GB493107A - Improvements in the suspension and mounting of internal combustion engines or other engine units - Google Patents

Abstract

493,107. Mountings for aircraftengines. JULIEN, M. F. A., and PAULSEN, J. F. March 30, 1937, Nos. 9097 and 9098. Convention dates, March 28, 1936 and Feb. 24, 1937. [Class 4] [Also in Groups XXVI and XXXI] An aircraft, vehicle, boat, &c. engine is mounted on resilient supports 9 longitudinally arranged in groups, on either side of the engine, each support comprising rubber 12 adhering to a part 10 rigid with the engine and a part 11 rigid with the aircraft &c. body, the surfaces of these parts being normal to a plane which includes an axis passing through the centre of gravity of the engine and parallel to the crankshaft axis. In a modified form, the groups extend around the crank-shaft axis and are situated at the longitudinal extremities of the engine. Fig. 8 shows a resilient support which comprises a plate 10a fixed to the engine by a bolt and sleeve 17 and vulcanized to rubber 12a also vulcanized to plates 11 fixed to a frame 6. One plate 11 may be bent over to engage the other at each side. The member 10a may be in the form of a flattened tube. In Fig. 14, the engine is mounted by the resilient means 9a on circular frames 6a in front and at the rear of the engine and concentric with the axis passing through the centre of gravity of the engine and parallel with the crank-shaft axis. In Fig. 23, the resilient support comprises a central plate 43 having teeth 48 penetrating recesses in the outer plates 45 with a rubber strip 46 between them. These supports are arranged to have great rigidity in the horizontal plane and to allow freedom of movement in the vertical plane. Fig. 26 shows a cylindrical support having inner and outer grooved cylinders 49, 51 with a rubber strip 52 between. Specification 493,119, [Group XXXII], is referred to. The Specification as open to inspection under Sect. 91 also describes an arrangement of supports for radial engines, in one of which the surfaces are at right-angles to the crank-shaft axis and in another the supports are formed by rings of rubber at each end of the engine, coaxial with the crank-shaft. In the case of radial engines, the group 1 of supports at one end of the engine is joined by rods or U-shaped members passing over the cylinders to the group at the other end of the engine. In another modification, the engine is mounted by groups of supports on rings which themselves are mounted by groups of supports on the aircraft body. This subject-matter does not appear in the Specification as accepted.