Gas turbine engine nacelle having a symmetric flowpath
US9328662B2 · kind B2 · utility
1Cited by
16References
3Claims
0Family size
Assignee
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Key dates
| Filing date | Jul 1, 2009 |
| Grant date | May 3, 2016 |
| Priority date | — |
| Expiry date | Aug 15, 2034 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0536
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An initial geometry for a nacelle provides an intake at the upstream end of the nacelle and an exhaust at the downstream end of the nacelle. The intake has in flow series, an intake lip and a diffuser. The intake lip has a highlight defining the boundary between the inner and outer surfaces of the intake lip. On all longitudinal sections containing the axis of the engine (i) the inner and outer surfaces are tangency matched at the highlight, and (ii) the inner and outer surfaces have their maximum curvatures at the highlight.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.