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2,678,784. Aeroplane. Edward M. Lanier, Croydon, Pa., assignor to Lanier Aircraft Corporation, Newark, U.S. Patent Specifications N.J. Application December 23, 1948. In an aeroplane, an aerofoil having an upwardly and rearwardly directed Venturi passage extending These details and drawings of patents granted in the United States are taken, by permission of the through said aerofoil from its lower surface to its Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies upper surface, said passage having a large intake of the full specifications can be obtained, price 25 cents each, from the Commissioner of Patents, opening at the lower surface of said aerofoil and a Washington, D.C., U.S A. They are usually available for inspection at the British Patent Office, restricted jet opening at the upper surface of said aerofoil, a movable concave scoop pivoted to said Southampton Buildings, Chancery Lane, London, W.C.2. aerofoil and providing one wall of said passage, said concave scoop engaging the bottom surface of said 2,674,845. Diffuser Apparatus with Boundary aerofoil to form a closure for said Venturi passage, Layer Control. Walter D. Pouchot, Prospect Park, Pa., means for moving said concave scoop within said assignor, by mesne assignments, to the United States passage for varying the size of said Venturi passage of America as represented by the Secretary of the and projecting it beneath said lower surface of said Navy. Application May 2, 1951. aerofoil for directing air into said Venturi passage, a chamber in said aerofoil adjacent said restricted jet In a gas motivated power plant, substantially opening, an inwardly swinging rigid door hinged to cylindrical outer wall structure, inner fairing struc the upper surface of said aerofoil and normally lying ture having a rearwardly converging exterior surface in the same plane with the upper surface of said aero and coaxially disposed within said wall structure to foil and closing said jet opening and chamber and provide a rearwardly diverging annular diffuser pas means for variably moving said door into said chamber sage adapted to conduct a high velocity stream of gas under pressure, said fairing structure having formed therein an interior chamber and a plurality of bleed ports providing communication thereto from a down stream region of said diffuser passage having relatively large flow area, a plurality of radially disposed sup porting struts secured to said wall structure and to said fairing structure at points upstream of said bleed ports therein, at least one of said struts having an interior passage communicating with said chamber and exposing said jet opening to allow air to be pro in said fairing structure, and a plurality of discharge jected over said door upon opening said Venturi pas ports formed in each of said struts, said discharge sage by said scoop to decrease the air pressure on the ports being remote from said bleed ports and com bustion gases are discharged, means for varying the upper surface of said aerofoil. municating with said diffuser passage in an upstream area of said nozzle, and pressure-responsive means region of relatively small flow area, the differential controlling said nozzle area varying means including a housing having three chambers therein defined by 2,679,367. Trim Tab Control Mechanism. Richard interconnected diaphragms of different areas, three F. Pribil, Palos Verdes Estates, and Sanford Falbaum, pressure stations at spaced points along the gas path Hollydale, Calif., assignors to North American through said afterburner, one station located adjacent Aviation, Inc. Application March 28, 1950. the turbine end of said afterburner, another station In flutter prevention mechanism for high speed air located in the downstream portion of said after craft having a main aerofoil, a control surface pivotally burner, and the third station located between and mounted upon said aerofoil upon a spanwise extend spaced from said other stations, and a fluid connexion ing axis, a tab pivotally mounted upon said control between each of said chambers and one of said stations surface, a rockable actuating element pivotally so that nozzle area is controlled as a function of pres mounted within said control surface upon an axis sure ratio in said afterburner. extending in the direction of the thickness of said control surface, said rockable element having op 2,677,932. Combustion Power Plants in Parallel. posed pivotal connexions spaced in the direction of Bengt E. G. Forsling, Rugby, England, assignor to the axis of its pivotal mounting within said control General Electric Company. Application August 10, surface, said tab having opposed pivotal connexions spaced thereon in the spanwise direction and disposed Energy converting apparatus comprising a compres at either side of the pivotal mounting of said tab, sor having inlet and discharge passages, first and between static pressures of gas in the respective down second hot gas generating means connected in parallel stream and upstream regions of the diffuser passage flow relation to said compressor discharge passage, serving to effect withdrawal of boundary layer gas a first turbine connected in series flow relation to said away from the exterior surface of said fairing structure first gas generating means and connected in driving through said bleed ports, and return of such gas to relation to the compressor, a second turbine adapted the main gas stream by way of said discharge ports. for operation at rotational speeds independent of the rotational speeds of the first turbine and connected in series flow relation to said second gas generating 2,676,773. Aircraft Insulated Fuel Tank. Manuel C. means, fluid consuming means having an inlet open Sanz, Los Angeles and James Castelfranco, South ing connected to the compressor discharge passage Gate, Calif., assignors to North American Aviation, and in parallel flow relation with said gas generating Inc. Application January 8, 1951. means, and valve means at a location between the compressor discharge and the inlet to said second gas generating means and between said compressor dis a push-pull link pivotally connected to one of the charge and said fluid consuming means for varying pivotal connexions of said rockable element and to the relative proportions of the compressor flow re one of the pivotal connexions of said tab, a second ceived by said first and second gas generating means push-pull link connected to the remaining pivotal and said fluid consuming means, and conduit means connexion of said rockable element and to the other connecting said fluid consuming means in series flow In a supersonic aircraft which has fuel tanks integral of said pivotal connexions of said tab, said links being relation with said second gas generating means at a with said aircraft, a fuel tank comprising a liquid- disposed to extend in parallelism to each other sub location between the inlet to said second generating tight container whose outside surface is subject to stantially at right angles to the axis of pivoting of means and the downstream side of the valve means heat of friction due to flight of said aircraft through said rockable element, the said links being spaced from controlling the flow thereto, and bypass means con the atmosphere, a layer of porous material lining the each other in the direction of the axis of the rockable nected to said fluid consuming means for directing interior of said container, a liquid, said porous mate element, adjustment means associated with at least the flow to the atmosphere. rial immersed in said liquid, and a thin discontinuous one of said push-pull links arranged for pre-tensioning nonstructural sheet inside said porous layer for hold said links to reduce the clearance play within each of ing said porous material in place and for entrapping said pivotal connexions and mountings having axes vapour generated on the inside surface of said con extending in both the spanwise and thickness direc tainer to thereby contain said liquid while insulating it. tions of said control surface, said pre-tensioning limiting the deflexion play at the trailing edge of said 2,677,233. Exhaust Nozzle Switch Responsive to tab to not more than one per cent of the chord Afterburner Pressure Ratio. Donald J. Jordan, Glaston length of said tab, and an extensible actuating motor bury, Conn., assignor to United Aircraft Corporation, pivotally supported at a fixed terminal to said control East Hartford, Conn. Application June 30, 1949. surface with its mass supported beneath the pivotal mounting of said control surface and having a mov A jet engine including a compressor, a turbine able terminal pivotally connected to said rockable driving said compressor, a combustion chamber re element substantially beneath said control surface ceiving compressed air from the compressor and sup pivotal mounting for imparting controlled movements plying combustion gases to drive said turbine, an to said tab with respect to said control surface with afterburner receiving combustion gases from said freedom from flutter and oscillations at high speeds turbine and compressor and having mounted on its of the aircraft. downstream end a nozzle through which the com 270 Aircraft Engineering
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Aug 1, 1954
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