GB505873A - Improvements in and relating to arrangements for preventing the formation of ice on aircraft - Google Patents

Abstract

505,873. Preventing formation of ice on aircraft. GROVES, W. W. (Junkers Flugzeug-und-Motorenwerke Akt.-Ges.) July 14, 1938, No. 20925. [Class 4] In means for preventing ice-formation on aircraft in which a gaseous or liquid heatcarrier is led into a chamber of large crosssection located inside the structure to be protected, e.g. a wing, strut, fin or rudder, and then passes along and in contact with the outer skin of the structure through one or more passages, the boundary walls of the chamber form at least part of the walls of the passages. In one form, Fig. 1, air is heated by passing it through aradiator 6 surrounding the exhaust pipe 3 and is led via a pipe 7 to chamber 8 extending along the entire wing span. The air then passes through an opening 9, formed along the front of the chamber, into passages 25 formed between the wing skin 10 and the walls 11 of the chamber, and finally escapes through openings in the rear part of the wing. The walls 11 may be formed by channel members, or . corrugated plates secured to the skin 10. In a second form, Fig. 5, which may also serve as a cooler for combustion air for a supercharged engine, air, heated, e.g. by passage through a blower or one stage of a multi-stage blower, enters a chamber 32 similar to the chamber 8 and passes via passages 33 into a second chamber 35 separated from the chamber 32 by a heat-insulating partition 36. The air then passes out via a pipe 37, e.g. to the carburetter or the next stage of the blower.