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U.S. Patent Specifications

U.S. Patent Specifications 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 25 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. 2,650,047. Variable Camber Wing. Nathan A. between said turning vanes and downstream of the Carhart and Eliot F. Stoncr, Los Angeles, Calif., 50 per cent chordwise location of said turning vanes assignors to Douglas Aircraft Co. Inc., Santa Monica, and terminating in vortex producing tips adjacent the Calif. Application January 22, 1949. common surface between the main and boundary layer streams for intermixing fluid particles having varied of America, Philadelphia, Pa. Application July 29, energy levels between said streams, adjacent fins hav­ 1946. In Great Britain August 1, 1945. ing their chords oppositely inclined relative to the axis of flow of the main stream whereby adjacent A rotary-wing aircraft having three sustaining counterrotating vortices are produced. motors with separate axes defining the vertices of a triangle in plan, the centre of gravity of the aircraft being toward the centre of said triangle, the axes of 2,650,781. Boundary Layer Control for Aircraft. two of said rotors being in lateral side-by-side rela­ Harlan D. Taylor, Manchester, Conn., assignor to tion, one on each side of the longitudinal vertical United Aircraft Corporation, East Hartford, Conn. plane of the craft, and the axis of the third of said Application August II, 1950. rotors being substantially in said plane, each of said In an aircraft having a fuselage and a wing, said rotors having collective pitch varying means; and a wing forming external upper and lower major sur­ control system including a control member mounted faces and terminating in a free tip which produces a with freedom for movement in two senses, and linkage tip vortex during flight, suction means in said wing interconnecting said member and said pitch varying for taking off boundary layer air from an external means responsive to movement of the member in the surface of the wing comprising an unobstructed, im­ first of said senses to operate the pitch varying means perforate, fluid-tight duct in said wing communicating of said two sidc-by-sidc rotors in opposite directions In an aerofoil construction that includes a main at one end with an opening in said external surface for controlling roll, and responsive to movement of and terminating at the other end in a rcarwardly aerofoil portion and a semi-floating droopable section said member in the second of said senses to operate facing opening at the trailing edge of said wing tip, flexibly suspended at its upper inner surface by an the pitch varying means of said two rotors in the same integral flexible portion thereof from the adjacent direction and simultaneously operate the pitch varying surface of the main aerofoil portion; means for posi­ means of the third rotor in the opposite direction for tively and pivotally supporting said section for down­ pitching control of the aircraft, wherein at least one wardly rcflexing same, comprising: a support attached of said rotors has a mounting providing for tilting of at one end to, and projecting longitudinally from, the the rotor whereby to effect trimming of the aircraft main aerofoil portion; a link disposed between the without utilizing the pitch varying means. unattached end of the support and the upper inner surface of said section and pivotally connected at its ends to the support and to said section; and an 2,651,913. Gas Turbine Combustion Chamber. actuating member for reflcxing said section pivotally Grant B. Hodgson, San Diego, Calif., assignor to attached to the lower adjacent surface of said section, Solar Aircraft Company, San Diego, Calif. Applica­ the aforesaid pivot points together defining a tri­ tion March 13, 1951. angular truss-like structure having rigid sides dis­ whereby suction in said duct is produced by the low In a gas turbine combustion chamber structure posed under the flexible portion of said aerofoil con­ pressure developed at the core of said tip vortex comprising a cylinder of substantially uniform dia­ struction, said sides being pivotally adjustable by the during movement of the wing in flight. meter having an outlet and adapted for direct con­ actuating member into positions defining a scries of nexion with and to form a coaxial prolongation of the triangles taking all the stresses in all positions of said inlet end of a turbine scroll, a closure head secured flexible portion except those due to flexure of the 2,651,178. Combination Injector and Stabilizer for on the remote end of said cylinder, and means in the latter and to aerodynamic forces. Gas Turbine Afterburners. Frederick Denison Morgan cylinder wall adapted for connexion to a source of Williams, Weston, Ontario, Canada, assignor to compressed air: a fuel and air mixing head mounted A. V. Roe Canada Ltd., Malton, Ontario, Canada. on said cylinder closure head and comprising an 2,650,752. Boundary Layer Control in Blowers. Application January 18, 1951. annular rear section having a central inwardly directed Henry H. Hoadlcy, Manchester, Conn., assignor to depression, a fuel injector in said central depression, United Aircraft Corporation, East Hartford, Conn. a convergent annular wall extending generally axially Application August 27, 1949. from the periphery of said annular section, and a In combination, a fluid confining duct, a rotatable fluted divergent skirt the alternate flutes of which fan, means supporting said fan from the wall of said form passage means therein for deflecting air in a duct, said fan including a hub and a plurality of plurality of streams into said head and toward said blades, said blades having root sections and main fuel injector, said air thereby entraining fuel and sections terminating in tips adjacent the wall of said thereafter flowing successively over said rear section duct, a streamlined body forward of said fan for and being discharged in a convergent stream from directing a fluid stream in said duct around said hub said convergent section. and through said blades, turning vanes fixedly sup­ A fuel and air mixing head for a combustion cham­ ported from the wall of said duct and connected to ber comprising an end section of generally dished said body, means for increasing the overall efficiency shaped cross-section and having a central opening; of said propeller including a plurality of fins of aero­ An afterburner for a gas turbine engine, com­ a fuel nozzle secured in fluid tight relation in said foil shape carried by said body and the duct wall and prising a combustion chamber defined by an outer central opening; and inwardly and axially extending exposed to the fluid stream, said fins being located wall providing a duct through which a stream of gas section secured to the rim of said end section and is caused to flow, a hollow injector tube in the duct for providing a restricted throat opening; and a divergent injecting fuel into the combustion chamber, the in­ skirt portion secured to the free end of said inwardly jector tube being disposed with its longitudinal axis and axially extending section and having in its external parallel to the stream of gas and having open ends face outwardly opening, annularly spaced passages providing a fuel jet at each end, the jet at the down­ terminating at said throat opening and adapted to stream end of the tube being an auxiliary jet dis­ supply air interiorly of said head through said throat charging in a downstream direction and the jet at the opening. other end of the tube being a main jet discharging in an upstream direction, a baffle connected to and sur­ rounding the injector tube at a location upstream of the auxiliary jet and extending away from the in­ jector tube into the stream of gas to protect the auxiliary jet from the gas stream, igniting means for the auxiliary jet, and means for supplying fuel from a remote source to the injector tube. 2,651,480. Multiple Rotor Helicopter. Cyril George Pullin, Tadburn, Ampfield, Hampshire, England, assignor, by mesne assignments, to Autogiro Company :-.:iary 1954 31 http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

U.S. Patent Specifications

Aircraft Engineering and Aerospace Technology , Volume 26 (1): 1 – Jan 1, 1954

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032387
Publisher site
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Abstract

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 25 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. 2,650,047. Variable Camber Wing. Nathan A. between said turning vanes and downstream of the Carhart and Eliot F. Stoncr, Los Angeles, Calif., 50 per cent chordwise location of said turning vanes assignors to Douglas Aircraft Co. Inc., Santa Monica, and terminating in vortex producing tips adjacent the Calif. Application January 22, 1949. common surface between the main and boundary layer streams for intermixing fluid particles having varied of America, Philadelphia, Pa. Application July 29, energy levels between said streams, adjacent fins hav­ 1946. In Great Britain August 1, 1945. ing their chords oppositely inclined relative to the axis of flow of the main stream whereby adjacent A rotary-wing aircraft having three sustaining counterrotating vortices are produced. motors with separate axes defining the vertices of a triangle in plan, the centre of gravity of the aircraft being toward the centre of said triangle, the axes of 2,650,781. Boundary Layer Control for Aircraft. two of said rotors being in lateral side-by-side rela­ Harlan D. Taylor, Manchester, Conn., assignor to tion, one on each side of the longitudinal vertical United Aircraft Corporation, East Hartford, Conn. plane of the craft, and the axis of the third of said Application August II, 1950. rotors being substantially in said plane, each of said In an aircraft having a fuselage and a wing, said rotors having collective pitch varying means; and a wing forming external upper and lower major sur­ control system including a control member mounted faces and terminating in a free tip which produces a with freedom for movement in two senses, and linkage tip vortex during flight, suction means in said wing interconnecting said member and said pitch varying for taking off boundary layer air from an external means responsive to movement of the member in the surface of the wing comprising an unobstructed, im­ first of said senses to operate the pitch varying means perforate, fluid-tight duct in said wing communicating of said two sidc-by-sidc rotors in opposite directions In an aerofoil construction that includes a main at one end with an opening in said external surface for controlling roll, and responsive to movement of and terminating at the other end in a rcarwardly aerofoil portion and a semi-floating droopable section said member in the second of said senses to operate facing opening at the trailing edge of said wing tip, flexibly suspended at its upper inner surface by an the pitch varying means of said two rotors in the same integral flexible portion thereof from the adjacent direction and simultaneously operate the pitch varying surface of the main aerofoil portion; means for posi­ means of the third rotor in the opposite direction for tively and pivotally supporting said section for down­ pitching control of the aircraft, wherein at least one wardly rcflexing same, comprising: a support attached of said rotors has a mounting providing for tilting of at one end to, and projecting longitudinally from, the the rotor whereby to effect trimming of the aircraft main aerofoil portion; a link disposed between the without utilizing the pitch varying means. unattached end of the support and the upper inner surface of said section and pivotally connected at its ends to the support and to said section; and an 2,651,913. Gas Turbine Combustion Chamber. actuating member for reflcxing said section pivotally Grant B. Hodgson, San Diego, Calif., assignor to attached to the lower adjacent surface of said section, Solar Aircraft Company, San Diego, Calif. Applica­ the aforesaid pivot points together defining a tri­ tion March 13, 1951. angular truss-like structure having rigid sides dis­ whereby suction in said duct is produced by the low In a gas turbine combustion chamber structure posed under the flexible portion of said aerofoil con­ pressure developed at the core of said tip vortex comprising a cylinder of substantially uniform dia­ struction, said sides being pivotally adjustable by the during movement of the wing in flight. meter having an outlet and adapted for direct con­ actuating member into positions defining a scries of nexion with and to form a coaxial prolongation of the triangles taking all the stresses in all positions of said inlet end of a turbine scroll, a closure head secured flexible portion except those due to flexure of the 2,651,178. Combination Injector and Stabilizer for on the remote end of said cylinder, and means in the latter and to aerodynamic forces. Gas Turbine Afterburners. Frederick Denison Morgan cylinder wall adapted for connexion to a source of Williams, Weston, Ontario, Canada, assignor to compressed air: a fuel and air mixing head mounted A. V. Roe Canada Ltd., Malton, Ontario, Canada. on said cylinder closure head and comprising an 2,650,752. Boundary Layer Control in Blowers. Application January 18, 1951. annular rear section having a central inwardly directed Henry H. Hoadlcy, Manchester, Conn., assignor to depression, a fuel injector in said central depression, United Aircraft Corporation, East Hartford, Conn. a convergent annular wall extending generally axially Application August 27, 1949. from the periphery of said annular section, and a In combination, a fluid confining duct, a rotatable fluted divergent skirt the alternate flutes of which fan, means supporting said fan from the wall of said form passage means therein for deflecting air in a duct, said fan including a hub and a plurality of plurality of streams into said head and toward said blades, said blades having root sections and main fuel injector, said air thereby entraining fuel and sections terminating in tips adjacent the wall of said thereafter flowing successively over said rear section duct, a streamlined body forward of said fan for and being discharged in a convergent stream from directing a fluid stream in said duct around said hub said convergent section. and through said blades, turning vanes fixedly sup­ A fuel and air mixing head for a combustion cham­ ported from the wall of said duct and connected to ber comprising an end section of generally dished said body, means for increasing the overall efficiency shaped cross-section and having a central opening; of said propeller including a plurality of fins of aero­ An afterburner for a gas turbine engine, com­ a fuel nozzle secured in fluid tight relation in said foil shape carried by said body and the duct wall and prising a combustion chamber defined by an outer central opening; and inwardly and axially extending exposed to the fluid stream, said fins being located wall providing a duct through which a stream of gas section secured to the rim of said end section and is caused to flow, a hollow injector tube in the duct for providing a restricted throat opening; and a divergent injecting fuel into the combustion chamber, the in­ skirt portion secured to the free end of said inwardly jector tube being disposed with its longitudinal axis and axially extending section and having in its external parallel to the stream of gas and having open ends face outwardly opening, annularly spaced passages providing a fuel jet at each end, the jet at the down­ terminating at said throat opening and adapted to stream end of the tube being an auxiliary jet dis­ supply air interiorly of said head through said throat charging in a downstream direction and the jet at the opening. other end of the tube being a main jet discharging in an upstream direction, a baffle connected to and sur­ rounding the injector tube at a location upstream of the auxiliary jet and extending away from the in­ jector tube into the stream of gas to protect the auxiliary jet from the gas stream, igniting means for the auxiliary jet, and means for supplying fuel from a remote source to the injector tube. 2,651,480. Multiple Rotor Helicopter. Cyril George Pullin, Tadburn, Ampfield, Hampshire, England, assignor, by mesne assignments, to Autogiro Company :-.:iary 1954 31

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Jan 1, 1954

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