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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. 2,689,680. Means for Regulating the Character­ with its frame member disposed substantially parallel istics of Multistage Axial-Flow Compressors. Alfred to and adjacent the tank and the edges of the skin in approximate abutment with the tank on opposite Cyril Lovesey, Littleover, England, assignor to Rolls- to Dowty Equipment Limited, Cheltenham, England. sides of said frame member, scaling means carried by Royce Limited, Derby, England. Application June 15, Application July 1, 1952. the edges of the skin and organized and arranged to 1950. Application Great Britain June 16, 1949. sealingly engage the tank, and means of attachment A burner gallery assembly for the combustion disposed between the tank and the frame member chamber of a gas turbine engine, comprising a plurality whereby the latter may be secured to the former said of spill type burners adapted to be secured separately means including means for its release and the removal to the combustion chamber therearound and to pro­ of the fin from the tank. ject therein, said spill burners having supply and spill ducts formed therein, a plurality of junction boxes adapted to be attached to the combustion chamber, said junction boxes including one for each burner 2,689,696. Freight Carrying Aircraft. Frank Alfred Gannon, Kogarah, Sydney, New South Wales, secured thereto and one adapted to be connected with Australia, assignor of one-half to Blackburn and both fuel supply and return conduits, a large diameter General Aircraft, Limited, Brough, England. Applica­ pipe socket at each end of said junction box, said pipe tion November 26, 1951. Application Great Britain sockets being connected together and having one A multi-stage axial-flow compressor having an inner October 3, 1951. branch connexion with one duct of the burner secured duct wall and an outer duct wall defining an annular thereto, and each large diameter pipe socket further compressor duct between them, and an inlet row of being arranged to lie co-axial with the opposite pipe stator blades each of which extends the whole way socket on the adjacent junction box, a small diameter across said compressor duct and each of which com­ pipe socket at the base of each large diameter pipe prises a plurality of relatively adjustable parts mounted socket, said small diameter pipe sockets being con­ for relative adjustment about an axis substantially nected together and having a second branch connexion radial to the axis of rotation of the compressor. with the other duct of the burner secured thereto, a straight and rigid large diameter connecting pipe held 2,689,681. Reversely Rotating Screw TypeMultiple captively by the opposite large diameter pipe sockets Impeller Compressor. Andrew Sabatiuk, New Britain, in each adjacent pair of junction boxes, a straight and Conn., assignor to United Aircraft Corporation, East rigid small diameter connecting pipe held captively An aircraft of the class described comprising: a Hartford, Conn. Application September 17, 1949. by the opposite small diameter pipe sockets in each fuselage; wall means forming a part of said fuselage adjacent pair of junction boxes, both large and small and defining a freight compartment; a detachable diameter pipes entering their respective sockets with bottom wall member connected to said fuselage and both radial and axial clearance, and flexible sealing forming a floor for said freight compartment; and at means interposed between each pipe socket and the least one end door included in said wall means through pipe end held therein and adapted to provide a non- which cargo supported on said freight compartment rigid scaling engagement therebetween. floor may be moved in and out of said fuselage by longitudinal movement of said bottom wall member 2,690,810. Aircraft Propeller. Robert Doussain, when said bottom wall member is detached. Vitry-sur-Seine, Robert Bousson, Lyon, and Louis Perrier, Arnouville-les-Gonesses, France, assignors to Office National d'Etudes et de Recherches Aero- A compressor comprising a casing structure having 2,690,314. Long-Range Guided Athodyd. Henry nautiques, Paris, France. Application July 15, 1948. an annular substantially unobstructed airflow passage, H. Porter, Washington, D.C., and Robert J. Vicars, Application France July 31, 1947. a plurality of compressor rotors journalled axially in Silver Spring, Md., assignors to the United States of said casing structure, blading carried by each of said An aircraft propeller comprising a blade and a America as represented by the Secretary of the Navy. rotors and extending across said passage, means for blade carrying member, an anehor plate forming an Application December 15, 1949. rotating each successive downstream rotor at pro­ extension of said blade carrying member, a recess in portionally lower rotational speed and in a direction the root of the blade for receiving said anchor plate, opposite to its preceding rotor, said blades having a a resilient packing interposed between said anchor thickness which reduces toward their trailing edges plate and said blade, and a plurality of assembling for at least a distance from mid-chord to said trailing elements extending through said blade and said an­ edges thereby forming diverging passages there­ chor plate to secure the latter within said recess there­ between so as to impart a normal shock to the gaseous by allowing slight radial and axial displacements of medium entering said blades to provide an immediate said blade with respect to the propeller axis, said reduction in the velocity of said medium relative to assembling elements being constituted by studbolts said rotor blades and thereby effecting an immediate comprising each an axle, two bevelled disks mounted increase in pressure of said medium. thereon and bearing on bevelled scats of the same con- icity adjacent to a bore into which said stud-bolt is A ramjet vehicle comprising an outer body having 2,689,698. Fin Construction and Mounting and extended, at least one resilient member interposed a forward ram opening, an inner body secured within Attaching Means. George E. Agnew, Cold Spring between the disks and the ends of the axle and allow said outer body, said inner and outer body defining Harbour, N.Y., assignor to Republic Aviation Cor­ ing a longitudinal displacement of the assembly along a ram channel therebetween, a combustion chamber poration, near Farmingdale, N.Y. Application No­ its axis, a radially yielding barrel mounted on the axle in said vehicle, a plurality of fuel tanks in said inner vember 1, 1949. in longitudinally rigid connexion therewith, and a resi­ body, said tanks being located symmetrically with lient muff interposed between the axle and the barrel The combination with an external storage tank for respect to the centre of gravity of said vehicle, a so as to leave to the assembly a certain freedom to an aircraft, of a fin comprising an internal frame plurality of compartments in each of said tanks, a move normally to the axis of said stud-bolt. member and a skin enveloping said frame member, common fuel conduit concurrently conveying fuel said fin being adapted to be mounted on said tank from each of said tanks to said combustion chamber, pressurizing means supplying fluid under pressure to each of said tanks, the pressure being supplied to the tank compartments most remote from the common fuel outlet, and connexions between the sequential compartments of each individual tank, said con­ nexions including a pipe extending from the bottom of the more remote compartment to the top of the next compartment in sequence whereby the compart­ ments are emptied in the order of the greatest remote­ ness from the centre of gravity of said vehicle. 2,690,648. Means for Conducting the Flow of Liquid Fuel for Feeding Burners of Gas Turbine Engines. Alfred W. Pearce, Yate, near Bristol, and Alan G. Hiscox, Hatherley, Cheltenham, England, assignors 32 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 27 (1): 1 – Jan 1, 1955

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032520
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. 2,689,680. Means for Regulating the Character­ with its frame member disposed substantially parallel istics of Multistage Axial-Flow Compressors. Alfred to and adjacent the tank and the edges of the skin in approximate abutment with the tank on opposite Cyril Lovesey, Littleover, England, assignor to Rolls- to Dowty Equipment Limited, Cheltenham, England. sides of said frame member, scaling means carried by Royce Limited, Derby, England. Application June 15, Application July 1, 1952. the edges of the skin and organized and arranged to 1950. Application Great Britain June 16, 1949. sealingly engage the tank, and means of attachment A burner gallery assembly for the combustion disposed between the tank and the frame member chamber of a gas turbine engine, comprising a plurality whereby the latter may be secured to the former said of spill type burners adapted to be secured separately means including means for its release and the removal to the combustion chamber therearound and to pro­ of the fin from the tank. ject therein, said spill burners having supply and spill ducts formed therein, a plurality of junction boxes adapted to be attached to the combustion chamber, said junction boxes including one for each burner 2,689,696. Freight Carrying Aircraft. Frank Alfred Gannon, Kogarah, Sydney, New South Wales, secured thereto and one adapted to be connected with Australia, assignor of one-half to Blackburn and both fuel supply and return conduits, a large diameter General Aircraft, Limited, Brough, England. Applica­ pipe socket at each end of said junction box, said pipe tion November 26, 1951. Application Great Britain sockets being connected together and having one A multi-stage axial-flow compressor having an inner October 3, 1951. branch connexion with one duct of the burner secured duct wall and an outer duct wall defining an annular thereto, and each large diameter pipe socket further compressor duct between them, and an inlet row of being arranged to lie co-axial with the opposite pipe stator blades each of which extends the whole way socket on the adjacent junction box, a small diameter across said compressor duct and each of which com­ pipe socket at the base of each large diameter pipe prises a plurality of relatively adjustable parts mounted socket, said small diameter pipe sockets being con­ for relative adjustment about an axis substantially nected together and having a second branch connexion radial to the axis of rotation of the compressor. with the other duct of the burner secured thereto, a straight and rigid large diameter connecting pipe held 2,689,681. Reversely Rotating Screw TypeMultiple captively by the opposite large diameter pipe sockets Impeller Compressor. Andrew Sabatiuk, New Britain, in each adjacent pair of junction boxes, a straight and Conn., assignor to United Aircraft Corporation, East rigid small diameter connecting pipe held captively An aircraft of the class described comprising: a Hartford, Conn. Application September 17, 1949. by the opposite small diameter pipe sockets in each fuselage; wall means forming a part of said fuselage adjacent pair of junction boxes, both large and small and defining a freight compartment; a detachable diameter pipes entering their respective sockets with bottom wall member connected to said fuselage and both radial and axial clearance, and flexible sealing forming a floor for said freight compartment; and at means interposed between each pipe socket and the least one end door included in said wall means through pipe end held therein and adapted to provide a non- which cargo supported on said freight compartment rigid scaling engagement therebetween. floor may be moved in and out of said fuselage by longitudinal movement of said bottom wall member 2,690,810. Aircraft Propeller. Robert Doussain, when said bottom wall member is detached. Vitry-sur-Seine, Robert Bousson, Lyon, and Louis Perrier, Arnouville-les-Gonesses, France, assignors to Office National d'Etudes et de Recherches Aero- A compressor comprising a casing structure having 2,690,314. Long-Range Guided Athodyd. Henry nautiques, Paris, France. Application July 15, 1948. an annular substantially unobstructed airflow passage, H. Porter, Washington, D.C., and Robert J. Vicars, Application France July 31, 1947. a plurality of compressor rotors journalled axially in Silver Spring, Md., assignors to the United States of said casing structure, blading carried by each of said An aircraft propeller comprising a blade and a America as represented by the Secretary of the Navy. rotors and extending across said passage, means for blade carrying member, an anehor plate forming an Application December 15, 1949. rotating each successive downstream rotor at pro­ extension of said blade carrying member, a recess in portionally lower rotational speed and in a direction the root of the blade for receiving said anchor plate, opposite to its preceding rotor, said blades having a a resilient packing interposed between said anchor thickness which reduces toward their trailing edges plate and said blade, and a plurality of assembling for at least a distance from mid-chord to said trailing elements extending through said blade and said an­ edges thereby forming diverging passages there­ chor plate to secure the latter within said recess there­ between so as to impart a normal shock to the gaseous by allowing slight radial and axial displacements of medium entering said blades to provide an immediate said blade with respect to the propeller axis, said reduction in the velocity of said medium relative to assembling elements being constituted by studbolts said rotor blades and thereby effecting an immediate comprising each an axle, two bevelled disks mounted increase in pressure of said medium. thereon and bearing on bevelled scats of the same con- icity adjacent to a bore into which said stud-bolt is A ramjet vehicle comprising an outer body having 2,689,698. Fin Construction and Mounting and extended, at least one resilient member interposed a forward ram opening, an inner body secured within Attaching Means. George E. Agnew, Cold Spring between the disks and the ends of the axle and allow said outer body, said inner and outer body defining Harbour, N.Y., assignor to Republic Aviation Cor­ ing a longitudinal displacement of the assembly along a ram channel therebetween, a combustion chamber poration, near Farmingdale, N.Y. Application No­ its axis, a radially yielding barrel mounted on the axle in said vehicle, a plurality of fuel tanks in said inner vember 1, 1949. in longitudinally rigid connexion therewith, and a resi­ body, said tanks being located symmetrically with lient muff interposed between the axle and the barrel The combination with an external storage tank for respect to the centre of gravity of said vehicle, a so as to leave to the assembly a certain freedom to an aircraft, of a fin comprising an internal frame plurality of compartments in each of said tanks, a move normally to the axis of said stud-bolt. member and a skin enveloping said frame member, common fuel conduit concurrently conveying fuel said fin being adapted to be mounted on said tank from each of said tanks to said combustion chamber, pressurizing means supplying fluid under pressure to each of said tanks, the pressure being supplied to the tank compartments most remote from the common fuel outlet, and connexions between the sequential compartments of each individual tank, said con­ nexions including a pipe extending from the bottom of the more remote compartment to the top of the next compartment in sequence whereby the compart­ ments are emptied in the order of the greatest remote­ ness from the centre of gravity of said vehicle. 2,690,648. Means for Conducting the Flow of Liquid Fuel for Feeding Burners of Gas Turbine Engines. Alfred W. Pearce, Yate, near Bristol, and Alan G. Hiscox, Hatherley, Cheltenham, England, assignors 32 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Jan 1, 1955

There are no references for this article.