March, 1932 AIRCRAFT ENGINEERING 81 A Selection of the More Important Aircraft and Engine Specifications Published Recently 358,377 . Multi-englned aeroplanes. Siemens modification the propeller is mounted on the engine pocket extends over both valves and the sparking- & Halske Akt.-Ges., Siemensstadt, Berlin. Dec. 29, shaft 20, Figs 3 and 4, which carries centrifugal plu g is nearer th e exhaust valve. The valves may, 1930, No. 39078. Convention date, Feb. 7. bobs 23 having frictional facings 27. The drive is however, be overhead or opposed, and the inlet [Class 4.] transmitte d from th e engine t o th e propeller through valv e may be in a part F1 closely approached by A n aero th e bobs 23 engaging a torque plate 28 and through th e piston. The roof F3 may be inclined or domed. plan e is drive n th e intermediary of springs 33 situated between Relativ e dimensions of the pocket H, to produce b y several projections on the torque plate 28 and a plate 32 th e desired damping effect on the turbulence, two-strok e secured to the propeller. are given. motor s scav- enged or 358,908 . Cylinders. Ricardo, H. R., 21, 359,530 . Fuel Injectors. Winton Engine Co., charge d by a Suffolk Street, Pall Mall, London. July 14, 1930, Wes t 106th Street, Cleveland, Ohio, U.S.A. single blower No . 21227. [Class 7 (ii).] Jul y 21, 1930, No. 22002. Convention date, 4 within the A combustion chamber D1 has Oct. 24, 1929. [Class 7 (iii).] fuselag e a portion D2, which has less I n a fuel pum p for an internal-combustion engine, drive n by an heigh t than the remainder and a tappet 33 for operating the bypass valve 21 independen t is such tha t th e clearance formed passes through the lever 27 operating the pump water-coole d thereb y comprises between 25 plunger 9. The tappet 33 is operated by one end engine 5 or, in an alternative construction, by a an d 40 per cent of the whole 31a of a lever 31, the other end 31b of which is blower 7 driven by an air-cooled engine 8. clearance. The sparking plug is operate d by the lever 27. The timing is adjusted placed at F in the centre of the b y means of a wedge 34, or, alternatively, by portion D2 which is asymmetri adjustmen t of an eccentric mounting of th e fulcrum 358,789 . Mounting and driving aircraft cal t o a plan e joining th e cylinder pin 32 of the lever 31. The stem of the valve 21 propellers . Junkers, H., 21, Kaiserplatz, axis an d a point midway between is made of large diameter, in order partially to Dessau, Anhalt, Germany. Dec. 2, 1930, No . 36318. th e valve axis, when the valves balance th e pressure on th e valve head. The stem 8 Convention date, Dec. 14, 1929. [Class 4.] ar e arranged side by side, or the of th e injection valve slides in a bore in th e plunger 9 Mechanism for the transmission of energy from valv e axis when the valves are an d is acted on by a spring 14 through a pin 10 engines or motors with periodically fluctuating opposed to one another. Speci an d head 11. The valve is opened by th e discharge torqu e to aircraft propellers includes an elastic fications 309,092 and 309,297 pressure. member interposed in the revolving transmission [Class 7 (ii), Internal-combustion mechanism and so dimensioned as to prevent engines, Arrangement etc. of], are referred to. resonance of th e specific frequency of th e revolving part s during fluctuations in the engine torque in 358,910 . Cylinders. Ricardo, H. R., 21, Suffolk Street, Pall Mall, London. July 14, 1930, No . 21229. [Class 7 (ii).] Th e cylinder clearance space is restricted to a trough-shaped chambe r c, seen in plan in Fig. 1, which extend s across th e cylinder bore to form a lateral pocket containin g one of the valves D1 ; the other valve is either opposite th e valve D1 or a t the othe r end of the chamber and th e sparking plug is a t F. In Fig. 5 the inlet and exhaust valves J, K are side by side and th e sparking plug M is between th e exhaust valve and the cylinder bore. 358,912 . Cylinders. Ricardo, H. R., 21, Suffolk Street, Pall Mall, London. July 14, 1930, No . 21231. [Class 7 (ii).] 359,892 . Aircraft win g structures. Navarro, A cylinder has a J . G., and Navarro, M. A,, 21, Berrylands Road, wedge - shaped com Surbiton, Surrey. June 27, 1930, No. 19664. bustion chamber C2 [Class 4.] an d inlet an d exhaust Aeroplane wings of the type having separately th e range of higher engine speeds, and a clutch in port s D, E arranged . constructe d leading and/or trailing edge portions th e transmission mechanism, in series with the as shown or inter and/o r wing tips have the ribs 2, Fig. 1, of the elastic member, said clutch having a slip-torque- changed , the spark centra l portion of the wing extending outwardly speed characteristic which follows approximately ing plug socket being beyond the longitudinal spars 1 an d the ribs 31, 41, th e same law as th e torque-absorbed-speed charac located at either M of the leading and/or trailing edge portions 3, 4, teristic of the propeller. In one form, the elastic or M1. member takes th e form of a long shaft 2, Figs. 1, an d 2, of low natural period of oscillation. The clutch 359,016 . Cylinders. Ricardo, H. R., 21, consists of cross-arms 11 mounted rigidly on the Suffolk Street, Pall Mall, London. July 14, 1930, engine shaft 10 and carrying radially displaceable No . 21232. [Class 7 (ii).] bobs 12 exposed to the action of centrifugal force Th e cylinder clearance and which are provided with frictional facings 13 space is comprised by a bearin g against a clutch plate 14 mounted on the lateral chamber F2 having shaft 2. Weak springs 15 produce an auxiliary a troughlike pocket H, initial pressure between the friction surfaces. In a containing the sparking- plug socket J, and com which may be of any desired width, extending * These abstracts of complete specifications of Patents recently prising a volume of be inwardl y beyond the spars 1, th e ribs of the several published are specially compiled, by permission of H.M. Stationery tween 10 and 25 per cent portions interpenetrating. The ribs 31, 41 are Office, from abridgments which are issued by the Office classified into groups. Sets of group abridgments can be obtained from of the whole clearance secured to the spars 1 and may if required be the Patent Office, 25, Southampton Buildings, London, W.C.2, space. The side walls H1 secured to ribs 2. The portions 3, 4 may be either sheet by sheet as issued on payment of a subscription of of the pocket are perpen separatel y assembled on longitudinal spars before 5s. per group volume, or in bound volumes at 2s. each. Copies of the full specifications can be obtained from the same address, dicular to the flat roof F3 attachmen t to the spars 1 or the ribs 31, 41, may prixce 1s. each. of th e chamber F2, and in be first secured and the outer covering applied Except where otherwise stated, the specification is unaccompanied a side-valve engine the when they are in position. by drawings if none is reproduced.
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Mar 1, 1932
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