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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 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, Southampton Buildings, Chancery Lane, London, W.C.2. 2,541,900. Multiple Fuel Jet Burner and Torch Igniter Unit with Fuel Vaporizing Tubes. Frederick D. M. Williams, Nobel, Ontario, Canada, assignor means supporting all wheels except the upper wheel to A. V. Roc Canada Limited, Malton, Ontario, from the frame and arranged in a pattern, including Canada, a corporation. Application December 24, the upper wheel, to receive and. guide said track band 1948. Serial No. 67,118. 5 Claims. (CI. 60—44.) and to maintain it, between the front bogie yhcel and the rear wheel, in ground contact while the landing gear is ground-borne; a support carried by and for movement relative to the frame, and constituting the immediate support of said braking wheel, said sup­ port being opcrativcly connected for movement with the front bogie wheel, relative to the frame; brake re­ action means carried by said support and anchored of the wing, a flap bracket means to said frame; and brake means reacting between said extending forwardly and downwardly brake reaction means and said braking wheel. secured to said lower pivot, a slat having bracket means secured thereto extending for­ In a combustion chamber of a gas turbine engine, wardly and downwardly from the leading edge thereof 2,548,087. Vaporizer System for Combustion a flame tube in which combustion takes place, open­ supported on said upper pivot, linkage means pivoted Chambers. Frederick Denison Morgan Williams, ings in the flame tube for admitting a stream of air at a point on said slat adjacent the trailing edge Nobel, Ontario, Canada, assignor to A. V. Roe at one end of the flame tube to support combustion, thereof, and a point on said flap adjacent the nose Canada Limited, Malton, Ontario, Canada. Applica­ vaporizer tubes mounted in the fiamc tube adjacent portion thereof to control the incidence of said slat tion January 21, 1950. the upstream end of the flame tube and extending as the flap is moved to a position of high lift or drag, In a vaporizer system for a combustion chamber in longitudinally thereof, each such vaporizer tube a two-part streamline housing faired around the which liquid fuel is burned in an air stream flowing in having an inlet end exposed to the air stream through portions of said brackets extending below the lower the combustion chamber, vaporizer tubes having inlet the combustion chamber and an outlet end discharg­ surface of said wing, one portion of said housing ends and outlet ends, said tubes being secured with ing into the flame tube, and an injector head located sscurcd to said wing structure and the other portion their inlet ends facing the air stream and the outlet substantially on the longitudinal axis of the flame tube of said housing secured to said flap. ends of the tubes converging into a common outlet at its upstream end, said injector head comprising an facing the air stream. igniter jet directed into the flame tube substantially 2,544,985. Track-type Landing Gear. George T. at the longitudinal axis thereof between the vaporizer Drakclcy and Donald W. Finlay, Seattle, Wash., tubes, whereby an igniting flame may be injected assignors to Boeing Airplane Company, Seattle, directly into the flame tube and played upon the Wash., a corporation of Delaware. Application July vaporizer tubes, an igniter situated in front of said 11,1949. jet, a plurality of fuel supply jets arranged around A track-type landing gear comprising an endless the igniter jet and directed to the inlet ends of the track band, a frame, a front bogie wheel, a braking vaporizer tubes, a fuel inlet conduit for the fuel wheel ahead thereof and elevated thercabove, a rear supply jets, and a fuel inlet conduit for the igniter jet wheel, additional bogie wheels intermediate the within and substantially co-axial with the fuel inlet front bogie wheel and the rear wheel, an upper wheel conduit for the fuel supply jets. supported from the frame, resilicntly yicldable 2,542,499. Automatic Control for Gas Turbines. Peter Fortcscuc, Bristol, England, assignor to The British Aeroplane Company Limited, Bristol, Eng­ land, a British company. Application October 29, 1946. Serial No. 706,317. In Great Britain October 16, 1945. 5 Claims. (CI. 175—355.) Apparatus for automatically controlling a gas- turbine engine in which an operating variable of the engine is electrically controlled comprising a bridge network, means for applying an electrical quantity, proportional to the engine variable, to the network, means for applying a standard electrical quantity representing the datum value which the variable outfit to have, said quantities being compared in the net­ work so that an electrical quantity results from said comparison when the network is unbalanced, control means to which said resultant electrical quantity is applied to adjust the engine variable and means actuated by the resultant electrical quantity for increasing the unbalanced state of the network. 2,542,792. Aeroplane Wing Flap and Slat Mount- in};. James H. Bennett, Baltimore, and James A. Webb, Essex, Md., assignors to The Glenn L. Martin Company, Middle River, Md., a corporation of Maryland. Application August 16, 1947. Serial No. 769,002. 5 Claims. (CI. 244—42.) An aeroplane wing flap mounting comprising a plurality of bracket means rigidly affixed on the trailing edge of an aeroplane wing extending down­ wardly and to the rear thereof, each of said bracket means supporting an upper and lower pivot, said upper pivot being located within the wing profile and said lower pivot being located below the under side 248 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 23 (8): 1 – Aug 1, 1951

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032074
Publisher site
See Article on Publisher Site

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 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, Southampton Buildings, Chancery Lane, London, W.C.2. 2,541,900. Multiple Fuel Jet Burner and Torch Igniter Unit with Fuel Vaporizing Tubes. Frederick D. M. Williams, Nobel, Ontario, Canada, assignor means supporting all wheels except the upper wheel to A. V. Roc Canada Limited, Malton, Ontario, from the frame and arranged in a pattern, including Canada, a corporation. Application December 24, the upper wheel, to receive and. guide said track band 1948. Serial No. 67,118. 5 Claims. (CI. 60—44.) and to maintain it, between the front bogie yhcel and the rear wheel, in ground contact while the landing gear is ground-borne; a support carried by and for movement relative to the frame, and constituting the immediate support of said braking wheel, said sup­ port being opcrativcly connected for movement with the front bogie wheel, relative to the frame; brake re­ action means carried by said support and anchored of the wing, a flap bracket means to said frame; and brake means reacting between said extending forwardly and downwardly brake reaction means and said braking wheel. secured to said lower pivot, a slat having bracket means secured thereto extending for­ In a combustion chamber of a gas turbine engine, wardly and downwardly from the leading edge thereof 2,548,087. Vaporizer System for Combustion a flame tube in which combustion takes place, open­ supported on said upper pivot, linkage means pivoted Chambers. Frederick Denison Morgan Williams, ings in the flame tube for admitting a stream of air at a point on said slat adjacent the trailing edge Nobel, Ontario, Canada, assignor to A. V. Roe at one end of the flame tube to support combustion, thereof, and a point on said flap adjacent the nose Canada Limited, Malton, Ontario, Canada. Applica­ vaporizer tubes mounted in the fiamc tube adjacent portion thereof to control the incidence of said slat tion January 21, 1950. the upstream end of the flame tube and extending as the flap is moved to a position of high lift or drag, In a vaporizer system for a combustion chamber in longitudinally thereof, each such vaporizer tube a two-part streamline housing faired around the which liquid fuel is burned in an air stream flowing in having an inlet end exposed to the air stream through portions of said brackets extending below the lower the combustion chamber, vaporizer tubes having inlet the combustion chamber and an outlet end discharg­ surface of said wing, one portion of said housing ends and outlet ends, said tubes being secured with ing into the flame tube, and an injector head located sscurcd to said wing structure and the other portion their inlet ends facing the air stream and the outlet substantially on the longitudinal axis of the flame tube of said housing secured to said flap. ends of the tubes converging into a common outlet at its upstream end, said injector head comprising an facing the air stream. igniter jet directed into the flame tube substantially 2,544,985. Track-type Landing Gear. George T. at the longitudinal axis thereof between the vaporizer Drakclcy and Donald W. Finlay, Seattle, Wash., tubes, whereby an igniting flame may be injected assignors to Boeing Airplane Company, Seattle, directly into the flame tube and played upon the Wash., a corporation of Delaware. Application July vaporizer tubes, an igniter situated in front of said 11,1949. jet, a plurality of fuel supply jets arranged around A track-type landing gear comprising an endless the igniter jet and directed to the inlet ends of the track band, a frame, a front bogie wheel, a braking vaporizer tubes, a fuel inlet conduit for the fuel wheel ahead thereof and elevated thercabove, a rear supply jets, and a fuel inlet conduit for the igniter jet wheel, additional bogie wheels intermediate the within and substantially co-axial with the fuel inlet front bogie wheel and the rear wheel, an upper wheel conduit for the fuel supply jets. supported from the frame, resilicntly yicldable 2,542,499. Automatic Control for Gas Turbines. Peter Fortcscuc, Bristol, England, assignor to The British Aeroplane Company Limited, Bristol, Eng­ land, a British company. Application October 29, 1946. Serial No. 706,317. In Great Britain October 16, 1945. 5 Claims. (CI. 175—355.) Apparatus for automatically controlling a gas- turbine engine in which an operating variable of the engine is electrically controlled comprising a bridge network, means for applying an electrical quantity, proportional to the engine variable, to the network, means for applying a standard electrical quantity representing the datum value which the variable outfit to have, said quantities being compared in the net­ work so that an electrical quantity results from said comparison when the network is unbalanced, control means to which said resultant electrical quantity is applied to adjust the engine variable and means actuated by the resultant electrical quantity for increasing the unbalanced state of the network. 2,542,792. Aeroplane Wing Flap and Slat Mount- in};. James H. Bennett, Baltimore, and James A. Webb, Essex, Md., assignors to The Glenn L. Martin Company, Middle River, Md., a corporation of Maryland. Application August 16, 1947. Serial No. 769,002. 5 Claims. (CI. 244—42.) An aeroplane wing flap mounting comprising a plurality of bracket means rigidly affixed on the trailing edge of an aeroplane wing extending down­ wardly and to the rear thereof, each of said bracket means supporting an upper and lower pivot, said upper pivot being located within the wing profile and said lower pivot being located below the under side 248 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Aug 1, 1951

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