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162 AIRCRAFT ENGINEERING June, 1932 A Selection of the More Important Aircraft and Engin e Specifications Published Recently '360,170 . Aircraft framework. Gloster cylinder walls ; the chamber 21 may cool th e valve nacelle A carried by a wing B. Airscrew A1 is Aircraft Co., Ltd., Folland, II. P., and Preston, guide ; the openings 23 may bo replaced by a mounte d forward of the leading edge and airscrew H . E., Gloster Works and Aerodrome, Hucclecote, continuou s annular slit; and the air directed on to A 3 is arranged so tha t the blades sweep through a Gloucestershire. Oct. 20, 1930, Nos. 31391/30 and th e valve head may be taken from th e chamber 21 . rearwardl y sloped gap B2 in the wing. The two 19078/31 . Addition to 223,971. [Class 4.] Also, the valve stem may be hollow and contain airscrews may bo driven by one engine. The gap Th e wing spar cooling-liquid. B 2 shown is limited in length, bu t may bo formed described in the b y constituting the wing by front and rear portions paren t specification staye d together, the front portion being arranged is modified by forward of and above the rear portion. In this 360,617 . Charging aircraft engines. arrangin g the cor arrangemen t the tips of several propellers may Armstron g Siddeley Motors, Ltd., and Viale, S. M., rugate d booms with ente r the gap so formed, in their separate circular Par k Side, Coventry. Oct. 15, 1930, No. 30838. thei r edge parts paths . [Class 7 (ii).] directed inwardly To reduce eddy loss, an air inlet pipe 11, which an d forming them extend s into the wit h Hat sides A6, air stream, conver B6 to scat the ges for a short dis stiffeners C, D and tanc e at 13, to a bracin g members neck 14, and then I, J, which are diverges to an area arrange d outside larger than that of th e booms and th e entrance 10 ; it formed as channel- ma y hav e tru e Ven- section struts with tur i form. As outwardl y directed shown, two parallel flanges. The stif 363,382 . Charging and scavenging ; start pipes 11 join a feners C, D have ing . Siemens & Halske Akt.-Ges., Siemensstadt, branche d pipe 12 Hanged pad pieces Berlin. Aug. 13, 1930, No. 24252. Convention whic h leads E1 fitted in their date , Aug. 30, 1929. [Classes 7 (ii) and 7 (v).] throug h a carburet ends , extensions E3 I n a two-stroke multi-cylinder engine in which . to r 4 to a supercharger 6. Each pipe 11 may be being formed on th e cylinders are scavenged and charged by the rectangula r in cross section and comprise opposed th e pad pieces for ejector action of the exhaust gases, the exhaust curved walls which may be hinged at their inner securing them to blocks G5, H5 fixed to bridge pipes are approximately of equal length and dis ends and adjustable between parallel flat walls to pieces G, H. The stiffeners and bracing members charg e a t a common point into a single manifold. regulate the air flow. Alternatively a circular ar e secured to the booms by hollow rivets F. I n the radial-cylinder engine shown in Fig. 2, the Venturi-shape d passage may be slidable axially Rivet s passed through distance tubes L strengthen individual exhaust pipes 2 discharge into a common in th e mouth. th e members C, D, and similar bracing may be manifold 4, the length of which may bo adjusted. placed across those booms tha t are in compression A t starting, compressed air is discharged into the a t points between their connections to th e stiffeners manifold through a nozzle 6, the supply of air C, D. The gauge of the metal may vary to suit being controlled by a valve (not shown) which 361,799 . Aircraft wing structures. Fedor, th e load on the girder; for example, one boom may also distributes air to the cylinders. In an aircraft J . P., 2117, Cherrywood Avenue, New Castle, be thicker than the other and the thickness or the engine, Fig. 4, air admission ports 32 face the Indiana , U.S.A. April 13, 1931, No. 10829. spacing of th e members C, D may be varied. The direction of travel, and the outlet of the exhaust [Class 4.] diagonal struts I, J may be fixed to the booms by pipe 35 is located in the upper part of the wing 30. An all-metal aeroplane wing having top and separat e connections instead of overlapping the botto m covering sheets, 1, 4, respectively, is pro member s C, D. vided with an internal structure comprising a numbe r of parallel I-beams 11 running the length of the wing, and a zigzag sheet brace 8 of approxi 360,382 . Valves. Junkers, H., 21, Kaiserplatz, matel y the length and width of the wing and Dessau, Anhalt, Germany. April 28, 1930, No. passing alternately over and under successive 13054. Convention date, May 23, 1929. Void I-beams, the whole being permanently secured [Published under Sect. 91 of the Acts]. [Class 7 together . The sheet brace 8 is formed with upper (vi).] an d lower flat portions 9 to engage the flanges of Valves are cooled by th e I-beams and diagonal portions 10 which con directin g air or gas uni stitut e zig-zag braces between the beams. The formly over the' outer front I-beam 5 has one flange extended and curved face of the valve. The upwardl y to brace the leading edge portion of the figure shows an exhaust to p covering 1. After assembly in the manner valv e 9 which is cooled shown th e contactin g part s are spot-welded together. b y air directed through openings 22 a t th e under side of an annular chambe r 20. Cooling ai r is also supplied to a 363,262 . Storing fuel on aircraft. Dornier chambe r 21 surrounding Metallbaute n Ges. and Dornier, C , Friedrichshafen, th e valve stem, and Lake Constance, Germany. April 14, 1931, No. passes ou t throug h open 11030. Convention date, May 5, 1930. [Class 4.] ings 23. The air ma y be A Hying boa t having lateral fins b has fuel tanks supplied from the scav c mounted within the fin stumps and conforming 363,130 . Modifying flow over aircraf t wings . enging-pum p 6 throug h pipes 18, 19, whic h may be closely to the shape of the fin walls. The tanks Blackbur n Aeroplane & Motor Co., Ltd., and fitted with controlling devices 33, 34. In modi ma y be separated from one another and from the Rennie , J. D., Seaplane Base, Brough, near Hull. fications, the chamber 20 may be formed in the fin walls b y elastic packing. Dec . 15, 1930, No. 37755. [Class 4.] Means for accelerating the flow of air in the boundar y layer of an aircraft wing comprise a gap * These abstracts of complete specifications of Patents recently passing from the underside of the wing to the published are specially compiled, by permission of H.M. Stationery Office, from abridgments which are issued by the Office classified uppe r side, above which a propeller shaft is arranged into groups. Sets of group abridgments can be obtained from in such a manner that the tips of the propeller th e Patent Office, 25, Southampton Buildings London, W.C.2, canno t project through the gap below the under- 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 surface of the wing, but are so arranged that air the full specifications can be obtained from the same address, is drawn through the gap from the lower to the price 1s. each. uppe r side. In one form, as shown in the Figure, Except where otherwise stated, the specification is unaccom airscrews A1, A3 are mounted at the ends of a panied by drawings if none is reproduced
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Jun 1, 1932
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