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U.S. Patent Specifications

U.S. Patent Specifications AIRCRAF T ENGINEERING August, 1937 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,077,538 . Exhaust Gas Analyse r for Auto ­ polygon, control levers on said shafts extending motiv e Vehicles. Louis S. Wait, Seattle, Wash., toward s the inside of said polygon, pairs of co-axial assignor to Boeing Aircraft Company, Seattle, bearings supporting said shafts and positioned adjacent the corners of said polygon, and a movably Wash., a corporation of Washington. Application mounte d control element in symmetric relation to Jun e 8, 1935. Serial No. 25,692. 14 Claims. [Cl. said polygon and in operative connection with said 73-51.] levers. 14. An exhaust gas analyser, comprising a pluralit y of bleeder conduits each discharging to the 2,080,540 . Propeller. Otto Isaac, Ely, Nev. atmosphere , and arranged in scries relation, the Application August 22, 1936. Serial No. 97,450. first of which is connected to a preceding exhaust together , said means being automatically rendered 1 claim. [Class 170-163.] gas conduit between the hitter's ends, to bleed inoperative to declutch the drive and driven shafts A variable pitch propeller comprising a hub, should the engine speed fall below a predetermined internally threaded integral sockets projecting in value, permitting the rotors to autorotate, said mean s including a cylinder into which the fluid from the compressor is discharged, a piston operable in the cylinder, a lever operatively connected to the piston and movable member of the clutch structure an d spring means connected to the lever for normally holding the movable member of the clutch in an inoperative position. (herefrom a part only of its flow of exhaust gas, and the last of which is similarly connected be­ 2,080,488 . Means for De-icing Internal tween the ends of the preceding one, suction means Combustio n Engine Fuel Supply Apparatus. a t the discharge end of each bleeder conduit to Leo B. Kimball, New Haven, Conn., assignor to draw therethrough the gases bled from the pre­ Fuel Development Corporation, a corporation of ceding conduit, and analysing mechanism, the last Delaware. Application October 11, 1935. Serial bleeder conduit passing through said analysing No. 44,493. 3 claims. [Class 261-18.] mechanism. 1. A device for the purpose stated, comprising, a casing having an air intake passage, including a 2,078,854 . Boundary Layer Air Control. mixing chamber for fuel used in an internal com­ Clifford C. Jones, Washington, D.C. Application Jun e 20, 1936. Serial No. 86,425. 21 Claims. [Cl. 244-42.] opposite directions from said hub, sleeves threadedly 1. The method of modifying the absolute co- mounte d in said sockets, rotatably adjustable efficients of the lift and drag of an aerodynamic blades projecting radially from the sockets, said section while in motion, said section possessing blades including reduced inner end portions, shafts in the vicinity of its leading edge a normal atmo­ projecting into the sleeves from the inner ends of spheric pressure zone, above its upper cambered th e blades, said shafts comprising enlarged threaded surface a subatmospheric pressure zone, below its portion s adjacent the blades and threaded free end ower cambered surface a superatmospheric pressure portions, the end portions of the sleeves being zone at a higher pressure than the subatmospheric internall y stepped for providing the outer portions pressure zone and adjacent its trailing edge a of ball races, a ring threaded on the enlarged resultan t atmospheric pressure zone created by the portio n of each shaft, said ring constituting the convergence of th e airflows passing from the section inner portion of a ball race, a nu t threaded on the an d of a higher pressure than the normal pressure free end portion of each shaft and having its peripher y stepped for providing the inner portion of a ball race at the inner ends of the sleeves, ball bearings interposed between the outer and inner race portions, a ring fixed on the reduced inner portion of each blade, bearing plates interposed between the last named rings and the outer ends bustion engine and a throttle valve, a container or of the sockets, arms extending from the last named reservoir for antifreeze liquid, a conduit therefrom rings on opposite sides of the hub, and manually to said passage for supplying said liquid thereto in operable means connected to said arms for adjusting advanc e of said mixing chamber, and a pipe th e blades. connected between said mixing chamber and said zone, the steps of removing the boundary layer condui t to form a by-pass which when open will volume substantially over the entire span of said 2,082,172 . Aeroplane. Henri Mignet, Meaux, preven t the flow of said liquid through said conduit, section, from and at a point adjacent a lower pres­ France . Application April 16, 1936. Serial No. said pipe being made inoperative by the accumula­ sur e zone, compressing said removed boundary layer 74,769. In Belgium April 26, 1935. 16 claims. tion of ice in said passage and mixing chamber. volume within said section, and discharging said [Class 244-48.] compressedd boundary layer volume at a point 2,080,522 . Gyro Rotor. Edward Burke adjacen t a higher pressure zone, thereby utilising Wilford and Elliot Daland, Philadelphia, Pa. said compressed and discharged boundary layer Application September 18, 1936. Serial No. volume to remove boundary layer volume from the 101,516. 2 claims. [Class 244-18.] higher pressure zone. 2. A gyro rotor comprising a plurality of blades, shafts, constituting each the inner end of one of 2,079,217 . Auto-Cyclo-Giro. Isidor B. said blades and occupying the sides of a regular Laskowitz, Brooklyn, N.Y. Application August 10, 1933. Serial No. 684,568. 2 claims. [Class 244- 1. A flying machine which comprises, in com­ 16.] bination , a frame, two aerofoils carried by said 1. In combination, an aeroplane fuselage, a pair frame one behind the other, control means for of rotors arranged on opposite sides of th e fuselage, varyin g the incidence of the first aerofoil, control a driven shaft on which the rotors are mounted mean s for varying the incidence of the second extendin g transversely through the opposite sides aerofoil, a single operating control member for of the fuselage, an engine, a drive shaft extending simultaneously operating both of said control therefrom, a clutch interposed between the drive means , each of said control means including a an d driven shafts, an air compressor operable by plat e provided with a curved slot and a pin slidable the engine, means controlled by the fluid discharged in said slot, one of the two last mentioned parts from the compressor for actuating the clutch to being carried by said frame and the other being operatively connect the engine and rotor shafts interpoic d between said operating control member an d the aerofoil connected with said control means, * The above abstracts of patents granted in the United States said slots being so shaped that, for at least a part are taken, by permission of the Department of Commerce, from tiie of the range of variation of the incidence of the Official Gazette of the United States Patent Office. Printed copies of the full specilicalions can be obtained, price 10 cents each, from the aerofoils, a reduction of the incidence of the rear Commissioner of Patents, Washington, D.C, U.S.A. aerofoil corresponds to an increase of the incidence Except where otherwise stated, the specification is unaccompanied of the front aerofoil. by drawings if none is reproduced. 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 9 (8): 1 – Aug 1, 1937
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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb030216
Publisher site
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Abstract

AIRCRAF T ENGINEERING August, 1937 Some Recent Patents of Aeronautical Interest Granted in the U.S.A. 2,077,538 . Exhaust Gas Analyse r for Auto ­ polygon, control levers on said shafts extending motiv e Vehicles. Louis S. Wait, Seattle, Wash., toward s the inside of said polygon, pairs of co-axial assignor to Boeing Aircraft Company, Seattle, bearings supporting said shafts and positioned adjacent the corners of said polygon, and a movably Wash., a corporation of Washington. Application mounte d control element in symmetric relation to Jun e 8, 1935. Serial No. 25,692. 14 Claims. [Cl. said polygon and in operative connection with said 73-51.] levers. 14. An exhaust gas analyser, comprising a pluralit y of bleeder conduits each discharging to the 2,080,540 . Propeller. Otto Isaac, Ely, Nev. atmosphere , and arranged in scries relation, the Application August 22, 1936. Serial No. 97,450. first of which is connected to a preceding exhaust together , said means being automatically rendered 1 claim. [Class 170-163.] gas conduit between the hitter's ends, to bleed inoperative to declutch the drive and driven shafts A variable pitch propeller comprising a hub, should the engine speed fall below a predetermined internally threaded integral sockets projecting in value, permitting the rotors to autorotate, said mean s including a cylinder into which the fluid from the compressor is discharged, a piston operable in the cylinder, a lever operatively connected to the piston and movable member of the clutch structure an d spring means connected to the lever for normally holding the movable member of the clutch in an inoperative position. (herefrom a part only of its flow of exhaust gas, and the last of which is similarly connected be­ 2,080,488 . Means for De-icing Internal tween the ends of the preceding one, suction means Combustio n Engine Fuel Supply Apparatus. a t the discharge end of each bleeder conduit to Leo B. Kimball, New Haven, Conn., assignor to draw therethrough the gases bled from the pre­ Fuel Development Corporation, a corporation of ceding conduit, and analysing mechanism, the last Delaware. Application October 11, 1935. Serial bleeder conduit passing through said analysing No. 44,493. 3 claims. [Class 261-18.] mechanism. 1. A device for the purpose stated, comprising, a casing having an air intake passage, including a 2,078,854 . Boundary Layer Air Control. mixing chamber for fuel used in an internal com­ Clifford C. Jones, Washington, D.C. Application Jun e 20, 1936. Serial No. 86,425. 21 Claims. [Cl. 244-42.] opposite directions from said hub, sleeves threadedly 1. The method of modifying the absolute co- mounte d in said sockets, rotatably adjustable efficients of the lift and drag of an aerodynamic blades projecting radially from the sockets, said section while in motion, said section possessing blades including reduced inner end portions, shafts in the vicinity of its leading edge a normal atmo­ projecting into the sleeves from the inner ends of spheric pressure zone, above its upper cambered th e blades, said shafts comprising enlarged threaded surface a subatmospheric pressure zone, below its portion s adjacent the blades and threaded free end ower cambered surface a superatmospheric pressure portions, the end portions of the sleeves being zone at a higher pressure than the subatmospheric internall y stepped for providing the outer portions pressure zone and adjacent its trailing edge a of ball races, a ring threaded on the enlarged resultan t atmospheric pressure zone created by the portio n of each shaft, said ring constituting the convergence of th e airflows passing from the section inner portion of a ball race, a nu t threaded on the an d of a higher pressure than the normal pressure free end portion of each shaft and having its peripher y stepped for providing the inner portion of a ball race at the inner ends of the sleeves, ball bearings interposed between the outer and inner race portions, a ring fixed on the reduced inner portion of each blade, bearing plates interposed between the last named rings and the outer ends bustion engine and a throttle valve, a container or of the sockets, arms extending from the last named reservoir for antifreeze liquid, a conduit therefrom rings on opposite sides of the hub, and manually to said passage for supplying said liquid thereto in operable means connected to said arms for adjusting advanc e of said mixing chamber, and a pipe th e blades. connected between said mixing chamber and said zone, the steps of removing the boundary layer condui t to form a by-pass which when open will volume substantially over the entire span of said 2,082,172 . Aeroplane. Henri Mignet, Meaux, preven t the flow of said liquid through said conduit, section, from and at a point adjacent a lower pres­ France . Application April 16, 1936. Serial No. said pipe being made inoperative by the accumula­ sur e zone, compressing said removed boundary layer 74,769. In Belgium April 26, 1935. 16 claims. tion of ice in said passage and mixing chamber. volume within said section, and discharging said [Class 244-48.] compressedd boundary layer volume at a point 2,080,522 . Gyro Rotor. Edward Burke adjacen t a higher pressure zone, thereby utilising Wilford and Elliot Daland, Philadelphia, Pa. said compressed and discharged boundary layer Application September 18, 1936. Serial No. volume to remove boundary layer volume from the 101,516. 2 claims. [Class 244-18.] higher pressure zone. 2. A gyro rotor comprising a plurality of blades, shafts, constituting each the inner end of one of 2,079,217 . Auto-Cyclo-Giro. Isidor B. said blades and occupying the sides of a regular Laskowitz, Brooklyn, N.Y. Application August 10, 1933. Serial No. 684,568. 2 claims. [Class 244- 1. A flying machine which comprises, in com­ 16.] bination , a frame, two aerofoils carried by said 1. In combination, an aeroplane fuselage, a pair frame one behind the other, control means for of rotors arranged on opposite sides of th e fuselage, varyin g the incidence of the first aerofoil, control a driven shaft on which the rotors are mounted mean s for varying the incidence of the second extendin g transversely through the opposite sides aerofoil, a single operating control member for of the fuselage, an engine, a drive shaft extending simultaneously operating both of said control therefrom, a clutch interposed between the drive means , each of said control means including a an d driven shafts, an air compressor operable by plat e provided with a curved slot and a pin slidable the engine, means controlled by the fluid discharged in said slot, one of the two last mentioned parts from the compressor for actuating the clutch to being carried by said frame and the other being operatively connect the engine and rotor shafts interpoic d between said operating control member an d the aerofoil connected with said control means, * The above abstracts of patents granted in the United States said slots being so shaped that, for at least a part are taken, by permission of the Department of Commerce, from tiie of the range of variation of the incidence of the Official Gazette of the United States Patent Office. Printed copies of the full specilicalions can be obtained, price 10 cents each, from the aerofoils, a reduction of the incidence of the rear Commissioner of Patents, Washington, D.C, U.S.A. aerofoil corresponds to an increase of the incidence Except where otherwise stated, the specification is unaccompanied of the front aerofoil. by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace Technology – Emerald Publishing

Published: Aug 1, 1937

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