Air intake for a turbojet engine nacelle
US12116931B2 · kind B2 · utility
3Cited by
1References
18Claims
0Family size
Assignee
Inventors
Key dates
| Filing date | Oct 26, 2021 |
| Grant date | Oct 15, 2024 |
| Priority date | — |
| Expiry date | Dec 22, 2041 |
Classification
- Technology area (CPC F)Mechanical Engineering; Lighting; Heating
- CPC primaryF05D2230/60
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An air intake of a turbojet engine nacelle includes an air intake lip, an annular structure, a rear partition, and at least one acoustic attenuation structure. The annular structure includes at least a part of an outer fairing and an inner fairing joined to each other by the air intake lip. The rear partition is connected to the inner fairing. The acoustic attenuation structure is attached to the inner fairing of the annular structure. At least part of the outer fairing, the air intake lip and the inner fairing are integral with each other.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.