Gas turbine engine mid turbine frame with flow turning features
US8915090B2 · kind B2 · utility
4Cited by
19References
28Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Mar 21, 2014 |
| Grant date | Dec 23, 2014 |
| Priority date | — |
| Expiry date | Mar 21, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine includes first and second stages having a rotational axis. A circumferential array of airfoils is arranged axially between the first stage and the second stage. At least one of the airfoils have a curvature provided equidistantly between pressure and suction sides. The airfoils extend from a leading edge to a trailing edge at a midspan plane along the airfoil. An angle is defined between first and second lines respectively tangent to the intersection of the midspan plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.