GB130109A - Improvements in or relating to Radiators for Internal Combustion Engines. - Google Patents

Abstract

130,109. Cuau, C. Feb. 2, 1918, [Convention date]. Additior to 130,104. Plate apparatus.-The rigid internal borders of the hollow plate elements of radiators for aircraft described in the parent Specification are replaced by external folded strips 2<1>, Figs. 1 and 3, of comparatively thick metal, united to the thin walls 3 of the elements. The front and back edges of the elements are provided with tapered inlet and outlet chambers 8, 9, Fig. 3, (shown side uppermost) united to the walls 3 as shown in Fig. 17, and of triangular cross-section. The upper ends of these chambers have tubular extensions fitting into openings in inlet and outlet water boxes or headers 4, 5. and the lower ends 11, Fig. 3, of the rear chambers are connected to a common draining tube 12 of streamline form having a discharge plug 13 at each end. The outermost elements of a set have thicker outside walls 3<1>, Fig. 5, to resist shocks, and may be stiffened by open-ended hollow ribs 19. The elements may be protected at the bottom by a plate 17, Fig. 5, and may be covered at the top by a similar plate 18, and are spaced apart by top and bottom strips 16. The headers may be suspended by lugs 20 and brackets 22, Fig. 5, from longitudinal bearers 23, so that only the plates project into the path of the air current. The flow of water through the plates may be reversed by providing a partition 6 in the header and both inlet and outlet pipes 5<a> on the front header, but preferably the water inlet pipes 4a are arranged on the back header and the outlet pipes 5a on the front. Another method of supporting the radiator under the fuselage or under the wings of the aircraft is shown in Fig. 3. The headers are secured by straps 24 to cross bearers 25. Curved inlet and outlet pipes 4<a>, 5<a> are employed, and the headers may he fitted with pressure-gauge connexions 26 to enable the loss of head to Le ascertained. In a further arrangement, the ribs 28, Fig. 18, of the wing may be notched to receive the headers, which are secured by bars 29 detachably connected to lugs 30. Fig. 14 shows (side uppermost) an arrangement of elements especially adapted for aircraft of moderate speed, the elements being deep but narrow from front to back. The elements are fitted with distributing tubes 27 connected to headers 4, 5, both tubes and headers being of streamline form. The water flows vertically through the elements.