GB708046A - Multiple tube cooling device - Google Patents

Abstract

708,046. Cooling gases; tubular heat exchangers. GARRETT CORPORATION. June 25, 1951 [June 29, 1950], No. 30563/52. Divided out of 708,011. Classes 29 and 64(3) [Also in Group XXIX] Air or gas to be cooled is passed through banks of tubes 42, 43, 49, 57 in heatexchange relation with a coolant, and a valve 26 responsive to change in a condition affecting the density of the air or gas varies the quantity of tubes in action. The tubes 49, 57 are vortex tubes of the kind described in Specification 405,781. The tubes are arranged in a casing 11 and pressure air bled off the outlet of the jet engine compressor of an aircraft is supplied by a pipe 24 to a space 21 at one end of the casing and passes through the heat-exchange tubes 42, annular header 40 and heat-exchange tubes 43 to a space 18. Cooling air from the inlet of the compressor, which enters the casing at 36 and leaves at 38, as shown by the arrows 62, cools both the heat-exchange tubes 42, 43 and the vortex tubes 49, 57, which are of heat conductive material. From the space 18 the cooled compressed air passes to a dome 47 and to the tangential inlets 54 of the vortex tubes 49 which are continuously in operation. The ends 51 of the vortex tubes are closed and the cold air passes through a pipe 55 into the space to be cooled, e.g. the casing of an electric generator connected to the casing 11 by a fitting 56 with a clamping band 56a. The dome 47 communicates through a cylindrical slide-valve 26 with a space 16 divided into six sector-shaped chambers 34 by radial partitions 35 and the valve casing 25, shown developed in Fig. 4, has six openings 28 leading individually into the chambers 34 and spaced so as to be progressively opened by the cylindrical slide 27 of the valve. From each chamber 34 the cooled compressed air passes to the tangential inlets 54a of separate banks of vortex tubes 57 also cooled by the cooling air and closed at the ends 59, the cold air from these tubes issuing through pipes 61 to the fitting 56. The valve slide 27 is actuated by a bellows 30 so that as the aircraft rises more of the openings 26 are uncovered and more of the vortex tubes 57 brought into operation to compensate for the reduction of air flow through the individual tubes. Specification 708,011 also is referred to.