian D. Merry , Gabriel L. Suciu , Karl L. Hasel
- Applicant: Raytheon Technologies Corporation
- Applicant Address: US CT Farmington
- Assignee: Raytheon Technologies Corporation
- Current Assignee: Raytheon Technologies Corporation
- Current Assignee Address: US CT Farmington
- Agency: Carlson, Gaskey & Olds, P.C.
- Main IPC: F02C7/36
- IPC: F02C7/36 ; F02K3/00 ; F01D25/16 ; F02K3/04 ; F02C7/06 ; F02C3/04

Abstract:
A gas turbine engine includes a shaft and a hub supported by the shaft. A housing includes an inlet and an intermediate case that respectively provide an inlet and an intermediate case flow path. A rotor is connected to the hub and supports a compressor section arranged axially between the inlet and the intermediate case flow paths. A compressor section inlet has a radially inner boundary that is spaced a second radial distance from the rotational axis different from the first radial distance. First and second bearings support the shaft relative to the intermediate case and the inlet case, respectively. An inner race of the first bearing and an inner race of the second bearing engage and rotate with the hub. A fan shaft is drivingly connected to a fan having fan blades. A gear system is connected to the fan shaft and driven through a flex shaft.
Public/Granted literature
- US20210239074A1 GAS TURBINE ENGINE SHAFT BEARING CONFIGURATION Public/Granted day:2021-08-05
Information query
IPC分类: