Gas turbine fuel nozzle seal
US5328101A · kind A · utility
Assignee
Inventor
Key dates
| Filing date | Aug 27, 1993 |
| Grant date | Jul 12, 1994 |
| Priority date | — |
| Expiry date | Aug 27, 2013 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10S277/91
- WIPO fieldMechanical elements
- WIPO sectorMechanical engineering
Abstract
A fuel nozzle (10) for a gas turbine includes an annular nozzle body (12) having a forward end with interior and exterior surfaces; a gas tip (14) having a forward fuel discharge end and a rearward mounting end, the rearward mounting end at least partially receivable in the forward end of the nozzle body (12); a resilient seal (38) inserted between the nozzle body (12) and the gas tip (14); a seal ring (26) mounted on the rearward mounting end of the gas tip (14), adapted to axially compress the resilient seal (38) when the seal ring (26) is engaged with the nozzle body (12); and a locking sleeve (48) on the exterior surface of the nozzle body (12) for locking the seal ring ( 26 ) to the gas tip ( 14 ).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.