Thermal anti-icing of aircraft structures
US5400984A · kind A · utility
Assignee
Inventors
Key dates
| Filing date | Aug 16, 1993 |
| Grant date | Mar 28, 1995 |
| Priority date | — |
| Expiry date | Aug 16, 2013 |
Classification
- Technology area (CPC B)Performing Operations; Transporting
- CPC primaryB64D2033/0286
- WIPO fieldTransport
- WIPO sectorMechanical engineering
Abstract
An aircraft structural component comprising a forward compartment formed by a forward bulkhead and a skin structure which extends forwardly of the forward bulkhead and which has an outer surface, and a rear compartment formed between the forward bulkhead and a rear bulkhead. A supply duct extends through the rear compartment and into the forward compartment for the delivery thereto of pressurized hot gases for distribution over the inner surface of the skin structure. A protective shroud duct surrounds the supply duct, extends from the rear bulkhead to the forward bulkhead and forms an annular space between the protective shroud duct and the supply duct. The annular space is closed off at its rear end at the rear bulkhead and throughout its length within the rear compartment by the protective shroud duct and is open at its forward end for gaseous communication with the forward compartment. A discharge duct extends from the forward compartment to atmosphere.
Source: USPTO / EPO open patent data. Objective bibliographic and citation counts.