Diffuser for an annular combustion chamber, in particular for an airplane turbine engine
US7707834B2 · kind B2 · utility
7Cited by
7References
17Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Dec 23, 2005 |
| Grant date | May 4, 2010 |
| Priority date | — |
| Expiry date | Sep 21, 2027 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY02T50/60
- WIPO fieldEngines, pumps, turbines
- WIPO sectorMechanical engineering
Abstract
A diffuser for a single-head annular combustion chamber of an airplane engine, the diffuser comprising a separator formed by a thin sheet connected by structural arms to inner and outer circularly-symmetrical walls of the diffuser, the diffuser angle for each diffusion stream defined by the separator lying in the range about 12° to about 13°.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.