Patent GB-206819-A (GB)
Title: Improvements in or relating to radiators for aircraft or like motors
IPC: F28D1/03
Filed: 1923-09-26
Abstract: 206,819. Lamblin, A. Nov. 10, 1922, [Convention date]. Radiators, aircraft and like.-A series of parallel plate elements connected to juxtaposed headers are set in the direction of motion of the craft or vehicle with the headers at the rear or in front. The elements may consist of loops 4, Figs. 1 and 2, connected to a compound leader 1, 2 of stream-line shape divided into inlet and outlet chambers by a partition 3. The plates are spaced and stayed by side members 7 and an end member 8, the latter being hollow to serve as an air vent and overflow pipe. The loops may have sides tapering to the sides of the header. The plates may be without a central opening, as shown in Figs. 8 and 10, in which case flow and return paths for the water are provided by a narrow partition 24 in the centre of the plate. The thin walls 16, 17 of the plate are united by folding and pressing at the edges 18, and by hollow rivets 21. The partition 24 may be riveted and soldered in place, or the walls of the plates may be pressed and riveted together or folded and soldered at the centre to provide a baffle. The plates may be circular in shape, or tapering from the leading end. Another form of plate, shown in Figs. 17 and 18, comprises thin walls 16, 17 with a sheet 101 of paper, rubber, leather or other flexible material between them. This sheet of material is gripped between the folded edges of the metal walls, and is cut to provide washers around numerous hollow rivets 21, the washers being connected by strips 103. The Specification as open to inspection under Sect. 91 (3) (a) comprises also the following subject-matter :-Loop-shaped plates may be connected to separate headers at opposite ends of the plates, the headers being of tapered stream-line shape in cross-section. The headers may be shaped to complete the stream-line form of a spar or girder against which they are placed, for example a spar 42, Fig. 25 (Cancelled). A plate 41 is connected to the sides of the spar and the inner wall of the header is formed by a plate 43 shaped to fit the rounded edge of the spar. Means for controlling the flow of air over the plate elements may comprise shutters 35, Fig. 25 (Cancelled), pivoted to plates 37 mounted between the cooling-plates. The trailing parts of these pivoted shutters may be longer than the leading parts so as to assist in maintaining them in the set position when they are arranged parallel to one another in the direction of the air current. Such controlling-shutters may be applied to radiators generally, for example honeycomb radiators. Radiators having plates and headers as above described may be mounted in various positions on aircraft. As shown in Fig. 27 (Cancelled), a radiator is mounted between the front and rear members 52, 54 of the landing girder, the headers 56, 57 being shaped to complete the stream-line cross-section of the girder. Or the radiator may be mounted between the axles of the landing frame, between the landing frame and the fuselage, between inter-plane spans or struts, or on the leading edges of the planes. One arrangement of the radiator on the plane is shown in Fig. 34 (Cancelled). The divided header 1, 2 is formed in the edge of the plane 62 and the plates 4 are set vertically perpendicular to the edge of the plane. In another arrangement the loopshaped plates projecting partly above and partly below the plane are connected to a front header at the edge of the plane and a rear header located within the body of the plane. This subject-matter does not appear in the Specification as accepted.