location of the root member with respect to the sup porting member and with respect to one sense of the direction of slidable relationship, one of the said members having a recess located intermediately of its opposite end faces, and means co-operating with the These details and drawings of patents granted in the United States are taken, by permission or the recess for preventing relative movement of the root Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies member with respect to the supporting member in the other sense of the direction of slidable relationship, of the full specifications can be obtained, price 25 cents each, from the Commissioner of Patents, which means includes a plate disposed between the Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, said members and having projecting tabs at opposite Southampton Buildings, Chancery Lane, London, W.C.2. edges, the plate having a thickened portion at which the opposite faces of the plate bear upon the said members, one of the tabs extending into the recess in 2,639,579. Turbo-Jet Engine having Tail Pipe the recessed member and the other of the tabs en Ejector to Induce Flow of Cooling Air. Andrew V. D. gaging an exposed face of the member not so recessed, Willgoos, deceased, late of West Hartford, Conn., by the said other tab being bendable at the margin of the Hartford National Bank and Trust Company of plate after assembly to so engage the said face. Hartford, Conn., executor, assignor to United Air craft Corporation, East Hartford, Conn. Original application June 21, 1949. Divided and this application, 2,641,902. Combination Ram-Jet and Turbo-Jct. August 4, 1951. John A. Kerr, Columbus, Ohio, assignor to Curtiss- In a gas turbine power plant, a turbine including a Wright Corporation. Application September 13, 1947. rotor and a surrounding casing, a housing surround A jet propulsion power plant comprising a ram-jet ing the casing, supporting means extending between engine and a turbo-jet engine; said ram-jet engine the turbine casing and the housing for supporting the comprising an open-ended duct-like member having casing within the housing, a thrust nozzle through a forwardly directed air entrance opening at one end which gas from the turbine is discharged, and an ex and a rearwardly directed exhaust nozzle at its other haust duct connecting the turbine to the nozzle, in end; said ram-jet engine also including means for tending from said hub structure and having an ex ternal configuration of aerofoil section, jet propulsion units mounted at the outer ends of the tip elements of the blades, and means to feed fuel to said jet pro pulsion units and including a reservoir carried by said hub structure and extensible connecting pipes extend ing from said reservoir through said blades to said units. 2,641,104. Tail Cone having Radially Adjustable Wall. John Y. Estabrook, Oak Ridge, Tenn., assignor to United Aircraft Corporation, East Hartford, Conn. introducing fuel into said duct-like member for com Application April 18, 1950. bustion therein in a zone intermediate the ends of said duct-like member, the ram-jet combustion gases discharging rearwardly through said nozzle to provide the power plant with substantial forward propulsive thrust; said turbo-jet engine being disposed at least combination with at least one radiation shield located substantially completely within said duct-like member between and spaced from the turbine casing and hous and having a forwardly directed air entrance opening ing and surrounding the casing, the downstream end at one end and a rearwardly-directed axially-extending of the shield being concentric to and closely spaced exhaust passage at its other end, the downstream end from the exhaust duct to define an ejector located of said exhaust passage opening co-axially into the within the duct upstream of the thrust nozzle and surrounding duct-like member upstream of said com communicating with the space between the shield and bustion zone so that the turbo-jet exhaust gases dis housing for maintaining a flow of cooling air there charge into said duct-like member and thence through through. the exhaust nozzle of said duct-like member to pro vide the power plant with substantial forward pro 2,640,320. Liquid Fuel liurner and Combustion pulsive thrust, said duct-like member being clear of A variable area thrust nozzle including a substanti Apparatus. John Stanley Clarke, Blacko, near Nelson, all 'rotable blades' exteriorly of said turbo-jet ally closed conical member having a base, a wall and a England, assignor to Joseph Lucas Limited, Birming engine. tip and adapted to be centrally mounted within the ham, England. Application April 17, 1950. In Great nozzle, and means for expanding the wall of said Britain May 23, 1949. member radially including means for moving the tip of the member in an axial direction with respect to the 2,642,237. Automatic Fuel Feed Control System base thereby causing radial expansion or contraction for Aircraft Power Plants. Frederick William Page, of the wall. Preston, and Stanley George Hooker, Derby, Eng land; said Page assignor to the English ElcctncCom- pany Limited, London, England, and said Hooker 2,641,443. Rotor Blade Locking. Peter Dennis assignor to Rolls-Royce Limited, Derby, England. Application March 17, 1947. In Great Britain Comcry, Cooksvillc, Ontario, and Joseph Thompson January 4, 1946. Purvis, North York Township, York County, On tario, Canada, assignors to A. V. Roe Canada Limited, Malton, Ontario, Canada. Application March 17, 1951. A locking device for a blade of a rotary power con version machine having a blade supporting member and blades provided with blade root members whereby they are demountably secured to the supporting mem ber, the said members each having exposed opposite end faces and being in slideablc relationship in a direction extending between the end faces and in inter locking relationship in another direction, comprising a stop element projecting from one and engaging the A liquid fuel burner comprising in combination a other of the said members to provide positive relative nozzle formed by a pair of coaxially arranged metal In an aircraft having a jet propulsion engine in plates and having an annular discharge orifice between cluding a fuel supply system, a control system for the peripheral portions of said plates, a supporting said fuel supply system comprising a Pitot tube shank on and extending axially from one side of one of mounted on said aircraft to be subjected to the Pitot said plates, a hollow boss on and extending axially pressure, and pressure-ratio-responsive means con from the other side of the last mentioned plate through nected to said fuel supply system, to said Pitot tube the other plate which is carried by said boss, and a and to a point on said aircraft subjected to the static vaporizing tube secured at one end to said hollow pressure of the ambient atmosphere and responsive boss. to the ratio of said Pitot pressure and said static pressure to reduce the flow of fuel supplied by said 2,640,549. Jet-driven Sustaining Propeller for Air fuel supply system whenever said aircraft attains a craft. Vittorio lsacco, London, England. Application selected Mach number irrespective of the individual August 3, 1946. In Great Britain August 3, 1945. values of said Pitot pressure and said static A sustaining propeller for flying devices, comprising pressure. a hub structure, blades of telescopic structure ex 328 Aircraft Engineering
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Oct 1, 1953
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