2,518,854. Wing High Lift Flap Device. Benjamin W. Badenoch, Los Angeles, Calif., assignor to Doug las Aircraft Company, Inc., Santa Monica, Calif. Application June 14, 1943. These details and drawings of patents granted in the United States are taken, by permission of the Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, 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. 2,517,680. Flying Control for Aircraft. Henry Knowler, Ryde, and Frank Henry Robertson, Caris- brooke, Isle of Wight, England, assignors to Saunders- Roe Limited, East Cowes, Isle of Wight, England. Application November 29, 1947. In Great Britain October 7, 1946. 2,519,015. Sonic Air-Speed and Stall Indicator. Igor B. Bensen, Alplaus, N.Y., assignor to General Electric Company, a corporation of New York. Application November 23, 1948. A sonic airspeed and stall indicator adapted to be secured to the wing of an aeroplane comprising a leaf spring having one end adapted to be secured on the 2,516,909. Adjustable Jet Propulsion Nozzle for wing and its body resiliently responsive to airflow Gas Turbines. Arnold H. Redding, Swarthmore, Pa., over said wing, a reed having one end pivotally se and David W. Hutchinson, Mamaroneck, N.Y., cured to the movable end of said leaf spring and its assignor to Westinghouse Electric Corporation, East other free end directed into said air flow and arranged Pitsburgh, Pa., a corporation of Pennsylvania. Appli to be vibrated in response to said air flow, an electrical cation September 17, 1947. pickup adapted to be mounted on the wing adjacent In jet propulsion apparatus, a turbine, means said reed, a feeler tip on said pickup through which providing motive fluid for the turbine and including said reed passes freely, audio amplifying and repro a combustor furnished with fuel and supplied with ductive means electrically connected to said electrical air by a compressor driven by the turbine, a nozzle In an aircraft, the combination, with a pilot's pickup, and an audio frequency tone generator acting on the exhaust of the turbine to provide a pro control member and a control surface to be operated electrically connected to said amplifying means. pulsion jet, said nozzle including a component which thereby, of a torque shaft, an irreversible mechanical is movable to vary the nozzle exit area to vary the jet driving gear located adjacent the control surface for thrust, a speed governor operated by the turbine for imparting movement from the torque shaft to the controlling the supply of fuel to the combustor and control surface, a pair of variable speed power units, including speed-setting means, and mechanism for a differential gear coupling the power units to the adjusting the speed-setting means of the governor torque shaft, connections between the pilot's control and the movable component of the nozzle and in member and the power units for rendering the power cluding a member movable to adjust the governor units operative, on movement of the pilot's control speed-setting means to increase the fuel input to member, to move the control surface in a direction increase the turbine speed to maximum and then, and at a rate determined by the movement of the while maintaining the turbine speed at maximum, pilot's control member, means of terminating opera movable to operate the movable component of the tion of the power units on arrival for the control nozzle to reduce the nozzle exit area to increase the surface at a position, selected by the movement of the jet thrust. control member, and means for preventing reverse rotation of either power unit, should it fail, by the other power unit. 2,519,130. Compound Gas-Turbine Power Plant with Parallel Flow Turbines. Alan Arnold Griffith, Derby, England, assignor to Rolls-Royce Limited, Derby, England, a British company. Application July 29, 1946. In Great Britain April 23, 1945. A gas-turbine power-plant comprising a first axial- flow turbine; a first compressor coaxial with and driven by said first turbine and constituting the only 2,516,910. Gas Turbine Apparatus with Selective load therefor; a combustion chamber; an inlet duct Regenerator Control. Arnold H. Redding, Swarth connecting the discharge of said first compressor and more, Pa., assignor to Westinghouse Electric Corpora said combustion chamber; a first outlet duct con tion, East Pittsburgh, Pa., a corporation of Pennsyl necting said combustion chamber and the inlet of said vania. Application June 2, 1948. first turbine; a second axial-flow turbine coaxial with In a gas turbine power plant comprising casing but rotatable independently of said first turbine; a structure having an inner annular passageway com second outlet duct connecting said combustion municating with an air inlet and a discharge nozzle, chamber and the inlet of said second turbine; a low- a compressor disposed in said structure adjacent said pressure compressor coaxial with and driven by said 2,518,660. Internal-Combustion Engine and Ex- inlet, fuel combustion apparatus, a turbine responsive second turbine; and an intake for said first com haust Gas Turbine Therefor. Kenneth A. Browne, to flow of motive fluid from said combustion appara pressor arranged to receive air compressed by said Ridgewood, N.J., assignor to Wright Aeronautical tus for operating said compressor and normally low-pressure compressor. Corporation, a corporation of New York. Application adapted to exhaust directly through said nozzle, an September 7, 1944. outer annular by-pass formed in said casing structure In combination, an internal combustion engine, a for providing another communication for conducting turbine arranged to be driven by the engine exhaust exhaust fluid from said turbine to said nozzle, and gases, a multi-speed transmission drivably connecting annular heat exchange structure interposed in said said turbine to said engine, and speed responsive by-pass in thermal relation with a portion of said means automatically operative to decrease the turbine inner passageway in advance of said combustion to engine speed ratio when the speed of said turbine apparatus. exceeds a predetermined value. In combination, an internal combustion engine, a fan for supplying said engine with cooling air, a turbine driven by the engine exhaust gases for driving 2,519,624. Fuel Control System for Aircraft Gas- said fan, means drivably connecting said turbine to an Turbine Power Plants. David Havelock Ballantyne, engine auxiliary, and speed responsive means auto Littleover, and Albert Jubb, Buttersaw, Bradford, matically operative for varying the power required to England, assignors to Rolls-Royce Limited, Derby, drive said fan in order to regulate the speed of said England, a British Company. Application December turbine and engine auxiliary. 28, 1948. In Great Britain January 5, 1948. An aircraft having a gas-turbine power plant, a fuel-supply control system, a pressure-sensitive device in said system controlling the fuel flow to the turbine so that increase of pressure to which the device is 2,517,015. Combustion Chamber with Shielded subjected results in increase of fuel flow and decrease Fuel Nozzle. Frank C. Mock, South Bend, Ind., and of pressure in decrease of fuel flow, and a connextion Herbert H. Thurston, St Joseph, Mich., assignors to between said pressure-sensitive device and a point on Bendix Aviation Corporation, South Bend, Ind., a the external surface of the aircraft at which the corporation of Delaware. Application May 16, 1945. pressure decreases with increase of forward speed of Serial No. 594,006. the aircraft. 380 Aircraft Engineering
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Dec 1, 1950
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