Access the full text.
Sign up today, get DeepDyve free for 14 days.
References for this paper are not available at this time. We will be adding them shortly, thank you for your patience.
the remainder of said compressor air to said com pressor turbine combustion chamber, the total supply of compressor air being sufficient to operate both tur bines under full load, and an exhaust gas duct from said compressor turbine extending straight aft be These details and drawings of patents granted in the United States are taken, by permission of the neath said wing, said compressor turbine being Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies bladed to pass a significant amount of energy into said of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, exhaust duct to produce a jet thrust. Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, Southampton Buildings, Chancery Lane, London, W.C.2. 2,523,579. Control of Aircraft. John Lloyd, sections, the one blade section of each blade being Coventry, England, assignor to Sir W. G. Armstrong disposed in alingment with one of said annular Whitworth Aircraft Limited, Coventry, England. discharge passages and its other blade section being Application July 30, 1947. In Great Britain October disposed in alingment with the other said annular 21, 1946. discharge passages. 2,527,245. Gyroscopically Controlled Gunsight. An aircraft of the kind having a tail plane, and Leslie Bennet Craigie Cunningham, Stanmore, and wings with ailerons which are substantially in line Howard Ford, Jeffery Walton Barnes, Ben Sykes, with the centre of gravity of the aircraft, comprising Maurice Hancock, and Bernard Wheeler Robinson, a main control, a planetary gearing including two Farnborough, England; Barclays Bank Limited, coaxial shafts, a driving connection between each said London, England, administrator of said Cunning shaft and a respective aileron, a gear fast with each ham, deceased, assignors, by mesne assignments, to said shaft, a planet carrier, a planet gear rotatable in Ferranti Limited, Hollinwood, England, a company said carrier and intermeshing said shaft gears, and a of the United Kingdom of Great Britain and Northern connection between said carrier and said main Ireland. Application March 17, 1944. In Great control which does not restrain rotation of said planet Britain August 22, 1942. gear on its axis, whereby an operation of the main In a predictor gunsight, adjustable means for de control merely tilts the axis of said planet gear to fining a sighting line, a gyroscope having a spindle, rotate the carrier about the axis of said shafts for means operatively connecting said spindle to said moving the ailerons differentially, the rotative support adjustable means for actuating the same, an electric of said planet gear permitting non-differential move ally conducting member mounted on the spindle to ment of the ailerons in response to sudden changes spin with the gyroscope and offset along the spin axis of incidence of the air stream thereon without com of the same, a symmetrical group of magnetic pole municating a reaction force to said main control. pieces arranged in pairs at either side of said electric ally conducting member to impose an eddy current drag on said conducting member and thereby on the rotation of the gyroscope, coils associated with at least one pair of said magnetic pole pieces, whereby 2,526,929. Aeroplane Flap Extension. Robert W. the pole strengths of said pole pieces may be modified, Bowcott, Columbus, Ohio, assignor to Curtiss- gun means with which said group of pole pieces is fast Wright Corporation, a corporation of Delaware. whereby when the gyroscope is spinning and the gun Application May-29, 1948. means is moved the eddy current drag applies a In an aircraft having a body with a substantially couple about an axis perpendicular to the gyroscope upright and curved side surface, a first airfoil extend spin axis which is therefore constrained to follow the ing from said body in a spanwise direction and having movement of the gun means with a lag dependent on an auxiliary airfoil mounted thereon for extension the angular velocity of movement of the gun means, from one edge thereof in a direction generally longi and an electrical computing network for supplying tudinal of the aircraft, the end of said auxiliary airfoil variable currents to said coils associated with said adjacent said surface moving in a path which diverges pole pieces to modify the orientation of the gyroscope from said surface as the auxiliary airfoil is extended, spin axis in accordance with ballistic requirements. the combination therewith comprising: a member for 2,525,782. Shock Wave Trap for Multiple Com telescoping movement with respect to said auxiliary bustion Chamber Reso-Jet Motors. James Y. Dunbar, airfoil in a direction generally spanwise of the latter, United States Navy. Application August 2, 1945. said member projecting beyond said end of the auxili A reso-jet motor comprising combustion chambers ary airfoil and having rollers on the projecting end each having an air-inlet opening, a housing forming thereof for engaging and rolling upon said surface as a shock wave trap affixed to the said combustion the auxiliary airfoil is moved. chambers communicating with the said air-inlet openings, an air-inlet affixed to the said housing, and a baffle within the said housing disposed between the air-inlet openings of the said combustion chambers for directing the air from said air inlet in the housing into said combustion chamber air-inlet openings. 2,527,732. Braking Device for Aircraft Jet Turbo- propellers. Roger Jean Imbert, Paris, France, assignor to Société Rateau (Societe Anonyme), Paris, France, a company of France, and Rene Anxionnaz, Paris, France. Application January 14, 1947. In. France 2,526,281. Turbine and Turbine Nozzle Construc February 7, 1946. tion. Thomas M. Ryan, Paramus, and Walter J. In a jet turbo-propeller system, the combination of a Romlein, Nutley, N.J., assignors to Wright Aero rear gas engine; combustion means for generating hot nautical Corporation, a corporation of New York. gas, connexions to feed said turbine for operating the Application April 10, 1947. same; front means coupled with said turbine so as to In a turbine power plant; a pair of ducts for sup be driven therefrom for compressing air, connections 2,526,941. Gas Turbine System for Aircraft plying motive fluid to the turbine rotor, said ducts to deliver part of compressed air to said combustion Propulsion. Meyer Fishbein, Los Angeles, Calif., having annular discharge passage portions disposed means; adjustable means, providing a passage-way assignor to Northrop Aircraft, Inc., Hawthorne, one within and immediately adjacent to the other, from said compressing means to discharge the re Calif., a corporation of California. Application June each said duct also having a tubular passage portion mainder of said compressed air at the rear of said tur 10, 1948. and an intermediate passage portion serially connect bine; and second adjustable means extending from the ing and providing a smooth transition between its In an airplane propelling system, a combustion gas first adjustable means in a generally forward direction, power turbine located adjacent the trailing edge of a annular and tubular passage portions, each of said for venting at least a portion of said air remainder to wing of said airplane, a pusher propeller mounted duct passage portions extending substantially parallel atmosphere. behind the trailing edge of said wing and connected to the axis of said annular passage portions with the by a shaft to said power turbine, a power turbine com tubular passage portions of said ducts being disposed bustion chamber connected to said power turbine, an on diametrically opposite sides of said axis; and air compressor located adjacent and below the leading blades on said rotor adapted to receive motive fluid from the annular discharge passage portions of said edge of said wing and directly connected to a com ducts for imparting rotation to said rotor, each of said pressor turbine, a compressor turbine combustion turbine blades having a laterally extending flange chamber connected to said compressor turbine, means intermediate its ends such that said flanges define for supplying part of the compressor air to said power an annular rim separating each blade into two turbine combustion chamber, means for supplying 60 Aircraft Engineering
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Feb 1, 1951
Access the full text.
Sign up today, get DeepDyve free for 14 days.