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U.S. Patent Specifications

U.S. Patent Specifications the blades thereof comprising in combination a case, a rotor hub mounted in said case for ratation about an axis defining an annular axial flow channel therewith and a plurality of axial flow blades carried on said hub 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. 2,786,538. Aircraft Propeller Blade. Mack O. In an aircraft boost control system, an aerofoil, a Blackburn and Selwyn E. Gaber, Dayton and Clifford control, surface movably mounted upon said aero­ B. Wright, Tipp City, Ohio, assignors to General foil, a tab movably mounted upon said control sur­ Motors Corporation, Detroit, Mich. Application May face, actuating means for applying control forces to I, 1952. spaced peripherally thereabout and extending span- said control surface, a spring-biased member opera- wise radially across said channel, said blades defining tivcly connected to said tab, to said control surface a plurality of axial flow passages therebetween each and to said actuating means whereby control forces having an inlet and an exit respectively at the front and applied to said control surface actuating means impart rear sides of said rotor, said case and said hub bound­ through said spring-biased member movement to said ing said passages and defining the general lengthwise tab, and means including an aerodynamic pressure direction thereof, each said blade having a curved plate operatively connected to said control surface mean camber line presenting the concave side thereof initiated by deflexion of said tab to apply balance toward the direction of rotation with the maximum pressure to said control surface. curvature thereof in the forward half thereof position­ ing the mean camber line maximum ordinate above 2,787,889. Aircraft Compartment Cooling Mech­ its subtending chord substantially forward of the mid anism. Douglas H. Swank, Seattle, Wash., assignor to point of said chord to turn the flow in each said pass­ Boeing Airplane Company, Seattle, Wash. Applica­ age chiefly in the forward half thereof toward the tion August 15, 1955. direction of rotation, said case and said hub co-operat­ ing to define portions of the surfaces thereof at radi­ In a hollow propeller blade, a thrust member having ally opposite ends of each said blade converging rear­ an integral longitudinally extending rib, a leading ward radially one relative to the other along a forward edge and a trailing edge, a camber member joined to portion of the chord of each said blade establishing said rib, the leading edge and the trailing edge to com­ for each said passage cross-sectional areas and radial plete the blade aerofoil, said rib being provided with op­ depths thereof decreasing in magnitude rearward positely extending integral flanges having knife-like therealong from each said inlet to a locality sub­ edges, said flanges, merging with the inner surface stantially as far rearward as said ordinate providing of said camber member adjacent the joint therebetween continuously decreasing cross-sectional areas of said Aircraft compartment cooling mechanism compris­ whereby the concentration of stress along said joint is passage to accelerate the flow in each said passage ing means operable to evaporate refrigerant into the substantially uniform. while said flow is being turned by the forward portions compartment for cooling the same, compressor means of said blades. operable, to withdraw evaporated refrigerant from the 2,787,120. Plural Annular Coaxial Combustion compartment, condenser means operable to condense Chambers. Rene Leduc, Argenteuill, France. Applica­ 2,792,998. Brake System on Aircraft Multi-Wheel refrigerant compressed by said compressor means, and tion France, August 5, 1950. Bogie Undercarriage. George H. Dowty, Cheltenham, differential pressure sensitive control means exposed England. Application Great Britain, October 23,1952. to the pressure in the compartment and to the external ambient atmospheric pressure and operable to limit the reduction in compartment pressure to a value at east not appreciably below external ambient atmos­ pheric pressure by controlling operation of said com­ pressor means to curtail transfer of refrigerant from the compartment to said condenser means. 2,788,075. Helicopter with Paddle Wheel Type Tail Rotor. Cyril George Pullin, Moseley, Birmingham, Propulsion apparatus, comprising, in combination, and Jacob Samuel Shapiro, London, assignors, by an elongated duct adapted to convey a combustible mesne assignments, to Autogiro Company of Ameri­ fluid axially along the duct in the interior thereof; a ca, Philadelphia, Pa. Application Great Britain, Oct­ plurality of annular substantially frustoconical blades ober 11, 1944. arranged in overlapping relationship in said duct about the axis thereof and being spaced along said axis with the larger end of each blade located upsptream of its smaller end, the spaces between said blades being free so that said blades form a plurality of frustoconical annular passages directed inwardly toward the axis of the duct, overlapping each other, and being dis­ tributed along the axis of the duct, said blades each In combination with an aircraft undercarriage which having adjacent to but spaced from said smaller end comprises a generally upright landing leg, a bogie thereof an elongated region of a diameter which de­ frame, a first journal means pivotally supporting one In a helicopter, in combination with a lifting rotor creases at a greater rate than the diameter of said blade end of said bogie frame upon the lower end of said system and a power plant, at least one controllable in the region of said larger end thereof; and a plurality landing leg for swinging in an upright fore and aft yaw-moment-producing auxiliary rotor operative in of combustion means respectively located in said plane, a first wheel assembly rotatively mounted upon hovering flight and off-set rearwardly from the centre annular passages. said first journal means, a parallel second journal of gravity of the helicopter with its axis in a fore and means upon the swinging end of said bogie frame, a aft vertical plane and comprising a rotatable wheel 2,787,429. Aircraft Control Surface Boost Arrange­ second wheel assembly rotatively mounted upon said structure, a number of blades supported thereon with ments. Roland J. White, Seattle, Wash., assignor to second journal means, and shock absorber means re­ their spanwise axes extended forwardly and rear­ Boeing Airplane Company. Application April 14, acting between said bogie frame and said landing leg; wardly and arranged parallel to and evenly spaced 1953. brake means for said wheel assemblies which com­ about the auxiliary rotor axis, the wheel structure in­ prises a first brake plate mounted coaxially of said first cluding a mounting for each blade, permitting oscilla­ journal means and fixed relatively to said landing leg, tion of the blade about its spanwise axis, and mechan­ a second brake plate mounted coaxially of said second ism for oscillating all the blades on their mountings journal means and swingable with but free to oscillate through a limited angle with a frequency of once per relative to said bogie frame, a torque link, pivot pins revolution of the rotor and with the same amplitude joining said torque link to each of said brake plates, at and phasing, and transmission means connecting the points equally distant from and located along parallel power plant with the auxiliary rotor for rotating the radii of their respective journal axes, fluid pressure latter. brake actuating devices mounted upon each brake plat for operation of brakes on the corresponding wheel 2,788,172. Bladed Structures for Axial Flow Com­ assemblies, and pressure fluid conduits extending from pressors. Edward A. Stalker, Bay City, Mich., assignor said landing leg to the several brake actuating devices, to The Stalker Development Company, Bay City, said conduits including swivel joints disposed coaxially Mich. Application December 6, 1951. of and mounted upon said pivot pins, and sections fixedly mounted with respect to the landing leg, the two An axial flow subsonic compressor for operation brake plates, and the torque link. with relative fluid velocities less than sonic relative to 226 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 29 (7): 1 – Jul 1, 1957

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032857
Publisher site
See Article on Publisher Site

Abstract

the blades thereof comprising in combination a case, a rotor hub mounted in said case for ratation about an axis defining an annular axial flow channel therewith and a plurality of axial flow blades carried on said hub 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. 2,786,538. Aircraft Propeller Blade. Mack O. In an aircraft boost control system, an aerofoil, a Blackburn and Selwyn E. Gaber, Dayton and Clifford control, surface movably mounted upon said aero­ B. Wright, Tipp City, Ohio, assignors to General foil, a tab movably mounted upon said control sur­ Motors Corporation, Detroit, Mich. Application May face, actuating means for applying control forces to I, 1952. spaced peripherally thereabout and extending span- said control surface, a spring-biased member opera- wise radially across said channel, said blades defining tivcly connected to said tab, to said control surface a plurality of axial flow passages therebetween each and to said actuating means whereby control forces having an inlet and an exit respectively at the front and applied to said control surface actuating means impart rear sides of said rotor, said case and said hub bound­ through said spring-biased member movement to said ing said passages and defining the general lengthwise tab, and means including an aerodynamic pressure direction thereof, each said blade having a curved plate operatively connected to said control surface mean camber line presenting the concave side thereof initiated by deflexion of said tab to apply balance toward the direction of rotation with the maximum pressure to said control surface. curvature thereof in the forward half thereof position­ ing the mean camber line maximum ordinate above 2,787,889. Aircraft Compartment Cooling Mech­ its subtending chord substantially forward of the mid anism. Douglas H. Swank, Seattle, Wash., assignor to point of said chord to turn the flow in each said pass­ Boeing Airplane Company, Seattle, Wash. Applica­ age chiefly in the forward half thereof toward the tion August 15, 1955. direction of rotation, said case and said hub co-operat­ ing to define portions of the surfaces thereof at radi­ In a hollow propeller blade, a thrust member having ally opposite ends of each said blade converging rear­ an integral longitudinally extending rib, a leading ward radially one relative to the other along a forward edge and a trailing edge, a camber member joined to portion of the chord of each said blade establishing said rib, the leading edge and the trailing edge to com­ for each said passage cross-sectional areas and radial plete the blade aerofoil, said rib being provided with op­ depths thereof decreasing in magnitude rearward positely extending integral flanges having knife-like therealong from each said inlet to a locality sub­ edges, said flanges, merging with the inner surface stantially as far rearward as said ordinate providing of said camber member adjacent the joint therebetween continuously decreasing cross-sectional areas of said Aircraft compartment cooling mechanism compris­ whereby the concentration of stress along said joint is passage to accelerate the flow in each said passage ing means operable to evaporate refrigerant into the substantially uniform. while said flow is being turned by the forward portions compartment for cooling the same, compressor means of said blades. operable, to withdraw evaporated refrigerant from the 2,787,120. Plural Annular Coaxial Combustion compartment, condenser means operable to condense Chambers. Rene Leduc, Argenteuill, France. Applica­ 2,792,998. Brake System on Aircraft Multi-Wheel refrigerant compressed by said compressor means, and tion France, August 5, 1950. Bogie Undercarriage. George H. Dowty, Cheltenham, differential pressure sensitive control means exposed England. Application Great Britain, October 23,1952. to the pressure in the compartment and to the external ambient atmospheric pressure and operable to limit the reduction in compartment pressure to a value at east not appreciably below external ambient atmos­ pheric pressure by controlling operation of said com­ pressor means to curtail transfer of refrigerant from the compartment to said condenser means. 2,788,075. Helicopter with Paddle Wheel Type Tail Rotor. Cyril George Pullin, Moseley, Birmingham, Propulsion apparatus, comprising, in combination, and Jacob Samuel Shapiro, London, assignors, by an elongated duct adapted to convey a combustible mesne assignments, to Autogiro Company of Ameri­ fluid axially along the duct in the interior thereof; a ca, Philadelphia, Pa. Application Great Britain, Oct­ plurality of annular substantially frustoconical blades ober 11, 1944. arranged in overlapping relationship in said duct about the axis thereof and being spaced along said axis with the larger end of each blade located upsptream of its smaller end, the spaces between said blades being free so that said blades form a plurality of frustoconical annular passages directed inwardly toward the axis of the duct, overlapping each other, and being dis­ tributed along the axis of the duct, said blades each In combination with an aircraft undercarriage which having adjacent to but spaced from said smaller end comprises a generally upright landing leg, a bogie thereof an elongated region of a diameter which de­ frame, a first journal means pivotally supporting one In a helicopter, in combination with a lifting rotor creases at a greater rate than the diameter of said blade end of said bogie frame upon the lower end of said system and a power plant, at least one controllable in the region of said larger end thereof; and a plurality landing leg for swinging in an upright fore and aft yaw-moment-producing auxiliary rotor operative in of combustion means respectively located in said plane, a first wheel assembly rotatively mounted upon hovering flight and off-set rearwardly from the centre annular passages. said first journal means, a parallel second journal of gravity of the helicopter with its axis in a fore and means upon the swinging end of said bogie frame, a aft vertical plane and comprising a rotatable wheel 2,787,429. Aircraft Control Surface Boost Arrange­ second wheel assembly rotatively mounted upon said structure, a number of blades supported thereon with ments. Roland J. White, Seattle, Wash., assignor to second journal means, and shock absorber means re­ their spanwise axes extended forwardly and rear­ Boeing Airplane Company. Application April 14, acting between said bogie frame and said landing leg; wardly and arranged parallel to and evenly spaced 1953. brake means for said wheel assemblies which com­ about the auxiliary rotor axis, the wheel structure in­ prises a first brake plate mounted coaxially of said first cluding a mounting for each blade, permitting oscilla­ journal means and fixed relatively to said landing leg, tion of the blade about its spanwise axis, and mechan­ a second brake plate mounted coaxially of said second ism for oscillating all the blades on their mountings journal means and swingable with but free to oscillate through a limited angle with a frequency of once per relative to said bogie frame, a torque link, pivot pins revolution of the rotor and with the same amplitude joining said torque link to each of said brake plates, at and phasing, and transmission means connecting the points equally distant from and located along parallel power plant with the auxiliary rotor for rotating the radii of their respective journal axes, fluid pressure latter. brake actuating devices mounted upon each brake plat for operation of brakes on the corresponding wheel 2,788,172. Bladed Structures for Axial Flow Com­ assemblies, and pressure fluid conduits extending from pressors. Edward A. Stalker, Bay City, Mich., assignor said landing leg to the several brake actuating devices, to The Stalker Development Company, Bay City, said conduits including swivel joints disposed coaxially Mich. Application December 6, 1951. of and mounted upon said pivot pins, and sections fixedly mounted with respect to the landing leg, the two An axial flow subsonic compressor for operation brake plates, and the torque link. with relative fluid velocities less than sonic relative to 226 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Jul 1, 1957

There are no references for this article.