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U.S. Patent Specifications

U.S. Patent Specifications of spaced flexible leaves each having one end secured to the duct, the leaves extending from the duct to define a nozzle opening and the leaves of the outer series overlapping the spaces between the leaves of the inner scries, at least one series of leaves being bi-metal These details and drawings of patents granted in the United States are taken, by permission of the to cause expansion and contraction of said opening Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies in response to temperature changes in the gas. 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, 2,563,453. Device for Controlling the Trailing Edge Southampton Buildings, Chancery Lane, London, W.C.2. Camber Flap of the Wing of an Aircraft. Paul Briend, Aix-en-Provence, France, assignor to Societe Anony- me Societc Nationale de Constructions Aeronautiques du Sud-Est. Application October 31, 1945. In France 2,563,218. Laminated Airfoil Section and Method of the keel line of the float, the combination with said January 26, 1945. Making Same. George F . Darracott, Stratford, Gerald float of a float lock for locking the two portions of the In a variable lift wing, a flap movable between an N. Barba, Fairfield, and Ludwig Reichert, Stratford, float together, a first power-operated retractor for upper retracted position and a lower extended position Conn., assignors to United Aircraft Corporation, retracting the float laterally, and with the two portions and forming when retracted a portion of the normal East Hartford, Conn. Application April 9, 1948. thereof locked together, to introduce one portion of under contour of the wing, a bracket rigidly secured the float into a recess in the wing, means responsive to on the front of said flap, and a control device for the entry of said portion into said recess for auto­ moving said flap which comprises a first pivot on matically releasing the float lock, and a second power- said wing, a second pivot on said wing to the rear of operated retractor, rendered operative by release of said first pivot, said pivots being located in the aerofoil said float lock, for separating the two portions of the float. 2,563,269. Gas Turbine. Nathan C. Price, Los Angeles, Calif., assignor to Lockheed Aircraft Cor­ poration, Burbank, Calif. Original application May 22, 1943, now Patent No. 2,468,461, dated April 26, 1949. Divided and this application February 7,1945. In a gas turbine, a hollow turbine blade having a tip portion and a root portion, the internal surfaces of the hollow blade being sloped so that the walls of the blade diminish in thickness from the root portion section of said wing, a first lever one end of which is A laminated aerofoil section comprising spaced toward the tip portion, a tip wall extending across pivotally mounted on said first pivot and the other curved surface sheets of high density material the tip end of the blade, an axial web in the root end of which is pivoted on said bracket, said first adhesively bonded to a continuous core sheet of wood portion of the blade for increasing the cooling surface lever being forwardly and downwardly directed when area thereof and extending only a limited distance in which has the ends of the grain abutting said surface the flap is retracted, a lever-link member formed by a the blade, the root end of the hollow blade being open sheets, said core sheet in the area of the leading edge second lever one end of which is pivotally mounted for the reception of coolant, said tip wall having at of said aerofoil comprising a plurality of pieces adhes­ on said second pivot and by a link the ends of which least one restricted port for the discharge of coolant ively bonded together having the bond lines between are respectively pivoted on the other end of said from the tip of the blade and to maintain coolant flow said pieces and the seasonal growth lines of said second lever and on the front part of said flap, the axially through the blade, the rear wall of the blade pieces substantially perpendicular to said leading edge, line connecting the pivotal points of said lever-link said core and surface sheets forming a continuous member on said wing and said flap being forwardly panel having a curvature corresponding to the contour and downwardly directed when the flap is retracted, of said aerofoil, a plurality of spaced flanges attached means for varying the angular position of said first to each of the upper and lower internal surfaces of lever by rotation thereof about said first wing pivot so said aerofoil shaped panel in chordwise planes of said that said lever passes below said pivot, whereby said aerofoil, and means for rigidly connecting said flanges control device has no clement projecting above said to internal structure adapted to be disposed in said aerofoil section, means for varying the relative angu­ aerofoil. lar position of said second lever with respect to said In a method of fabricating sharply bent aerofoil link as a function of the angular displacement of said sections of composite laminated structure the steps first lever according to a predetermined law, so that comprising, assembling a core sheet comprising, a the resulting unfolding of said lever-link member plurality of pieces of wood having a length along the generates a predetermined lowering movement of relative to the direction of the gas flow having a longi­ grain equal to the thickness of the core, adhesively of said flap with respect to said wing. tudinally extending slot spaced substantially mid-way securing said pieces together to form a core sheet, ad­ between its leading and trailing extremities for dis­ hesively bonding a metal sheet to the face of said core charging a layer of the coolant over the rearward 2,565,007. Nose Landing Gear. Willem D. van sheet which is to become the outer surface of the aero­ portion of said surface, and inwardly projecting lips Zelm, Ruxton, and Joseph Sheleski, Baltimore, Md., foil, adhesively bonding spaced metal sheets to the other on the internal surface of said rear wall extending assignors to The Glen L. Martin Company, Middle face of said core sheet on opposite sides of the axis along the margins of said slot and shaped to give the River, Md. Application December 19, 1946. about which the bend is to take place, curing said slot a nozzle-like configuration and increasing the assembly under suitable temperature and pressure to depth of the slot. form a unitary laminated panel, bending said panel in a jig to conform the panel to aerofoil shape, transferring said aerofoil to a mould, adhesively bonding a surface 2,563,270. Gas Reaction Power Plant with a plate to the inner exposed surface of said core along Variable Area Nozzle. Nathan C. Price, Hollywood, the bend axis, and curing said adhesive while said sur­ Calif., assignor to Lockheed Aircraft Corporation, face plate is held under pressure in said mould. Burbank, Calif. Original application February 14, 1944. Divided and this application June 29, 1945. A nozzle for a fluid conduit comprising a tubular 2,563,263. Two Stage Retractable Float for Aircraft. nozzle assembly extending from the conduit and char­ Edward James Nicholl, Cheltenham, England, as­ signor to Saunders-Roc Limited, Osborne, East acterized by an annular series of overlapping bi-metal leaves defining the nozzle opening and free throughout Cowes, Isle of Wight, England. Application October the major portion of its length to be expansible and 23, 1948. In Great Britain November 6, 1947. contractable in a radial direction to vary the area of said opening upon a change in temperature of the In an aeroplane having jet propulsion means arrang­ fluid. ed to discharge rearwardly relative thereto, retractable An internal combustion reaction type power plant main landing gear located aft the centre of gravity and comprising turbo-compressor means, a duct for carry­ a retractable nose gear forward of the centre of ing the exhaust gas from said means, and a nozzle for gravity, said gear when fully extended adapted to sup­ spouting the gas from the duct in the form of a pro­ port said aeroplane on the ground in a normal, generally pulsive jet comprising inner and outer annular series horizontal position, said nose gear comprising a wheel, and supporting and retracting mechanism therefor movably connecting said wheel to said aeroplane and operable to move said wheel between fully extended and fully retracted position, said mechanism including means for locking said wheel in either said position, and a separate releasable latch means carried by said aeroplane adjacent said nose gear and adapted to selectively engage said mechanism for holding said wheel in an intermediate partially retracted position wherein said aeroplane will be supported in a rear­ wardly and upwardly inclined position relative to the In an aircraft, comprising a wing and a stabilizing ground to direct the discharge from said jet propulsion float divided into two portions hinged together along means upwardly and rearwardly. 120 Aircraft Engineering 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 24 (4): 1 – Apr 1, 1952
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032153
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Abstract

of spaced flexible leaves each having one end secured to the duct, the leaves extending from the duct to define a nozzle opening and the leaves of the outer series overlapping the spaces between the leaves of the inner scries, at least one series of leaves being bi-metal These details and drawings of patents granted in the United States are taken, by permission of the to cause expansion and contraction of said opening Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies in response to temperature changes in the gas. 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, 2,563,453. Device for Controlling the Trailing Edge Southampton Buildings, Chancery Lane, London, W.C.2. Camber Flap of the Wing of an Aircraft. Paul Briend, Aix-en-Provence, France, assignor to Societe Anony- me Societc Nationale de Constructions Aeronautiques du Sud-Est. Application October 31, 1945. In France 2,563,218. Laminated Airfoil Section and Method of the keel line of the float, the combination with said January 26, 1945. Making Same. George F . Darracott, Stratford, Gerald float of a float lock for locking the two portions of the In a variable lift wing, a flap movable between an N. Barba, Fairfield, and Ludwig Reichert, Stratford, float together, a first power-operated retractor for upper retracted position and a lower extended position Conn., assignors to United Aircraft Corporation, retracting the float laterally, and with the two portions and forming when retracted a portion of the normal East Hartford, Conn. Application April 9, 1948. thereof locked together, to introduce one portion of under contour of the wing, a bracket rigidly secured the float into a recess in the wing, means responsive to on the front of said flap, and a control device for the entry of said portion into said recess for auto­ moving said flap which comprises a first pivot on matically releasing the float lock, and a second power- said wing, a second pivot on said wing to the rear of operated retractor, rendered operative by release of said first pivot, said pivots being located in the aerofoil said float lock, for separating the two portions of the float. 2,563,269. Gas Turbine. Nathan C. Price, Los Angeles, Calif., assignor to Lockheed Aircraft Cor­ poration, Burbank, Calif. Original application May 22, 1943, now Patent No. 2,468,461, dated April 26, 1949. Divided and this application February 7,1945. In a gas turbine, a hollow turbine blade having a tip portion and a root portion, the internal surfaces of the hollow blade being sloped so that the walls of the blade diminish in thickness from the root portion section of said wing, a first lever one end of which is A laminated aerofoil section comprising spaced toward the tip portion, a tip wall extending across pivotally mounted on said first pivot and the other curved surface sheets of high density material the tip end of the blade, an axial web in the root end of which is pivoted on said bracket, said first adhesively bonded to a continuous core sheet of wood portion of the blade for increasing the cooling surface lever being forwardly and downwardly directed when area thereof and extending only a limited distance in which has the ends of the grain abutting said surface the flap is retracted, a lever-link member formed by a the blade, the root end of the hollow blade being open sheets, said core sheet in the area of the leading edge second lever one end of which is pivotally mounted for the reception of coolant, said tip wall having at of said aerofoil comprising a plurality of pieces adhes­ on said second pivot and by a link the ends of which least one restricted port for the discharge of coolant ively bonded together having the bond lines between are respectively pivoted on the other end of said from the tip of the blade and to maintain coolant flow said pieces and the seasonal growth lines of said second lever and on the front part of said flap, the axially through the blade, the rear wall of the blade pieces substantially perpendicular to said leading edge, line connecting the pivotal points of said lever-link said core and surface sheets forming a continuous member on said wing and said flap being forwardly panel having a curvature corresponding to the contour and downwardly directed when the flap is retracted, of said aerofoil, a plurality of spaced flanges attached means for varying the angular position of said first to each of the upper and lower internal surfaces of lever by rotation thereof about said first wing pivot so said aerofoil shaped panel in chordwise planes of said that said lever passes below said pivot, whereby said aerofoil, and means for rigidly connecting said flanges control device has no clement projecting above said to internal structure adapted to be disposed in said aerofoil section, means for varying the relative angu­ aerofoil. lar position of said second lever with respect to said In a method of fabricating sharply bent aerofoil link as a function of the angular displacement of said sections of composite laminated structure the steps first lever according to a predetermined law, so that comprising, assembling a core sheet comprising, a the resulting unfolding of said lever-link member plurality of pieces of wood having a length along the generates a predetermined lowering movement of relative to the direction of the gas flow having a longi­ grain equal to the thickness of the core, adhesively of said flap with respect to said wing. tudinally extending slot spaced substantially mid-way securing said pieces together to form a core sheet, ad­ between its leading and trailing extremities for dis­ hesively bonding a metal sheet to the face of said core charging a layer of the coolant over the rearward 2,565,007. Nose Landing Gear. Willem D. van sheet which is to become the outer surface of the aero­ portion of said surface, and inwardly projecting lips Zelm, Ruxton, and Joseph Sheleski, Baltimore, Md., foil, adhesively bonding spaced metal sheets to the other on the internal surface of said rear wall extending assignors to The Glen L. Martin Company, Middle face of said core sheet on opposite sides of the axis along the margins of said slot and shaped to give the River, Md. Application December 19, 1946. about which the bend is to take place, curing said slot a nozzle-like configuration and increasing the assembly under suitable temperature and pressure to depth of the slot. form a unitary laminated panel, bending said panel in a jig to conform the panel to aerofoil shape, transferring said aerofoil to a mould, adhesively bonding a surface 2,563,270. Gas Reaction Power Plant with a plate to the inner exposed surface of said core along Variable Area Nozzle. Nathan C. Price, Hollywood, the bend axis, and curing said adhesive while said sur­ Calif., assignor to Lockheed Aircraft Corporation, face plate is held under pressure in said mould. Burbank, Calif. Original application February 14, 1944. Divided and this application June 29, 1945. A nozzle for a fluid conduit comprising a tubular 2,563,263. Two Stage Retractable Float for Aircraft. nozzle assembly extending from the conduit and char­ Edward James Nicholl, Cheltenham, England, as­ signor to Saunders-Roc Limited, Osborne, East acterized by an annular series of overlapping bi-metal leaves defining the nozzle opening and free throughout Cowes, Isle of Wight, England. Application October the major portion of its length to be expansible and 23, 1948. In Great Britain November 6, 1947. contractable in a radial direction to vary the area of said opening upon a change in temperature of the In an aeroplane having jet propulsion means arrang­ fluid. ed to discharge rearwardly relative thereto, retractable An internal combustion reaction type power plant main landing gear located aft the centre of gravity and comprising turbo-compressor means, a duct for carry­ a retractable nose gear forward of the centre of ing the exhaust gas from said means, and a nozzle for gravity, said gear when fully extended adapted to sup­ spouting the gas from the duct in the form of a pro­ port said aeroplane on the ground in a normal, generally pulsive jet comprising inner and outer annular series horizontal position, said nose gear comprising a wheel, and supporting and retracting mechanism therefor movably connecting said wheel to said aeroplane and operable to move said wheel between fully extended and fully retracted position, said mechanism including means for locking said wheel in either said position, and a separate releasable latch means carried by said aeroplane adjacent said nose gear and adapted to selectively engage said mechanism for holding said wheel in an intermediate partially retracted position wherein said aeroplane will be supported in a rear­ wardly and upwardly inclined position relative to the In an aircraft, comprising a wing and a stabilizing ground to direct the discharge from said jet propulsion float divided into two portions hinged together along means upwardly and rearwardly. 120 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Apr 1, 1952

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