Get 20M+ Full-Text Papers For Less Than $1.50/day. Start a 14-Day Trial for You and Your Team.

Learn More →

U.S. Patent Specifications

U.S. Patent Specifications lead on said turbine shaft is in the same sense as the direction of rotation so that when torque is so trans­ U.S. Patent Specifications mitted a fourth axial load is generated in said turbine shaft opposing said third axial load and so that a fifth axial load is generated in said second compressor shaft opposing said second axial load; a second pair of sets These details and drawings of patents granted in the United States are taken, by permission of the of inter-engaging helical splines, the one on said first Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies compressor shaft and the other on said second com­ pressor shaft, whereby torque can bo transmitted from of the full specifications can be obtained, price 25 cents each, from the Commissioner of Patents, said second compressor shaft to said first compressor Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, shaft and whereof the helix lead on said second com­ pressor shaft is in the same sense as the direction of Southampton Buildings, Chancery Lane, London, W.C.2. rotation so that when torque is so transmitted a sixth axial load is generated in said first compressor shaft controlling the flaps so that deflexion thereof from the 2,658,334. Braking Aircraft. Francis Charles Ivor opposing said first axial load; a first locating thrust aerodynamically neutral position takes place succes­ Marchant, Bristol, England, assignor to The Bristol bearing for said first compressor shaft; a second sively from the rearmost flap forwardly, said means Aeroplane Company Limited, Bristol, England. locating thrust bearing for said second compressor Application March 25, 1950. including means for deflecting one flap, power oper­ shaft; and a third locating thrust bearing for said ated means for deflecting the flap immediately for­ turbine shaft. ward of said one flap, means for actuating the power operated means, an electric circuit, a normally open 2,663,372. Variable Pitch Control of Helicopter switch in the circuit adapted to be closed when the Coaxial Rotors. Igor I. Sikorsky, Bridgeport, Conn., said one flap is deflected beyond a predetermined assignor to United Aircraft Corporation. Application angle relative to said power operated flap, a potentio­ May 4, 1948. meter system in the circuit energized when the switch is closed and including a potentiometer having a poten­ tiometer arm movable proportionately to the relative movement between said one flap and the power oper­ ated flap for creating an electrical signal, proportional to, and in the same sense as, the difference between the For propelling an aeroplane, a gas turbine engine comprising a compressor assemblage having a low- pressure air compressor and a high-pressure air com­ pressor, combustion equipment to receive compressed air from said compressor assemblage means to supply fuel to said combustion equipment, and a pair of in­ dependently rotatablc turbine rotors to receive in In a helicopter, a main sustaining rotor having a turn the hot products of combustion from the com­ single, large-radius variable-pitch blade, an auxiliary bustion equipment, each of said turbine rotors driving rotor having a plurality of smaller-radius variable- one of the air compressors, in combination with an pitch blades, means including an engine for driving apparatus for producing a braking thrust on the said main and auxiliary rotors at different speeds and aeroplane said apparatus comprising a combustion in opposite directions relative to each other, pilot chamber separate of the combustion equipment, means controlled means including connexions to said auxili­ for supplying fuel to said chamber, a duct to convey ary rotor blades for changing the collective pitch of the compressed air from the compressor assemblage up­ latter, and means connecting said auxiliary rotor to stream of the high-pressure stage thereof to said com­ angle of deflexion of the said one flap and the said said main rotor and responsive to aerodynamic and bustion chamber, and a nozzle from which the com­ predetermined angle, and means in the circuit for dynamic forces acting on said auxiliary rotor as a re­ bustion products arc adapted to be discharged as a collecting the signal and transmitting same to the sult of a collective pitch change imposed thereon by high velocity jet in a direction to produce said braking means for actuating the power operated flap. the pilot for controlling the pitch of said main rotor thrust. blade. 2,659,530. Hollow Drive Shaft Construction for 2,661,594. Coaxial Combustion Products Gener­ Turbine Driven Compressors. Michel Robert Gamier 2,663,493. Blading for Compressors, Turbines, and ator, Turbine, and Compressors. James Alexander and Jules Cypricn Joseph Poujade, Paris, France, the Like. Francis H. Kcast, Toronto, Ontario, Canada, Petrie, Littlcovcr, England, assignor to Rolls-Royce assignors to Socicte Nationale d'Etude et dc Con­ assignor to A. V. Roe, Canada Limited. Application Limited. Application Great Britain October 28, 1948. April 26, 1949. struction de Moteurs d'Aviation. Application July 9, A gas-turbine engine comprising a first compressor 1948. Application France July 11, 1947. casing having an inlet and outlet; a first compressor rotor in said first compressor casing and on which when in operation, a first axial load is generated; a first compressor shaft on which said first compressor rotor is mounted for rotation therewith and to which said first axial load is transmitted; a second com­ pressor casing having an inlet and an outlet; ducting from the outlet of said first compressor casing to the inlet of said second compressor casing, a second com­ pressor rotor in said second compressor casing co­ axial with said first compressor rotor and on which, when in operation, a second axial load in the same direction as said first axial load is generated; a second compressor shaft on which said second compressor rotor is mounted for rotation therewith and to which said second axial load is transmitted; a turbine casing having an inlet and an outlet; ducting from the outlet of said second compressor casing to the inlet of said turbine casing and including heating means; a turbine rotor in said turbine casing, coaxial with said first and second compressor rotors and on which when in oper­ ation a third axial load in the opposite direction to In a gas turbine a rotor, a hollow rotor shaft directly A blade for compressors, turbines and the like said first and second axial loads is generated; a turbine connected to said rotor and extending axially from having successive alternating stator and rotor elements shaft on which said turbine rotor is mounted for rota­ said rotor, a rotary compressor mounted on and con­ each carrying similar fixed blades, the said blade being tion therewith and to which said third axial load is nected to said shaft and spaced thereon from said characterized in that the leading edge at every succes­ transmitted; a first pair of sets of intcr-cngaging sive foil section radially outward from a selected point rotor, said hollow shaft having an outer solid wall, an helical splines, the one on said second compressor on the leading edge between the root and the tip is inner lining made of a material having a considerably shaft and the other on said turbine shaft, whereby displaced relatively to the leading edge at the preced­ higher coefficient of thermal conductivity than that of torque can be transmitted from said turbine shaft to ing foil section in the same sense as the local fluid flow the material forming said outer wall, said inner lining said second compressor shaft and whereof the helix in the machine midway between the said sections, and having longitudinally extending slits formed there­ the leading edge at every successive foil section out­ through at intervals throughout its length and means connecting said inner lining to said outer wall. ward from the root to the said selected point is dis­ placed relatively to the leading edge at the preceding foil section in a sense generally opposite to that of the 2,661,170. Means for Controlling Aircraft in Flight. James Arthur Chambcrlin, Toronto, Ontario, fluid flow in the machine whereby the leading edge Canada, assignor to A. V. Roc Canada Limited. configuration of the root portion will conform gener­ Application February II, 1950. ally to the leading edge configuration of the tip por­ Flight control means for an aircraft comprising a tions of the preceding adjacent blades, the angle of sweep of the leading edge of the said blade at any sec­ fixed plane surface, a plurality of flaps hinged serially tion being not substantially less than the minimum to one another, the most forward flap of the scries required to maintain subsonic flow at that section. being hinged to the fixed plane surface, and means for 136 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 (4): 1 – Apr 1, 1954

Loading next page...
 
/lp/emerald-publishing/u-s-patent-specifications-A0mpfppw91
Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032419
Publisher site
See Article on Publisher Site

Abstract

lead on said turbine shaft is in the same sense as the direction of rotation so that when torque is so trans­ U.S. Patent Specifications mitted a fourth axial load is generated in said turbine shaft opposing said third axial load and so that a fifth axial load is generated in said second compressor shaft opposing said second axial load; a second pair of sets These details and drawings of patents granted in the United States are taken, by permission of the of inter-engaging helical splines, the one on said first Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies compressor shaft and the other on said second com­ pressor shaft, whereby torque can bo transmitted from of the full specifications can be obtained, price 25 cents each, from the Commissioner of Patents, said second compressor shaft to said first compressor Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, shaft and whereof the helix lead on said second com­ pressor shaft is in the same sense as the direction of Southampton Buildings, Chancery Lane, London, W.C.2. rotation so that when torque is so transmitted a sixth axial load is generated in said first compressor shaft controlling the flaps so that deflexion thereof from the 2,658,334. Braking Aircraft. Francis Charles Ivor opposing said first axial load; a first locating thrust aerodynamically neutral position takes place succes­ Marchant, Bristol, England, assignor to The Bristol bearing for said first compressor shaft; a second sively from the rearmost flap forwardly, said means Aeroplane Company Limited, Bristol, England. locating thrust bearing for said second compressor Application March 25, 1950. including means for deflecting one flap, power oper­ shaft; and a third locating thrust bearing for said ated means for deflecting the flap immediately for­ turbine shaft. ward of said one flap, means for actuating the power operated means, an electric circuit, a normally open 2,663,372. Variable Pitch Control of Helicopter switch in the circuit adapted to be closed when the Coaxial Rotors. Igor I. Sikorsky, Bridgeport, Conn., said one flap is deflected beyond a predetermined assignor to United Aircraft Corporation. Application angle relative to said power operated flap, a potentio­ May 4, 1948. meter system in the circuit energized when the switch is closed and including a potentiometer having a poten­ tiometer arm movable proportionately to the relative movement between said one flap and the power oper­ ated flap for creating an electrical signal, proportional to, and in the same sense as, the difference between the For propelling an aeroplane, a gas turbine engine comprising a compressor assemblage having a low- pressure air compressor and a high-pressure air com­ pressor, combustion equipment to receive compressed air from said compressor assemblage means to supply fuel to said combustion equipment, and a pair of in­ dependently rotatablc turbine rotors to receive in In a helicopter, a main sustaining rotor having a turn the hot products of combustion from the com­ single, large-radius variable-pitch blade, an auxiliary bustion equipment, each of said turbine rotors driving rotor having a plurality of smaller-radius variable- one of the air compressors, in combination with an pitch blades, means including an engine for driving apparatus for producing a braking thrust on the said main and auxiliary rotors at different speeds and aeroplane said apparatus comprising a combustion in opposite directions relative to each other, pilot chamber separate of the combustion equipment, means controlled means including connexions to said auxili­ for supplying fuel to said chamber, a duct to convey ary rotor blades for changing the collective pitch of the compressed air from the compressor assemblage up­ latter, and means connecting said auxiliary rotor to stream of the high-pressure stage thereof to said com­ angle of deflexion of the said one flap and the said said main rotor and responsive to aerodynamic and bustion chamber, and a nozzle from which the com­ predetermined angle, and means in the circuit for dynamic forces acting on said auxiliary rotor as a re­ bustion products arc adapted to be discharged as a collecting the signal and transmitting same to the sult of a collective pitch change imposed thereon by high velocity jet in a direction to produce said braking means for actuating the power operated flap. the pilot for controlling the pitch of said main rotor thrust. blade. 2,659,530. Hollow Drive Shaft Construction for 2,661,594. Coaxial Combustion Products Gener­ Turbine Driven Compressors. Michel Robert Gamier 2,663,493. Blading for Compressors, Turbines, and ator, Turbine, and Compressors. James Alexander and Jules Cypricn Joseph Poujade, Paris, France, the Like. Francis H. Kcast, Toronto, Ontario, Canada, Petrie, Littlcovcr, England, assignor to Rolls-Royce assignors to Socicte Nationale d'Etude et dc Con­ assignor to A. V. Roe, Canada Limited. Application Limited. Application Great Britain October 28, 1948. April 26, 1949. struction de Moteurs d'Aviation. Application July 9, A gas-turbine engine comprising a first compressor 1948. Application France July 11, 1947. casing having an inlet and outlet; a first compressor rotor in said first compressor casing and on which when in operation, a first axial load is generated; a first compressor shaft on which said first compressor rotor is mounted for rotation therewith and to which said first axial load is transmitted; a second com­ pressor casing having an inlet and an outlet; ducting from the outlet of said first compressor casing to the inlet of said second compressor casing, a second com­ pressor rotor in said second compressor casing co­ axial with said first compressor rotor and on which, when in operation, a second axial load in the same direction as said first axial load is generated; a second compressor shaft on which said second compressor rotor is mounted for rotation therewith and to which said second axial load is transmitted; a turbine casing having an inlet and an outlet; ducting from the outlet of said second compressor casing to the inlet of said turbine casing and including heating means; a turbine rotor in said turbine casing, coaxial with said first and second compressor rotors and on which when in oper­ ation a third axial load in the opposite direction to In a gas turbine a rotor, a hollow rotor shaft directly A blade for compressors, turbines and the like said first and second axial loads is generated; a turbine connected to said rotor and extending axially from having successive alternating stator and rotor elements shaft on which said turbine rotor is mounted for rota­ said rotor, a rotary compressor mounted on and con­ each carrying similar fixed blades, the said blade being tion therewith and to which said third axial load is nected to said shaft and spaced thereon from said characterized in that the leading edge at every succes­ transmitted; a first pair of sets of intcr-cngaging sive foil section radially outward from a selected point rotor, said hollow shaft having an outer solid wall, an helical splines, the one on said second compressor on the leading edge between the root and the tip is inner lining made of a material having a considerably shaft and the other on said turbine shaft, whereby displaced relatively to the leading edge at the preced­ higher coefficient of thermal conductivity than that of torque can be transmitted from said turbine shaft to ing foil section in the same sense as the local fluid flow the material forming said outer wall, said inner lining said second compressor shaft and whereof the helix in the machine midway between the said sections, and having longitudinally extending slits formed there­ the leading edge at every successive foil section out­ through at intervals throughout its length and means connecting said inner lining to said outer wall. ward from the root to the said selected point is dis­ placed relatively to the leading edge at the preceding foil section in a sense generally opposite to that of the 2,661,170. Means for Controlling Aircraft in Flight. James Arthur Chambcrlin, Toronto, Ontario, fluid flow in the machine whereby the leading edge Canada, assignor to A. V. Roc Canada Limited. configuration of the root portion will conform gener­ Application February II, 1950. ally to the leading edge configuration of the tip por­ Flight control means for an aircraft comprising a tions of the preceding adjacent blades, the angle of sweep of the leading edge of the said blade at any sec­ fixed plane surface, a plurality of flaps hinged serially tion being not substantially less than the minimum to one another, the most forward flap of the scries required to maintain subsonic flow at that section. being hinged to the fixed plane surface, and means for 136 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Apr 1, 1954

There are no references for this article.