Gas turbine engine rotor tip clearance and shaft dynamics system and method
US8702377B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Jun 23, 2010 |
| Grant date | Apr 22, 2014 |
| Priority date | — |
| Expiry date | Feb 20, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/4932
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine rotor tip clearance and shaft dynamics system and method are provided. The system includes a gas turbine engine that is disposed within an engine case and includes a rotor. A rotor bearing assembly disposed within the engine case rotationally mounts the gas turbine engine rotor. Vibration isolators mounted on the engine case are coupled to the rotor bearing assembly, and are configured to provide linear and independently tunable stiffness and damping. A method includes determining the location of a gas turbine engine rotor rotational axis, disposing the gas turbine engine rotor in an engine case at the rotational axis location, mounting a plurality of vibration isolators that include a plurality of adjustment devices on the engine case, coupling each vibration isolator to the gas turbine engine rotor, and locking the gas turbine engine rotor at the rotational axis location using the plurality of adjustment devices.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.