Seal configurations for turbine assembly and bearing compartment interfaces
US10107141B2 · kind B2 · utility
0Cited by
3References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Apr 13, 2015 |
| Grant date | Oct 23, 2018 |
| Priority date | — |
| Expiry date | Sep 25, 2036 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2250/75
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
The present disclosure relates to gas turbine engine and seal configurations, and components for a gas turbine engine. In one embodiment, a seal for a gas turbine engine includes a first circumferential seal, a second circumferential seal and a seal support structure configured to retain at least a portion of each of the first and second seals. The seal support structure is mounted between a turbine assembly and bearing compartment, and wherein the first and second seals provide barriers to a cavity between the turbine assembly and bearing compartment.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.