Sealing arrangement on combustor to turbine interface in a gas turbine
US10753214B2 · kind B2 · utility
2Cited by
1References
15Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Jul 14, 2017 |
| Grant date | Aug 25, 2020 |
| Priority date | — |
| Expiry date | Aug 17, 2038 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF02C7/20
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine unit having a combustor having a liner, a turbine, arranged downstream of the liner along a main flow gas direction and including a plurality of first stage vanes, a rotor cover support located inwardly of the vanes, and a sealing arrangement at a combustor to turbine interface, wherein the sealing arrangement includes a first dogbone seal extending between the rotor cover support and an inner downstream end of the liner or between the rotor cover support and a bulkhead located at the inner downstream end of the liner.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.