Gas turbine engine mid turbine frame with flow turning features
US8424313B1 · kind B1 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 9, 2012 |
| Grant date | Apr 23, 2013 |
| Priority date | — |
| Expiry date | Feb 9, 2032 |
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 mid turbine frame is arranged axially between the first and second stages. The mid turbine frame includes a circumferential array of airfoils, and the airfoils each 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 plane and the curvature at airfoil leading and trailing edges. The angle is equal to or greater than about 10°, for example. In one example, an airfoil aspect ratio is less than 1.5.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.