GB565531A - Improvements in power plant for aircraft - Google Patents

Abstract

565,531. Heating aircraft. MACKIRDY, W. Dec. 3, 1942, No. 17226. [Class 64 (ii)] [Also in Groups XXVI and XXXIII] A power plant for an aircraft comprises one or more internal-combustion engines 10, and one or more other type heat engines 11 driven by a gas, such as carbon dioxide, which is heated by the exhaust, and cooling medium, of the internal-combustion engines. The engines 11 may have valve gear &c. to allow them to operate as internal-combustion engines, at low altitudes, and as heat engines using the Rankine or Carnot cycle, at high altitudes. All the engines drive propellers. An additional engine 12 is used to drive auxiliaries such as electric generators, air compressors, &c., and heat engines 28, 29 drive acompressor 36 (for the carbon dioxide), and a pump 16 (for the liquid carbon dioxide) respectively. When the engines 11 operate as second type heat engines, the working fluid passes through a closed circuit. Air for the internal-combustion engines passes through a heat-exchanger 14, supercharger 26 (driven by a turbine 27) and cooler 46 through lines 15. Fuel is supplied through conduits 31. The CO2, or other gas, passes through heat exchangers 17, 18, where the incoming CO2 is heated, before entering the compressor 36 and heat-exchanger 14, where the C02 is liquified. The incoming C02 passes through pipes 19 to a main heat-exchanger 20 heated by exhaust gases from the internal-combustion engines passing through pipes 21. The heated CO2 passes through pipes 22 to the engines 11 and other prime movers. Heat from the cooling jackets of the engines 10 may be utilised in the heat-exchanger 17, the liquid afterwards passing to a radiator 24. The compression ratios of the compressor 15 and pump 16 may be adjustable. The exhaust gas from the engines 10 may be used in heaters 30 for preventing ice formation on various exposed surfaces of the aircraft. The heat-exchanger tubes 31, 32 (see Fig. 3) may form part of the structure of the walls of the fuselage, which may be of the pressure-cabin type. The helices of the tubes are joined by webs 33 and have coverings 34, 35. The fluids in the tubes flow in opposite directions. The tubes and webs may be cast from light alloy to form a structure which is attached to the fuselage by brackets. Air for the pressure-cabin may be obtained from the conduit between the supercharger and the air cooler. Specification 565,560 is referred to.