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container, an apron therein, a parachute pack holding a main parachute, means for opening up said pack, said parachute pack normally resting on said apron, timing mechanism for releasing the drogue shackle from the slip member, connexions between the drogue These details and drawings of patents granted in the United States are taken, by permission of the shackle and the face screen, the apron, and the main parachute pack, said connexions being operative Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies when the drogue shackle is released from the slip of the full specifications can be obtained, price 25 cents each, from the Commissioner of Patents, member to release the face screen, to straighten the apron so as to eject the parachute pack from the con Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, tainer, and to open up the parachute pack to with Southampton Buildings, Chancery Lane, London, W.C.2. draw the main parachute therefrom, and means also operative on the freeing of the drogue shackle to release the scat harness, the pilot thus being freed entirely from the scat to enable him to make a normal parachute descent. 2,705,867. Engine having a Rotor with a Plurality landing wheel mounted upon said spindle for rotation of Circumferentially-spaced Combustion Chambers. relative to said leg, said wheel being annularly re Robert B. Lewis, Glen Rock, N.J., assignor to Curtiss- cessed at its side which faces the leg, and provided 2,708,556. Aircraft Gust Damper. C. B. Smith and with a rim and a hub defining the radial outer and Wright Corporation. Application June 30, 1949. J. Goldsmith, assignors, by mesne assignments, to inner limits of said recess, brake plate structure posi Chance Vought Aircraft, Inc. Application November A power plant comprising a rotor having a plurality tioned within the wheel's recess and comprising an 23, 1951. of circumfercntially spaced combustion chambers; a inner annular plate attached to said hub and extending stator having an air intake port and a pair of exhaust radially outward therefrom and an outer annular plate In a lift control device for an aerofoil, the aerofoil ports disposed so that upon rotor rotation said air attached to the rim of the wheel and extending radially having upper and lower surfaces, a trailing edge fixed intake port communicates sequentially with said inward and coplanar with said inner plate and spaced to said surfaces and having a curved configuration, chambers at one of their ends and each of said exhaust' therefrom thereby forming an annular slot between ports communicate sequentially with said chambers at said plates, a friction pad located within the wheel's their other ends; means for adding fuel to said cham recess, at the side of the annular plates opposite said bers; and means for initiating combustion within said leg, for co-operation with said annular plates and guided for shifting in a direction parallel to the axis of the wheel and spindle into and from frictional braking engagement with said annular plates, a fluid pressure cylinder mounted directly upon the leg with the axis located radially outward of the wheel's rotative axis, a plurality of openings in said trailing edge, means for parallel to that rotative axis and extending inter inducting air through said openings from said surfaces mediate said annular plates and through said slot including suction means and a common duct leading formed between them, a piston shiftable axially within to said openings, a flap means in said duct and co said cylinder and a stem extending from the piston and operating with said openings and movable relative to between said spaced apart inner and outer annular said trailing edge openings to adjust the relative plates and through the annular slot formed between amount of air flow inducted from each of said sur chambers; the relative circumferential positions of them, said stem being operatively connected to said faces, sensing means located upstream of the aerofoil said ports and the point of combustion initiation friction pad, to shift the latter as stated, in accordance and predeterminately positioned relative to the aero within said chambers being such that during rotor with the position of the piston within its cylinder. rotation and after combustion in a chamber, said foil for detecting variations in relative angle of the chamber, cyclically and in the sequence stated, is oncoming airstream, and means operatively con placed in communication with one of said exhaust necting said sensing means and flap means for repo ports, is closed to said one exhaust port, is placed in sitioning the latter in response to variations in the communication with the other of said exhaust ports, is angle of the airstrcam. placed in communication with said intake port, is closed to said other exhaust port, is closed to said in take port, and thereafter combustion is initiated in 2,708,564. Turbine Apparatus. J. W. Erickson, said chamber while it is closed to all of said ports, the assignor to Westinghouse Electric Corporation. Appli overlap between said intake port and said other ex cation February 29, 1952. haust port being sufficiently large so that in each said cycle each said chamber is simultaneously in com In a turbine, a hollow rotor, means forming a path munication with said intake port and said other ex for hot motive fluid about said rotor, means for trans haust port for a length of time substantially longer mitting a cooling fluid through said rotor, and a than the length of time said chamber is in com plurality of radially extending blades mounted on munication solely with either of said latter two ports. said rotor, each of said blades comprising a vane portion disposed outwardly of said rotor in the path 2,706,889. Combustion Chambers of Gas Turbine of hot motive fluid and a root portion extending into Engines. Sidney Allen and Morris A. Stokes, Coven said rotor in heat exchange relation with said cooling try, England, assignors to Armstrong Siddeley Motors fluid therein, said vane and root portions having a Limited, Coventry, England. Application July 19, closed chamber formed therein, tubular baffle struc ture disposed in said chamber in coaxial relation with 2,708,083. Ejection Seats for Aircraft. J. Martin. said blade, said baffle structure having openings For use with a combustion chamber in which a Application August 23, 1952. Application Great formed in the opposite ends thereof and louvres vapour is adapted to be ignited, a J-like pipe adapted Britain September 7, 1951. The combination in an ejection scat for aircraft having an ejection gun operating between the scat and a fixed part of the aircraft to eject the seat therefrom, seat harness, a face screen attached to the scat, a droguegun and a drogue connected thereto, of a slip member fixed t o the scat, a drogue shackle attached to a drogue line secured to the drogue, said drogue shackle being normally retained in the slip member, means for holding the face screen in position, means for releasing said holding means, a parachute pack to be positioned within the combustion chamber and having an inlet portion and an outlet portion disposed in substantially parallel spaced apart relation to one another, said inlet portion having an inlet opening at one end for receiving a supply of air and fuel, said outlet portion having a discharge opening at one end adapted to discharge the air and fuel mixture into the formed therein intermediate said ends, said end open combustion chamber, said pipe also having a sub ings and said louvres operatively connecting said stantially straight portion connecting the other ends of chamber and the interior of said baffle, and a quantity the inlet and outlet portions. of material having a high boiling point disposed in said chamber, said material being adapted to become 2,707,604. Aircraft Alighting Gear and Braking vaporized by absorption of heat in the portion of said Mechanism for the Wheel or Wheels Thereof. George chamber in said vane portion, said vaporized material H. Dowty, Cheltenham, England, assignor to Dowty being condensed upon flow into the portion of said Equipment Limited, Cheltenham, England. Applica chamber within said root portion owing to dissipation tion March 30, 1951. of heat into said cooling fluid passing through the rotor, whereby each of said blades is maintained An aircraft alighting gear comprising a main sup resistant to the heat of the turbine motivating fluid. port leg, a transverse spindle carried by said leg, a 356 Aircraft Engineering
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Oct 1, 1955
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