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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. 2,665,859. Aircraft with Rotary and Fixed Wings. Peter James Papadakos, Brooklyn, N.Y., assignor to Gyrodyne Company of America, Inc. Application 2,663,994. Engine Starter System. Adrian Albert December 19, 1950. Lombard, Allestree, Derby, and Donald Hamilton Mattinson, Derby, England, assignors to Rolls-Royce Limited. Application October 11, 1952. Application Aircraft comprising a fuselage, fixed wings project­ Great Britain October 26, 1951. ing laterally from the fuselage, engines carried on said wings and spaced from the fuselage, propellers A starter system for an aircraft gas-turbine engine for forward propulsion associated respectively with comprising a starter motor and a gear mechanism con­ and adapted to be driven by said engines, a rotor nected between the starter motor and the engine head surmounting the fuselage and comprising axially whereby during starting the motor drives a turbine/ spaced, contrarotating coaxial rotors, coaxial shafts compressor rotor assembly of the engine, which gear carrying said rotors and extending downwardly from defining a primary combustion zone, and means for mechanism comprises a first gear train giving a first the rotors, a central transmission connected to said injecting fuel into said zone, said baffle being apertured ratio of motor rotational speed to rotor assembly rota­ rotor shafts for driving said rotor shafts at equal speed to provide an inlet for part of said stream as primary tional speed suitable for starting under normal ground in opposite directions, a transmission unit disposed combustion air to said zone, and said flame tube hav­ adjacent and connected to each engine and a torque ing an outlet at its other end, whereby the flame tube tube connecting each of said latter transmission units defines a path for a stream of hot combustion gases; to the central transmission to provide driving con­ means for directing a layer of cooling air along the nexions between each engine and both rotors, said inside of the flame tube wall, said means comprising transmissions comprising means for selectively coup­ a tubular member enclosing the baffle and projecting ling each engine to both of said rotors and to the for a short distance into the end of the flame tube and propeller associated with the engine. defining therewith an annular gap providing a path from the casing into the flame tube for a stream of cooling air, the gap being so dimensioned in relation to the conditions inside and outside the flame tube in the conditions of operation, that the velocity of said 2,666,291. Jet Pipe having a Discharge End Por­ stream of cooling air through the gap is substantially tion of Variable Cross Sectional Area. Jan Skorecki, the same as the velocity of said stream of hot com­ conditions and a second gear train giving a second Burnley, England, assignor to Joseph Lucas Limited. bustion gases. ratio less than the first ratio and suitable for starting Application December 19, 1950. the engine in flight, and means for selecting the desired gear train. 2,665,085. Selective Dual Aileron Control for Air­ craft. Frederick F. Crocombe, Gerrard's Cross, Eng­ 2,664,700. Jet Propelled Aircraft Tail Unit. land, and Geoffrey T. Hill, Londonderry, Northern Edmond Benoit, Paris, France, assignor to Office Ireland, assignors to Blackburn & General Aircraft National d'Etudes et de Recherches Aeronautiques Limited. Original application June 13, 1950. Divided (O.N.E.R.A.). Application November 12, 1948. and this application November 27, 1951. Application France March 20, 1948. In a jet propulsion plant, in combination, a jet Means for exerting pressure on the exterior of a nozzle having its rear part shaped to constitute at least longitudinally corrugated and elastically deformable two flat branches located in planes parallel to the axis discharge end portion of a jet tube to reduce the cross of said nozzle and making together a dihedral angle, sectional area thereof in the vicinity of at least the said branches including a fixed central portion and a outer end thereof, comprising in combination at least one chain of annular form for embracing said end por­ tion, said chain being composed of links having pin- and-slot connexions there-between to render said chain contractible, a fixed annular housing of trough- like form containing said chain, at least one flexible cable embracing said chain for effecting contraction thereof, and guide means connecting said links to said housing whilst allowing radial movement of said links relatively to said housing. An aircraft having an aileron control system, said aircraft having pivotally mounted wings displaceable between a slow speed position extending substantially normal to the centre line of the aircraft and a high 2,666,603. Balanced Control Surface. Edward J. speed swept back position at an acute angle with re­ Horkey, Rolling Hills, Calif., assignor to North spect to said centre line, said aircraft having pivotally American Aviation, Inc. Application January 3, mounted wing-tip ailerons for use with said wings in said high speed position and trailing edge ailerons in said wings for use with said wings in said low speed movable marginal section slidable on said fixed por­ position, said control system comprising: aileron tion, and means for controlling the position of said control means operable by a pilot of said aircraft; marginal portion with respect to said fixed portion. wing-tip aileron control means connected to vary the position of said wing tip ailerons; trailing edge aileron control means connected to vary the position of said 2,664,702. Cooled Flame Tube. Peter Lloyd, Farn- trailing edge ailerons; linkage means interconnecting ham, Walter Frederick Shilling, Woking, John said pilot operable aileron control means, said wing- Brown, Highfields, and Raymond Arthur Boulter, tip aileron control means and said trailing edge aileron Great Yarmouth, England, assignors to Power Jets control means and disposed selectively to connect The combination with an aerofoil, a control surface (Research and Development) Limited. Application either said wing tip aileron control means or said hingedly mounted thereon and forming a gap there­ July 29, 1948. Application Great Britain August 11, trailing edge aileron control means for control by said with and a pressure balance system co-operatively pilot operable aileron control means; and means re­ connected between said aerofoil and said control sur­ sponsive to the position of said wings and connected face, of means arranged for actuation by said control In combustion apparatus in which fuel is to be to said linkage means for rendering said selective con­ surface and including a vane element movably carried burnt in a fast-moving airstream, and comprising an nexion effective with respect to said wing tip ailerons upon said aerofoil for increasing the gap between said outer tubular casing having an inlet for the stream, with said wings in said high speed position and effec­ aerofoil and said control surface on the negative a tubular flame tube within the casing, a hollow tive with respect to said trailing edge ailerons with said pressure side of the displaced control surface as said baffle centrally located in one end of the flame tube wings in said low speed position. control surface is displaced. 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 26 (5): 1 – May 1, 1954
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032431
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 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. 2,665,859. Aircraft with Rotary and Fixed Wings. Peter James Papadakos, Brooklyn, N.Y., assignor to Gyrodyne Company of America, Inc. Application 2,663,994. Engine Starter System. Adrian Albert December 19, 1950. Lombard, Allestree, Derby, and Donald Hamilton Mattinson, Derby, England, assignors to Rolls-Royce Limited. Application October 11, 1952. Application Aircraft comprising a fuselage, fixed wings project­ Great Britain October 26, 1951. ing laterally from the fuselage, engines carried on said wings and spaced from the fuselage, propellers A starter system for an aircraft gas-turbine engine for forward propulsion associated respectively with comprising a starter motor and a gear mechanism con­ and adapted to be driven by said engines, a rotor nected between the starter motor and the engine head surmounting the fuselage and comprising axially whereby during starting the motor drives a turbine/ spaced, contrarotating coaxial rotors, coaxial shafts compressor rotor assembly of the engine, which gear carrying said rotors and extending downwardly from defining a primary combustion zone, and means for mechanism comprises a first gear train giving a first the rotors, a central transmission connected to said injecting fuel into said zone, said baffle being apertured ratio of motor rotational speed to rotor assembly rota­ rotor shafts for driving said rotor shafts at equal speed to provide an inlet for part of said stream as primary tional speed suitable for starting under normal ground in opposite directions, a transmission unit disposed combustion air to said zone, and said flame tube hav­ adjacent and connected to each engine and a torque ing an outlet at its other end, whereby the flame tube tube connecting each of said latter transmission units defines a path for a stream of hot combustion gases; to the central transmission to provide driving con­ means for directing a layer of cooling air along the nexions between each engine and both rotors, said inside of the flame tube wall, said means comprising transmissions comprising means for selectively coup­ a tubular member enclosing the baffle and projecting ling each engine to both of said rotors and to the for a short distance into the end of the flame tube and propeller associated with the engine. defining therewith an annular gap providing a path from the casing into the flame tube for a stream of cooling air, the gap being so dimensioned in relation to the conditions inside and outside the flame tube in the conditions of operation, that the velocity of said 2,666,291. Jet Pipe having a Discharge End Por­ stream of cooling air through the gap is substantially tion of Variable Cross Sectional Area. Jan Skorecki, the same as the velocity of said stream of hot com­ conditions and a second gear train giving a second Burnley, England, assignor to Joseph Lucas Limited. bustion gases. ratio less than the first ratio and suitable for starting Application December 19, 1950. the engine in flight, and means for selecting the desired gear train. 2,665,085. Selective Dual Aileron Control for Air­ craft. Frederick F. Crocombe, Gerrard's Cross, Eng­ 2,664,700. Jet Propelled Aircraft Tail Unit. land, and Geoffrey T. Hill, Londonderry, Northern Edmond Benoit, Paris, France, assignor to Office Ireland, assignors to Blackburn & General Aircraft National d'Etudes et de Recherches Aeronautiques Limited. Original application June 13, 1950. Divided (O.N.E.R.A.). Application November 12, 1948. and this application November 27, 1951. Application France March 20, 1948. In a jet propulsion plant, in combination, a jet Means for exerting pressure on the exterior of a nozzle having its rear part shaped to constitute at least longitudinally corrugated and elastically deformable two flat branches located in planes parallel to the axis discharge end portion of a jet tube to reduce the cross of said nozzle and making together a dihedral angle, sectional area thereof in the vicinity of at least the said branches including a fixed central portion and a outer end thereof, comprising in combination at least one chain of annular form for embracing said end por­ tion, said chain being composed of links having pin- and-slot connexions there-between to render said chain contractible, a fixed annular housing of trough- like form containing said chain, at least one flexible cable embracing said chain for effecting contraction thereof, and guide means connecting said links to said housing whilst allowing radial movement of said links relatively to said housing. An aircraft having an aileron control system, said aircraft having pivotally mounted wings displaceable between a slow speed position extending substantially normal to the centre line of the aircraft and a high 2,666,603. Balanced Control Surface. Edward J. speed swept back position at an acute angle with re­ Horkey, Rolling Hills, Calif., assignor to North spect to said centre line, said aircraft having pivotally American Aviation, Inc. Application January 3, mounted wing-tip ailerons for use with said wings in said high speed position and trailing edge ailerons in said wings for use with said wings in said low speed movable marginal section slidable on said fixed por­ position, said control system comprising: aileron tion, and means for controlling the position of said control means operable by a pilot of said aircraft; marginal portion with respect to said fixed portion. wing-tip aileron control means connected to vary the position of said wing tip ailerons; trailing edge aileron control means connected to vary the position of said 2,664,702. Cooled Flame Tube. Peter Lloyd, Farn- trailing edge ailerons; linkage means interconnecting ham, Walter Frederick Shilling, Woking, John said pilot operable aileron control means, said wing- Brown, Highfields, and Raymond Arthur Boulter, tip aileron control means and said trailing edge aileron Great Yarmouth, England, assignors to Power Jets control means and disposed selectively to connect The combination with an aerofoil, a control surface (Research and Development) Limited. Application either said wing tip aileron control means or said hingedly mounted thereon and forming a gap there­ July 29, 1948. Application Great Britain August 11, trailing edge aileron control means for control by said with and a pressure balance system co-operatively pilot operable aileron control means; and means re­ connected between said aerofoil and said control sur­ sponsive to the position of said wings and connected face, of means arranged for actuation by said control In combustion apparatus in which fuel is to be to said linkage means for rendering said selective con­ surface and including a vane element movably carried burnt in a fast-moving airstream, and comprising an nexion effective with respect to said wing tip ailerons upon said aerofoil for increasing the gap between said outer tubular casing having an inlet for the stream, with said wings in said high speed position and effec­ aerofoil and said control surface on the negative a tubular flame tube within the casing, a hollow tive with respect to said trailing edge ailerons with said pressure side of the displaced control surface as said baffle centrally located in one end of the flame tube wings in said low speed position. control surface is displaced. Aircraft Engineering

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: May 1, 1954

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