GB562179A - Improvements in systems for heating the interior of aeroplanes and the like - Google Patents

Abstract

562,179. Heating aircraft. McCOLLUM, H. J. DE N. Oct. 28, 1942, No. 15153. Convention date, Oct. 3, 1941. [Class 64 (ii)] [Also in Group XI] A current of air passes, due to the motion of an aeroplane, into conduit 18, over a surface heater 10, through an air turbine 12 and conduit 16 into the cabin. Turbine 12 operates a blower 14 drawing combustible mixture from a carburetter 32 and delivering it through pipe 40 to a combustion chamber 38 provided with an electrical igniter 42. Combustion products pass through a finned heat exchanger 49 to exhaust pipe 46. The igniter 42 may be of the resistance type and is energized by a battery 50 through switch 52, 54 operated by the arm 60 carried by the control damper 58, and through thermal switch 56, 57 responsive to the heater 10. The damper 58 may be operated manually, or by thermostat responsive to the cabin temperature. Flow of air is regulated by damper 58, and the speed of the turbine 12 corresponds thereto, so that the combustible mixture is also regulated and overheating of the system is avoided. Closure of damper 58 opens switch 62, 54 in the ignition circuit. In a modification applicable to a supercharged cabin, air is delivered from the supercharger to the heater, which is also provided with a byepass conduit. The outlet from the heater, and the byepass, may be valve controlled to regulate the proportion of hot and cold air delivered.