Turbine frame assembly and method for a gas turbine engine
US8371812B2 · kind B2 · utility
64Cited by
29References
16Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Nov 29, 2008 |
| Grant date | Feb 12, 2013 |
| Priority date | — |
| Expiry date | Oct 13, 2031 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2230/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine frame assembly for a gas turbine engine includes: (a) a turbine frame including: (i) an outer ring; (ii) a hub; (ii) a plurality of struts extending between the hub and the outer ring; (b) a two-piece strut fairing surrounding each of the struts, including: (i) an inner band; (ii) an outer band; and (iii) an airfoil-shaped vane extending between the inner and outer bands; (d) a plurality of nozzle segments disposed between the outer ring and the hub, each nozzle segment being an integral metallic casting including: (i) an arcuate outer band; (ii) an arcuate inner band; and (ii) an airfoil-shaped vane.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.