Variable immersion lobe mixer for turbofan jet engine exhaust and method of fabricating the same
US9995245B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Apr 26, 2013 |
| Grant date | Jun 12, 2018 |
| Priority date | — |
| Expiry date | Mar 18, 2035 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49234
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A method of fabricating a mixer for a gas turbine engine is provided. The method includes forming a forward end and an aft end of the mixer, and forming an annularly undulating contour that defines a plurality of core immersion lobes and a plurality of bypass immersion lobes between the forward end and the aft end. The plurality of bypass immersion lobes includes a first bypass immersion lobe and a second bypass immersion lobe. The first bypass immersion lobe has a first crown contour line extending from the forward end to the aft end of the mixer, and the second bypass immersion lobe has a second crown contour line extending from the forward end to the aft end of the mixer. The first crown contour line is different than the second crown contour line.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.