Aircraft turbine rear structures
US11230943B2 · kind B2 · utility
0Cited by
3References
19Claims
0Family size
Assignee
Inventor
Key dates
| Filing date | Nov 6, 2018 |
| Grant date | Jan 25, 2022 |
| Priority date | — |
| Expiry date | Nov 6, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A turbine rear structure for a gas turbine engine includes a central hub and a circumferential outer ring coaxial with the central hub. The turbine rear structure further includes a plurality of guide vanes extending radially between the central hub and the circumferential outer ring, and an intermediate guide vane located in a space defined between adjacent guide vanes. The intermediate guide vane is located closer to one of the guide vanes than the other guide vane.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.