Gas turbine engine nacelle having a symmetric flowpath and design method thereof
US8985507B2 · kind B2 · utility
1Cited by
16References
8Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Feb 7, 2013 |
| Grant date | Mar 24, 2015 |
| Priority date | — |
| Expiry date | Feb 7, 2033 |
Classification
- Technology area (CPC Y)Emerging Cross-Sectional Technologies
- CPC primaryY10T137/0536
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
A method of designing a nacelle for a gas turbine engine includes defining an initial geometry for the nacelle, pivoting, at each of one or more positions on a highlight and in a plane of a respective longitudinal section, a front portion of a section of an intake lip lying in the respective longitudinal section about the highlight, and obtaining an altered geometry for the nacelle by adjusting surfaces of the intake neighboring the pivoted front portion to smoothly blend the surfaces of the pivoted front portion to unadjusted surfaces of the intake further removed from the pivoted front portion.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.