Seals for gas turbine engine nacelle cowlings
US9835092B2 · kind B2 · utility
7Cited by
3References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jun 30, 2015 |
| Grant date | Dec 5, 2017 |
| Priority date | — |
| Expiry date | Nov 12, 2035 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2240/55
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes an engine core and core nacelle cowling coupled to the engine core. The engine core has a core member that extends radially outward from the engine core. The core nacelle cowling has a cowling member that extends radially inward towards the engine core. The cowling member is offset axially from the core member to form a labyrinth seal that bounds a coolant inlet, thereby fluidly coupling the fan duct flow of the gas turbine engine with a core compartment defined between the engine core and core nacelle cowling.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.