Gas turbine engine airfoil total chord relative to span
US9347323B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 17, 2015 |
| Grant date | May 24, 2016 |
| Priority date | — |
| Expiry date | Feb 17, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
An airfoil for a turbine engine includes pressure and suction sides that extend in a radial direction from a 0% span position at an inner flow path location to a 100% span position at an airfoil tip. The airfoil has a relationship between a total chord length and a span position and corresponds to a curve that has an increasing total chord length from the 0% span position to a first peak. The first peak occurs in the range of 45-65% span position, and the curve either remains generally constant or has a decreasing total chord length from the first peak to the 100% span position. The total chord length is at the 0% span position in the range of 8.2-10.5 inches (20.8-26.7 cm).
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.