Thermal anti-icing of aircraft structures

Details Thermal anti-icing of aircraft structures Thermal anti-icing of aircraft structures

B - Operations, Transporting

64

D

B64D 15/04 (2006.01) B64D 33/02 (2006.01) F02C 7/047 (2006.01)

Patent

CA 2095530

2095530 9306005 PCTABS00021 An aircraft structural component comprises a forward compartment (17) formed by a forward bulkhead (19) and a skin structure (21) which extends forwardly of the forward bulkhead (17) and which has an outer surface which requires to be protected from accumulation of ice thereon, and a rear compartment (18) formed between the forward bulkhead (19) and a rear bulkhead (20). A supply duct (25) extends through the rear compartment (18) and into the forward compartment (17) for the delivery thereto of pressurised hot gases for distribution over the inner surface of the skin structure (21) to prevent accumulation of ice on the outer surface of the skin structure (21). A protective shroud duct (31) surrounds the supply duct (25), extends from the rear bulkhead (20) to the forward bulkhead (19) and forms an annular space between the protective shroud duct (31) and the supply duct (25). The annular space is closed off at its rear end at the rear bulkhead (20) and throughout its length within the rear compartment (18) by the protective shroud duct (31) and is open at its forward end to provide gaseous flow communication with the forward compartment (17), whereby leakage of hot gases from the supply duct (25) upon rupture are prevented by the protective shroud duct (31) from entering into the rear compartment (18) and pass into the forward compartment (17). A discharge duct is provided for discharging spent gases from the forward compartment (17) to atmosphere.

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