52 AIRCRAF T ENGINEERING February, 1935 A Selection of the More Important Aircraft and Engin e Specifications Published Recently 410,199 . Aircraft engine accessories. Faire y Aviation Co., Ltd., Cranford Lane, Hayes, Middlesex, and Forsyth, A. G., Venlaw, Burdon Lane , Cheam, Surrey. Sept. 17, 1932, Nos. 25936/32 and 3122/33. [Class 4.] A cooling system for aircraft engines is provided with a water-cooling radiator, 14 of such size as to effect adequate cooling under normal conditions an d a steam-condenser 17 which becomes operative unde r abnormal conditions, the condenser being located behind the radiator or incorporared in the wing or fuselage structure in known manner so tha t only the water-cooling radiator offers head resistance. Liquid and steam from the engine jacket s 10 pass by a pipe 11 to a steam separator 12 whence the liquid descends to the radiator and material , e.g. metal, and partly with non-rigid material, e.g. fabric. In one form, cross-bracing, 14, 15, 16 is arranged between the lower booms of two spars 10, 11 and ribs 12, 13 the portion of 17 of the upper surface is covered with metal and the remainde r of the wing surface is covered with fabric. In a modification, the bracing 14, 15 runs from one lower boom to the opposite upper boom of th e spars 10, 11 and the metal covering 17 extends to the trailing edge 18 of the wing. 411,965 . Driving aircraft propellers. Arm strong Siddeley Motors, Ltd., and Viale, S. M., Par k Side, Coventry. Jan. 31, 1933, No. 2967. In epicyclic gearing for transmitting the drive between an internal-combustion or other impulse engine and an aircraft propeller, the reaction ele men t is held against rotation by springs and auto matically forced axially by the propeller thrust to introduce damping between itself and a stationary member. As shown, the annulus 14 secured to the crankshaft 17 drives th e propeller shaft 12, which is rigid with the carrier 13, throug h the planets 19. Th e reaction sun 21 is in floating toothed engage men t with a sleeve 23 bolted to a drum 25 carrying spring-blades 26 engaging between teeth 27 on the casing 31. The propeller thrust urges the thrust- bearing 36 to the right, and thus through a flanged cylinder 38 forces the drum 25 into engagement with the friction surfaces 33, giving frictional dampin g in proportion to the thrust. Initial dampin g is produced by a brake 39 pressed against th e drum 25 by springs 40. stea m passes through a dome 15 to the condenser, which is preferably formed of two similar triangular part s 18, 19, Fig . 3. The water from the radiator is returned by a pump 24 to the jackets and the condensat e is delivered by a pump 21 back to the separator . In a modification, Fig. 4, a centrifugal stea m separator 26, as described in Specification 315007, is employed, and the condenser is constituted by headers 31 and conduits 32 in the wing surface. 410,750 . Aircraft planes. Bristol Aeroplane Co., Ltd. , and Pollard, H. J. , Filton House, Bristol. Nov . 19, 1932, No. 32750. [Class 4.] An aeroplane wing or like structure with internal diagonal bracing is covered partly with rigid * These abstracts of complete specifications of patents recently published are specially compiled, by permission of H.M. Stationery Office, from abridgments which are issued by the Office classified into groups. Sets of group abridgments can be obtained from the Patent Office, 25 Southampton Buildings, London, W.C.2, either sheet by sheet as issued, on payment of a subscription of 5s. per group volume, or in bound volumes at 2s. each. Copies of the full specifications can be obtained from the same address, price 1s. each. Except where otherwise stated, the specification is unaccom panied by drawings if none is reproduced.
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Feb 1, 1935