Gas turbine vane assembly seal and support system
US5149250A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Feb 28, 1991 |
| Grant date | Sep 22, 1992 |
| Priority date | — |
| Expiry date | Feb 28, 2011 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF01D9/042
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
Apparatus for statically determinant mounting of a vane assembly in a gas turbine engine includes means for assuring contact support of the vane assembly in a predetermined number of identified locations. The vane assembly includes at least one vane extending between a radially outer nozzle band and a radially inner nozzle band. The radially outer nozzle band has axially directed load bearing elements on distal ends. The radially inner nozzle band has a radially inwardly oriented flange depending therefrom. The engine includes a radially outer support member positioned to engage the load bearing elements in the radially outer nozzle band when the vane assembly is in an operative position. A radially inner support member is incorporated in the engine for engaging the flange to axially restrain the vane assembly. The inner support member includes means for releasably connecting the flange thereto for supporting the vane assembly in radially and circumferential directions. Both the inner nozzle band and outer nozzle band have seals associated therewith for inhibiting gas flow between the respective nozzle band and the adjacent supporting members.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.