Gas turbine engine inlet
US11480104B2 · kind B2 · utility
0Cited by
11References
11Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 26, 2014 |
| Grant date | Oct 25, 2022 |
| Priority date | — |
| Expiry date | Sep 20, 2038 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A gas turbine engine that includes a fan nacelle and a core nacelle that provide a bypass flow path radially between. The fan nacelle has an inlet including a throat. The inlet has an inlet forward-most point. A fan is arranged in the bypass flow path and rotatable about an axis. The fan has a leading edge recessed from the inlet forward-most point an inlet length in an axial direction. A spinner has a spinner length from a spinner forward-most point to the leading edge. A ratio of the spinner length to inlet length is equal to or greater than about 0.5.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.