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US 2013/0259649 A1Published application
Gas turbine engine fan drive gear system damper
AssigneeUnited Technologies Corporation
InventorsJames B. Coffin, John R. Otto
Life of this patent
Estimating the term…
Abstract
A gas turbine engine includes a fan section. A turbine section is coupled to the fan section via a geared architecture. The geared architecture includes a torque frame and a flex support spaced apart from one another at a location. A gear train is supported by the torque frame. A damper is provided between the torque frame and the flex support at the location.
Claims13
A fan drive gear system for a gas turbine engine comprising:
- first and second members spaced apart from one another at a location;
- a gear train supported by the first member;
- and
- a damper provided between the first member and the second member at the location, the damper is configured to engage the first and second members substantially throughout engine operation.
1 more element
-15. (canceled)
A gas turbine engine comprising:
- a fan section;
- a turbine section coupled to the fan section via a geared architecture, the geared architecture including:
- a torque frame and a flex support spaced apart from one another at a location;
- a gear train supported by the torque frame;
- and
- a damper provided between the torque frame and the flex support at the location, the damper is configured to engage the first and second members substantially throughout engine operation.
3 more elements
(canceled)
Dependencies are inferred from the claim text.