Nacelle inlet thermal anti-icing spray duct support system
US7900872B2 · kind B2 · utility
Assignee
Inventor
Key dates
| Filing date | Dec 12, 2007 |
| Grant date | Mar 8, 2011 |
| Priority date | — |
| Expiry date | Sep 22, 2029 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D2033/0286
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An anti-icing system for an aircraft engine nacelle comprises a generally ring-shaped hollow spray tube for directing hot gasses toward a portion of the nacelle; a plurality of fasteners for attaching the spray tube to a support structure of the aircraft engine; and a supply duct for delivering the hot gasses from the aircraft engine to the spray tube. The spray tube includes two closed ends which define a thermal expansion gap therebetween to accommodate thermal expansions and contractions caused by the hot gasses. Each of the fasteners comprises a support bracket for attachment to the support structure of the aircraft and a guide assembly for supporting the spray tube to the support bracket. The guide assembly includes a generally ring-shaped block for encircling the spray tube, a bushing positioned within the block for contact with a bearing sleeve of the spray tube, and a pair of bushing retainers positioned on opposite sides of the block for retaining the bushing within the block. The bushings permit the spray tube to slip relative to the fasteners to further accommodate thermal expansions and contractions.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.