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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, pherally thereto, a ring of axial flow turbine blades Southampton Buildings, Chancery Lane, London, W.C.2. carried radially outwardly by the compressor blades, a turbine entry nozzle ring immediately upstream of said turbine blades, two co-axial annular members located radially within and enveloped by said nozzle ring and immediately upstream of said compressor 2,643,076. Improvement In Aircraft of High Aspect inner casing, circumfcrentially-spaccd teeth fast with blades, defining between them an annular air entry Ratio. Maurice Louis Hurel, Dcauville, France. one radial wall of said deeper portion of said circum­ thereto and gas ducting leading to said nozzle ring, Application July 25, 1946. In France September 5, ferential groove and extending axially across said said ducting being intersected by passages for air flow 1945. deeper portion, said teeth arranged in pairs with the from the surrounding atmosphere to said air entry. An aeroplane which comprises, in combination, a adjacent faces of the teeth of each pair defining a wing with two spans, a fuselage centrally of said parallel-sided recess, and said shrouds having radial spans, and bracing struts connected to the fuselage teeth slidably engaged in said recesses to locate said 2,645,081. Spacing Means for the Wall Sections and to points on the wing nearer to the centre of each blades circumfcrcntially of said inner casing. of Flame Tubes. William M. McDonald, Nobel, span than to the root and tip thereof, each bracing Ontario, Canada, assignor to A. V. Roc Canada 2,643,725. Electrically Welded Hollow Steel Pro­ strut having a substantial lift effect in level flight Limited, Malton, Ontario, Canada. Application peller Blade and Method of Making Same. William throughout substantially its whole length, high lift August 19, 1949. C. Heath, Milwaukee, Wis., assignor to A. O. Smith devices of low drag coefficient mounted on each span A flame tube, having in combination a first wall Corporation, Milwaukee, Wis. Original application of the wing, means joined to said devices for con­ section, a second wall section having an end portion March 26, 1943. Divided and this application January trolling both of said devices simultaneously in the overlapping and spaced from an end portion of the 12, 1950. first wall section to provide a space between the said A hollow metallic propeller blade comprising a end portions through which air can flow, said end pair of plates comprising flattened thrust and camber portions having a common longitudinal axis, at least members disposed in facing relation and defining an one of the said end portions having a plurality of interior chamber, and a reinforcing rib integral with laterally spaccd-apart openings formed about its one of said plates and extending into said chamber periphery, and having sides extending substantially from the inner side only of said plate, said reinforcing longitudinally of the flame tube, and spacers formed rib being uninterrupted and disposed crosswise with of sheet material of a thickness substantially less respect to the longitudinal axis of said propeller blade than the width of the space between the overlapping and extending from a point adjacent the blade trailing sections and extending between the said end portions same direction, said wing, struts and high lift devices with their major surfaces substantially parallel to the in active position having a combined aspect ratio of longitudinal axis of said end portions and with one at least 15 and a loading of at least 80 kg. per sq. m. edge of each spacer facing the flow of air through said space whereby the flow of air is substantially un­ 2,643,085. Gas Turbine Apparatus. William J. impeded; a spacer being secured to one of the wall Durkin, Swarthmore, and Donald N. Arvidson, sections having such openings, at one longitudinally Prospect Park, Pa., assignors to Westinghouse extending side at least of each of the openings in that edge to a point adjacent the blade leading edge, the Electric Corporation, East Pittsburgh, Pa. Applica­ wall section and to the other wall section in face to surface of said reinforcing rib which faces the other tion September 8, 1948. face contact at a location lying adjacent said opening, plate being spaced from the interior surface thereof. A turbine diaphragm structure comprising a plurality of pairs of semicircular shroud sections 2,643.832. Aerodynamic Lift-Producing Device. carrying radial blades, said shroud sections having Bryan Thwaitcs, London, England, assignor to the marginal flanges and spigots formed thereon, and Imperial Trust for the Encouragement of Scientific and Industrial Research, London, England. Applica­ tion January 26, 1949. An aerodynamic device for producing variable lift, said device comprising an aerofoil having a leading portion and a trailing portion, the chordwise section of said trailing portion of the aerofoil being of rounded form, a porous skin on at least the trailing portion of the aerofoil, and means at least partially the openings being of such substantial area that access contained within said device and applied to the under­ to a spacer may be gained through each opening to side of said porous skin for applying suction to the secure the spacer to the said other wall section. air flowing over said porous skin through the pores integral supporting rings interposed between and thereof; in combination with a spanwisc thin plate- secured to the respective pairs of shroud sections, said like trailing flap, means adjustably and revolubly 2,645,435. Structure for Conveying a Fluid at rings being of I-shaped cross-section with concentric High Temperature. Robert Pouit, Lyon, France, inner and outer flanges engaging the flanges and assignor to Socicte Industriclle Gcnerale de Mecani- spigots of said shroud sections for preventing dis­ que Appliqudc (S.I.A.G.M.A.), Villeurbanne, France. tortion of the assembled diaphragm structure. Original application April 9, 1947. Divided and this application July 26, 1949. 2,643,086. Mounting of Turbine Blades. Albert An aircraft structure which comprises, in combina­ Thomas and Leslie Richard Fellows, Coventry, tion, a hollow wing having a skin of aerofoil cross- England, assignors to Armstrong Siddclcy Motors section, a continuous wall inside said wing substan­ Limited, Coventry, England. Application October 23, tially parallel to said skin running along most of the 1947. In Great Britain September 2, 1947. wing span to form a continuous central conduit An axial flow internal combustion turbine including stopping short of the wing tip where said skin forms an outer stator casing, an inner stator casing pro­ a hollow chamber, a jet nozzle at the tip of the wing viding with the outer casing an annular passage for opening from said chamber into the atmosphere, a the hot gases, a row of radially-extending turbine mounting said flap on the aerofoil adjacent said trail­ corrugated partition in the space between said wall blades in said passage and having their outer ends fast ing portion for movement peripherally of the trailing and said skin having its corrugations directed span- with said outer casing, said inner casing built up of surface of the aerofoil in a direction substantially wise and alternately applied against said skin and said separable parts with axially-spaccd radial walls de­ normal to the span of the aerofoil, guiding means wall to form, between said wall and said skin over fining between them a circumferential groove of included in said mounting means, said guiding means the whole periphery of their cross-sections, a layer of which one axial end is deeper than the rest, shrouds confining the movement of the flap to follow the fluid-tight tubular ducts running spanwisc and open­ at the radially inner ends of said blades engaging said contour of the surface of the trailing portion of the ing into said chamber at the tip of the wing, means radial walls for locating said blades axially of said aerofoil, and means included in said guiding means for feeding a stream of hot gas to the root end of said for maintaining said flap, at all points of its operative central conduit, and means for feeding a stream of movement, substantially normal to said surface. relatively cool gas to the root end of at least every second tubular duct. 2,644,298. Propulsive Thrust Augmcnter. Roderick Cristall McLcod, Cropston, Leicester, England, and Kenneth Watson, Clarkston, Scotland, assignors to Power Jets (Research and Development) Limited, London, England. Application November 13, 1945. In Great Britain March 15, 1943. A thrust augmentcr comprising a rotor disk, a •ring of axial flow compressor blades attached peri­ 358 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 25 (11): 1 – Nov 1, 1953

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032361
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, pherally thereto, a ring of axial flow turbine blades Southampton Buildings, Chancery Lane, London, W.C.2. carried radially outwardly by the compressor blades, a turbine entry nozzle ring immediately upstream of said turbine blades, two co-axial annular members located radially within and enveloped by said nozzle ring and immediately upstream of said compressor 2,643,076. Improvement In Aircraft of High Aspect inner casing, circumfcrentially-spaccd teeth fast with blades, defining between them an annular air entry Ratio. Maurice Louis Hurel, Dcauville, France. one radial wall of said deeper portion of said circum­ thereto and gas ducting leading to said nozzle ring, Application July 25, 1946. In France September 5, ferential groove and extending axially across said said ducting being intersected by passages for air flow 1945. deeper portion, said teeth arranged in pairs with the from the surrounding atmosphere to said air entry. An aeroplane which comprises, in combination, a adjacent faces of the teeth of each pair defining a wing with two spans, a fuselage centrally of said parallel-sided recess, and said shrouds having radial spans, and bracing struts connected to the fuselage teeth slidably engaged in said recesses to locate said 2,645,081. Spacing Means for the Wall Sections and to points on the wing nearer to the centre of each blades circumfcrcntially of said inner casing. of Flame Tubes. William M. McDonald, Nobel, span than to the root and tip thereof, each bracing Ontario, Canada, assignor to A. V. Roc Canada 2,643,725. Electrically Welded Hollow Steel Pro­ strut having a substantial lift effect in level flight Limited, Malton, Ontario, Canada. Application peller Blade and Method of Making Same. William throughout substantially its whole length, high lift August 19, 1949. C. Heath, Milwaukee, Wis., assignor to A. O. Smith devices of low drag coefficient mounted on each span A flame tube, having in combination a first wall Corporation, Milwaukee, Wis. Original application of the wing, means joined to said devices for con­ section, a second wall section having an end portion March 26, 1943. Divided and this application January trolling both of said devices simultaneously in the overlapping and spaced from an end portion of the 12, 1950. first wall section to provide a space between the said A hollow metallic propeller blade comprising a end portions through which air can flow, said end pair of plates comprising flattened thrust and camber portions having a common longitudinal axis, at least members disposed in facing relation and defining an one of the said end portions having a plurality of interior chamber, and a reinforcing rib integral with laterally spaccd-apart openings formed about its one of said plates and extending into said chamber periphery, and having sides extending substantially from the inner side only of said plate, said reinforcing longitudinally of the flame tube, and spacers formed rib being uninterrupted and disposed crosswise with of sheet material of a thickness substantially less respect to the longitudinal axis of said propeller blade than the width of the space between the overlapping and extending from a point adjacent the blade trailing sections and extending between the said end portions same direction, said wing, struts and high lift devices with their major surfaces substantially parallel to the in active position having a combined aspect ratio of longitudinal axis of said end portions and with one at least 15 and a loading of at least 80 kg. per sq. m. edge of each spacer facing the flow of air through said space whereby the flow of air is substantially un­ 2,643,085. Gas Turbine Apparatus. William J. impeded; a spacer being secured to one of the wall Durkin, Swarthmore, and Donald N. Arvidson, sections having such openings, at one longitudinally Prospect Park, Pa., assignors to Westinghouse extending side at least of each of the openings in that edge to a point adjacent the blade leading edge, the Electric Corporation, East Pittsburgh, Pa. Applica­ wall section and to the other wall section in face to surface of said reinforcing rib which faces the other tion September 8, 1948. face contact at a location lying adjacent said opening, plate being spaced from the interior surface thereof. A turbine diaphragm structure comprising a plurality of pairs of semicircular shroud sections 2,643.832. Aerodynamic Lift-Producing Device. carrying radial blades, said shroud sections having Bryan Thwaitcs, London, England, assignor to the marginal flanges and spigots formed thereon, and Imperial Trust for the Encouragement of Scientific and Industrial Research, London, England. Applica­ tion January 26, 1949. An aerodynamic device for producing variable lift, said device comprising an aerofoil having a leading portion and a trailing portion, the chordwise section of said trailing portion of the aerofoil being of rounded form, a porous skin on at least the trailing portion of the aerofoil, and means at least partially the openings being of such substantial area that access contained within said device and applied to the under­ to a spacer may be gained through each opening to side of said porous skin for applying suction to the secure the spacer to the said other wall section. air flowing over said porous skin through the pores integral supporting rings interposed between and thereof; in combination with a spanwisc thin plate- secured to the respective pairs of shroud sections, said like trailing flap, means adjustably and revolubly 2,645,435. Structure for Conveying a Fluid at rings being of I-shaped cross-section with concentric High Temperature. Robert Pouit, Lyon, France, inner and outer flanges engaging the flanges and assignor to Socicte Industriclle Gcnerale de Mecani- spigots of said shroud sections for preventing dis­ que Appliqudc (S.I.A.G.M.A.), Villeurbanne, France. tortion of the assembled diaphragm structure. Original application April 9, 1947. Divided and this application July 26, 1949. 2,643,086. Mounting of Turbine Blades. Albert An aircraft structure which comprises, in combina­ Thomas and Leslie Richard Fellows, Coventry, tion, a hollow wing having a skin of aerofoil cross- England, assignors to Armstrong Siddclcy Motors section, a continuous wall inside said wing substan­ Limited, Coventry, England. Application October 23, tially parallel to said skin running along most of the 1947. In Great Britain September 2, 1947. wing span to form a continuous central conduit An axial flow internal combustion turbine including stopping short of the wing tip where said skin forms an outer stator casing, an inner stator casing pro­ a hollow chamber, a jet nozzle at the tip of the wing viding with the outer casing an annular passage for opening from said chamber into the atmosphere, a the hot gases, a row of radially-extending turbine mounting said flap on the aerofoil adjacent said trail­ corrugated partition in the space between said wall blades in said passage and having their outer ends fast ing portion for movement peripherally of the trailing and said skin having its corrugations directed span- with said outer casing, said inner casing built up of surface of the aerofoil in a direction substantially wise and alternately applied against said skin and said separable parts with axially-spaccd radial walls de­ normal to the span of the aerofoil, guiding means wall to form, between said wall and said skin over fining between them a circumferential groove of included in said mounting means, said guiding means the whole periphery of their cross-sections, a layer of which one axial end is deeper than the rest, shrouds confining the movement of the flap to follow the fluid-tight tubular ducts running spanwisc and open­ at the radially inner ends of said blades engaging said contour of the surface of the trailing portion of the ing into said chamber at the tip of the wing, means radial walls for locating said blades axially of said aerofoil, and means included in said guiding means for feeding a stream of hot gas to the root end of said for maintaining said flap, at all points of its operative central conduit, and means for feeding a stream of movement, substantially normal to said surface. relatively cool gas to the root end of at least every second tubular duct. 2,644,298. Propulsive Thrust Augmcnter. Roderick Cristall McLcod, Cropston, Leicester, England, and Kenneth Watson, Clarkston, Scotland, assignors to Power Jets (Research and Development) Limited, London, England. Application November 13, 1945. In Great Britain March 15, 1943. A thrust augmentcr comprising a rotor disk, a •ring of axial flow compressor blades attached peri­ 358 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Nov 1, 1953

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