Method for defining the shape of a turbomachine convergent-divergent nozzle, and corresponding convergent-divergent nozzle
US9249755B2 · kind B2 · utility
Assignee
Inventors
Key dates
| Filing date | Feb 11, 2013 |
| Grant date | Feb 2, 2016 |
| Priority date | — |
| Expiry date | May 30, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T29/49826
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
According to the invention, the method for defining the shape of a convergent-divergent nozzle of longitudinal axis L-L comprising a convergent part connected, at a throat, to a divergent part the downstream free end of which comprises scallops delimiting noise-reducing chevrons distributed in the circumferential direction, comprises defining beforehand the divergent part of the nozzle using a divergent first portion, a divergent second portion and a convergent portion, attributing an initial value to dimensional parameters defining the chevrons and the three portions, calculating performance criteria and checking that the calculated performance criteria satisfy predefined performance conditions.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.