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U.S. Patent Specifications

U.S. Patent Specifications In a gas turbine power plant having fixed housing structure and a rotor mounted therein, said rotor being subjected, during turbine operation, to a pres­ sure differential imposing an axial thrust on said rotor: a thrust balancing member co-axial with said These details and drawings of patents granted in the United States are taken, by permission of the rotor; an annular shoulder on said rotor; means Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies disposed between said member and said rotor to of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, inhibit fluid flow therebetween and to provide a Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, thrust bearing between said member and said rotor Southampton Buildings, Chancery Lane, London, W.C.2. shoulder for resisting axial movement of said rotor in the direction of said axial thrust; and annular axially flexible means connecting the periphery of Application October 7, 1944. Serial No. 557,708. said member to fixed structure of said power plant 5 Claims. (CI. 287—75.) to inhibit fluid flow acioss the periphery of said member; said member being subjected, during turbine operation, to a pressure differential imposing an axial force on said member which, through said thrust bearing, is applied to said rotor shoulder to at least partially balance said axial rotor thiust. 2,541,098. Gas Turbine Propeller Apparatus. A control system comprising two cables, fitting Arnold H. Redding, Swarthmorc.-Pa., assignor to members on adjacent ends of the cables, one member Westinghouse Electric Corporation, East Pittsburgh, 2,540,335. Lateral Control Device for Aircraft. having a socket, the other member extending into the Pa., a corporation of Pennsylvania. Application June Francis B. Johnson, Burbank, California, assignor to socket, the members having aligned transverse open­ 14,1948. Serial No. 32,941.5 Claims. (CI. 170—135.7.) Consolidated Vultce Aircraft Corporation, San ings, a pin inserted in the openings to connect the Diego, California, a corporation of Delaware. members, the pin having parts projecting from the Application November 4, 1946. Serial No. 707,600. socketed member, a ring on the socketed member 8 Claims. (Cl. 244—90.) having a circumferential internal groove for receiving In combination with an aeroplane wing, an aileron, the end parts of the pin and axial grooves for admitting means hingedly connecting said aileron to said aero­ said parts to the circumferential groove, and means plane wing for upward and downward movement and for holding the ring in the angular position where locating it spaced from an edge of said wing, a wall the axial grooves are out of alignment with the pin surface of said wing co-operating with the forward so that the ring prevents displacement of the pin. end of the aileron to provide an air passage between said wing and said aileron closable upon upward 2,540,594. Ram Jet Engine Having Variable Area movement of said aileron, the axis of said hinge Inlets. Nathan C. Price, Los Angeles, California, means being disposed beneath the aileron and rear- assignor to Lockheed Aircraft Corporation, Burbank, wardly of said wing, an inverted auxiliary aerofoil, California. Application August 23, 1946. Serial No. Aircraft propulsion apparatus comprising a casing means mounting said auxiliary aerofoil to the bottom 692,423. 30 Claims. (Ci. 60—35.6.) structure, a turbine rotor mounted in said casing surface of said aileron and holding it spaced there­ structure, a plurality of radially extending propeller from to provide a Venturi air passage between said blades adapted to be carried on the peripheral portion auxiliary aerofoil and said aileron and means for of said turbine rotor, a plurality of tension members deflecting said aileron upwardly to close said first- interposed between the base portions of said blades, mentioned air passage and to place said Venturi air each of said tension members being substantially passage defined by said auxiliary aerofoil in position tangcntially aligned with relation to said turbine in the airstream to cause air to pass at an accelerated rotor and interlocked therewith, and means for rate on to said bottom surface of said aileron. securing the base portion of each blade between the abutting ends of the adjacent tension members, each base portion being clear of said turbine rotor. A reactive propulsion power plant comprising a tubular shell having a ram inlet at one end and a 2,541,429. Aircraft Balance Indicator. Frank D. propulsive nozzle at the other end, heat generating Mathes, Jr., and Walter J. Ccrny, Los Angeles, means in the shell between its ends, a member mov­ California, assignors to Northrop Aircraft, Inc., able in the inlet to control the same, means responsive Hawthorne, California, a corporation of California. to aerodynamic conditions in the ram inlet for moving Application March 26, 1949. Serial No. 83,544. the member and for controlling the heat generating 7 Claims. (CI. 73—65.) means. In a reactive propulsion engine, a tubular shell, two elements related for relative axial movement, one an inlet ram at the forward end of the shell, the other a needle arranged substantially centrally in the inlet 'ssxii "u P^ 1T and operable to reflect supersonic shock waves against 2,540,526. Internal-Combustion Turbine Power the wall of the inlet, the needle presenting an external I ■ ^©nfX Plant. Alun Raymond Howell, Neath, England, to* Difoutatl—^ 1 surface shaped to cause convergence of the shock to*******"' . ^,iy«w» assignor to Power Jets (Research and Development) waves toward the wall of the inlet, and servo-motor | 1 -£A*LAJ*C lO*/ I—' Ltd., London, England, a British company. Applica­ means sensitive to the location of substantial con­ tion January 31, 1945. Serial No. 575,535. In Great vergence of said shock waves for moving said ele­ 1 LZt 1 I ±-7r co Britain January 31, 1944. 3 Claims. (CI. 60—41.) ments axially one with respect to the other. A gas turbine aircraft power unit comprising an j ^___^____^^ . . mcio*r 2,540,902. Thrust Balancing Means. Vincent T. axial flow multistage compressor which supplies Moore, Ridgewood, N.J., assignor to Wright Aero­ motive fluid to an axial flow gas turbine which drives nautical Corporation, a corporation of New York. it, said compressor and turbine being coaxially Application November 24, 1944. Serial No. 565,022. arranged with the inlets thereto annularly disposed at 7 Claims. (Cl. 60-41.) adjacent ends and outlets at the remote ends thereof so that the flows therethrough arc in opposite direc­ In an aeroplane having a plurality of fuel tanks, tions, and with the compressor located ahead of the spaced at different distances along the length of said turbine (considered in relation to the intended direc­ aeroplane, a first electrical means on each tank tion of flight) so that the flow through the com­ variable in output in accordance with the weight of pressor is in the intended direction of flight, annularly fuel in said tank, a second electrical means on each disposed ducting leading through a turn of approxi­ tank variable in output in accordance with the mately 180 deg. in a plane including the axis of the longitudinal moment of said tank, a first electrically unit from the discharge (front) end of the compressor responsive means connected to indicate the sum of to the inlet (front) end of the turbine said ducting the output of said first electrical means, a second including heating means for the working fluid and electrically responsive means connected to indicate annularly surrounding the body and inlet end of the the sum of the output of said second electrical means, compressor and forming in the region of said inlet each of said electrically responsive means having a end circumfercntially spaced gas passages to said shaft, a scale and a pointer on said shaft traversing turbine, the spaces between said gas passages being said scale, means for mounting said electrically utilized for air entry to said inlet, whereby there is responsive means with their shafts coaxially positioned intersection of flow paths of air entering the com­ and with their scales concentric, adjacent and sub­ pressor and gas entering the turbine. stantially in a common plane, means for turning one of said electrically responsive means around the shaft axis thereof to change the relative position of 2,540,590. Control System. Ralph K. Mead and said scales, and means for indicating the change in Donald E. Slaton, Glendale, California, assignors to relative position of said scales. Lockheed Aircraft Corporation, Burbank, California. 216 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 (7): 1 – Jul 1, 1951
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032063
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Abstract

In a gas turbine power plant having fixed housing structure and a rotor mounted therein, said rotor being subjected, during turbine operation, to a pres­ sure differential imposing an axial thrust on said rotor: a thrust balancing member co-axial with said These details and drawings of patents granted in the United States are taken, by permission of the rotor; an annular shoulder on said rotor; means Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies disposed between said member and said rotor to of the full specifications can be obtained, price 10 cents each, from the Commissioner of Patents, inhibit fluid flow therebetween and to provide a Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, thrust bearing between said member and said rotor Southampton Buildings, Chancery Lane, London, W.C.2. shoulder for resisting axial movement of said rotor in the direction of said axial thrust; and annular axially flexible means connecting the periphery of Application October 7, 1944. Serial No. 557,708. said member to fixed structure of said power plant 5 Claims. (CI. 287—75.) to inhibit fluid flow acioss the periphery of said member; said member being subjected, during turbine operation, to a pressure differential imposing an axial force on said member which, through said thrust bearing, is applied to said rotor shoulder to at least partially balance said axial rotor thiust. 2,541,098. Gas Turbine Propeller Apparatus. A control system comprising two cables, fitting Arnold H. Redding, Swarthmorc.-Pa., assignor to members on adjacent ends of the cables, one member Westinghouse Electric Corporation, East Pittsburgh, 2,540,335. Lateral Control Device for Aircraft. having a socket, the other member extending into the Pa., a corporation of Pennsylvania. Application June Francis B. Johnson, Burbank, California, assignor to socket, the members having aligned transverse open­ 14,1948. Serial No. 32,941.5 Claims. (CI. 170—135.7.) Consolidated Vultce Aircraft Corporation, San ings, a pin inserted in the openings to connect the Diego, California, a corporation of Delaware. members, the pin having parts projecting from the Application November 4, 1946. Serial No. 707,600. socketed member, a ring on the socketed member 8 Claims. (Cl. 244—90.) having a circumferential internal groove for receiving In combination with an aeroplane wing, an aileron, the end parts of the pin and axial grooves for admitting means hingedly connecting said aileron to said aero­ said parts to the circumferential groove, and means plane wing for upward and downward movement and for holding the ring in the angular position where locating it spaced from an edge of said wing, a wall the axial grooves are out of alignment with the pin surface of said wing co-operating with the forward so that the ring prevents displacement of the pin. end of the aileron to provide an air passage between said wing and said aileron closable upon upward 2,540,594. Ram Jet Engine Having Variable Area movement of said aileron, the axis of said hinge Inlets. Nathan C. Price, Los Angeles, California, means being disposed beneath the aileron and rear- assignor to Lockheed Aircraft Corporation, Burbank, wardly of said wing, an inverted auxiliary aerofoil, California. Application August 23, 1946. Serial No. Aircraft propulsion apparatus comprising a casing means mounting said auxiliary aerofoil to the bottom 692,423. 30 Claims. (Ci. 60—35.6.) structure, a turbine rotor mounted in said casing surface of said aileron and holding it spaced there­ structure, a plurality of radially extending propeller from to provide a Venturi air passage between said blades adapted to be carried on the peripheral portion auxiliary aerofoil and said aileron and means for of said turbine rotor, a plurality of tension members deflecting said aileron upwardly to close said first- interposed between the base portions of said blades, mentioned air passage and to place said Venturi air each of said tension members being substantially passage defined by said auxiliary aerofoil in position tangcntially aligned with relation to said turbine in the airstream to cause air to pass at an accelerated rotor and interlocked therewith, and means for rate on to said bottom surface of said aileron. securing the base portion of each blade between the abutting ends of the adjacent tension members, each base portion being clear of said turbine rotor. A reactive propulsion power plant comprising a tubular shell having a ram inlet at one end and a 2,541,429. Aircraft Balance Indicator. Frank D. propulsive nozzle at the other end, heat generating Mathes, Jr., and Walter J. Ccrny, Los Angeles, means in the shell between its ends, a member mov­ California, assignors to Northrop Aircraft, Inc., able in the inlet to control the same, means responsive Hawthorne, California, a corporation of California. to aerodynamic conditions in the ram inlet for moving Application March 26, 1949. Serial No. 83,544. the member and for controlling the heat generating 7 Claims. (CI. 73—65.) means. In a reactive propulsion engine, a tubular shell, two elements related for relative axial movement, one an inlet ram at the forward end of the shell, the other a needle arranged substantially centrally in the inlet 'ssxii "u P^ 1T and operable to reflect supersonic shock waves against 2,540,526. Internal-Combustion Turbine Power the wall of the inlet, the needle presenting an external I ■ ^©nfX Plant. Alun Raymond Howell, Neath, England, to* Difoutatl—^ 1 surface shaped to cause convergence of the shock to*******"' . ^,iy«w» assignor to Power Jets (Research and Development) waves toward the wall of the inlet, and servo-motor | 1 -£A*LAJ*C lO*/ I—' Ltd., London, England, a British company. Applica­ means sensitive to the location of substantial con­ tion January 31, 1945. Serial No. 575,535. In Great vergence of said shock waves for moving said ele­ 1 LZt 1 I ±-7r co Britain January 31, 1944. 3 Claims. (CI. 60—41.) ments axially one with respect to the other. A gas turbine aircraft power unit comprising an j ^___^____^^ . . mcio*r 2,540,902. Thrust Balancing Means. Vincent T. axial flow multistage compressor which supplies Moore, Ridgewood, N.J., assignor to Wright Aero­ motive fluid to an axial flow gas turbine which drives nautical Corporation, a corporation of New York. it, said compressor and turbine being coaxially Application November 24, 1944. Serial No. 565,022. arranged with the inlets thereto annularly disposed at 7 Claims. (Cl. 60-41.) adjacent ends and outlets at the remote ends thereof so that the flows therethrough arc in opposite direc­ In an aeroplane having a plurality of fuel tanks, tions, and with the compressor located ahead of the spaced at different distances along the length of said turbine (considered in relation to the intended direc­ aeroplane, a first electrical means on each tank tion of flight) so that the flow through the com­ variable in output in accordance with the weight of pressor is in the intended direction of flight, annularly fuel in said tank, a second electrical means on each disposed ducting leading through a turn of approxi­ tank variable in output in accordance with the mately 180 deg. in a plane including the axis of the longitudinal moment of said tank, a first electrically unit from the discharge (front) end of the compressor responsive means connected to indicate the sum of to the inlet (front) end of the turbine said ducting the output of said first electrical means, a second including heating means for the working fluid and electrically responsive means connected to indicate annularly surrounding the body and inlet end of the the sum of the output of said second electrical means, compressor and forming in the region of said inlet each of said electrically responsive means having a end circumfercntially spaced gas passages to said shaft, a scale and a pointer on said shaft traversing turbine, the spaces between said gas passages being said scale, means for mounting said electrically utilized for air entry to said inlet, whereby there is responsive means with their shafts coaxially positioned intersection of flow paths of air entering the com­ and with their scales concentric, adjacent and sub­ pressor and gas entering the turbine. stantially in a common plane, means for turning one of said electrically responsive means around the shaft axis thereof to change the relative position of 2,540,590. Control System. Ralph K. Mead and said scales, and means for indicating the change in Donald E. Slaton, Glendale, California, assignors to relative position of said scales. Lockheed Aircraft Corporation, Burbank, California. 216 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Jul 1, 1951

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