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Month in the Patent Office

Month in the Patent Office 296 AIRCRAFT ENGINEERING November, 1930 A Selection of the More Important Aircraft and Engine Specifications Published Recently 330,990 . Internal-combustion Engines. 13 are riveted, a sheet-metal covering 16 being piston valve 3 actuated by an aneroid device 4. riveted to the outer flanges of the booms. The Darby, M. O., Regent House, Kingsway, Lon­ The valve 3 controls the connection of passages structur e may be reinforced by channel section don, and Sidney, A. A., 22, Lodge Road, Croy­ 9, 10, with the inlet and delivery sides of the ribs 17, 18, at right-angles to the booms, fixed blower a t 12, 13, and has a longitudinal passage don. Mirch 23, 1929, No. 9425. [Class 7 (iii).] on the inside and outside of the covering. 14 which balances the valve and connects the Cylinders receiving liquid fuel.—The com­ Eithe r of these ribs may be omitted or discon­ bustion chamber of a compression-ignition tinued at certain points, the rib 18 being shown engine has a concentric truncated conical discontinued at the parts where the booms are extension E° of the combustion chamber, an secured. To keep the stress at different sec­ auxiliary combustion chamber C being provided within the extension, into which chamber the tions constant, the booms may be laminated by adding an extra thickness to either or both fuel is directly injected through a nozzle G. of the quadrantal sections where necessary. According to the Provisional Specification a wing or other structure may be built up on seven girders having hollow tubular booms formed of flanged curved strips riveted together or interlocked and braced together by channel members and gusset plates, as described in Specification 309,110. Extra thicknesses of metal are applied singly or in pairs where required. The curved strips may be formed as The auxiliary chamber C is provided with single arcs or corrugated. The ribs comprise openings D communicating with the extension upper and lower formers supporting a fabric E 6 , a deflecting portion A of the chamber being covering. arranged directly opposite the nozzle and in a position where it is subjected to the maximum 332,642 . Aircraft. Feddon, A. H . R., and hea t so tha t the fuel impinging on the deflector Bristol Aeroplane Co., Ltd., Filton House, may be vaporized or partial combustion may be Bristol. April 26, 1929, No. 13037. [Class 4.] effected. Alternative forms and constructions casing 15 of the aneroid to the blower delivery. Propelling.—A propeller shaft 4 is driven of the auxiliary chamber are described ; it may The .setting of the valve 3 to determine the from an engine shaft 3 through epicyclic reduc­ be formed by a flat perforated plate which is pressure at which the relay conies into action secured across the upper portion of the cylinder is adjusted manually by means of a ported extension, the centre of the plate being im­ sleeve 7 surrounding the valve, this sleeve perforated to provide a deflector ; or a flat being moved longitudinally by a screw 20 deflecting-plate may be held in alignment with having an arm 16 connected to the hand-lever the injection nozzle by means of a plurality of 6 of the main throttle 5. After this throttle radial heat-conducting arms formed integral has been fully opened against a stop 50, further with the deflector, these arms being bolted or movement of the lever 6 in a gated slot is otherwise secured to the wall of the extension allowed against the pressure of a spring 17, and E6. A plurality of injector nozzles with de­ this further movement adjusts the screw 20. flecting and vaporizing plates may be em­ I n a modification, the additional movement of ployed in each combustion chamber. th e lever 6 takes place laterally. In another form of apparatus, the lever 6 during a part of 332,568 . Aircraft. Bristol Aeroplane Co., its movement adjusts the regulation 25 of the Ltd., and Pollard, H. J., Filton House, Bristol. aneroid device. In a modification, the piston Feb . 21, 1929, No. 5810. [Class 4.] tion gearing 5, 6, 8, of which the sun pinion 8 valve itself may be adjusted. is connected to the gear-casing by a free-wheel Planes, construction of; framework.—An aeroplane wing or other light metal structure clutch, comprising rollers 12 engaging inclined comprises a number of girders, each constituted surfaces on a ring 10. Normally the pinion 8 is prevented from rotating by the clutch, but by a pair of oppositely-directed channel-shaped as soon as the propeller overruns the engine booms braced together with their open sides shaft the pinion 8 can rotate in the same outermost, and forming the main-strength direction as the propeller. A removable pin members of the structure, and a sheet-metal may be inserted to lock the pinion 8 when it is desired to start the engine by turning the propeller. 332,672 . Internal-combustion Engines. Taylor, W. L., and Bargman, J. F., Royal Air­ craft Establishment, South Farnborough, Hampshire. May 16, 1929, No. 15324. [Class 7 (vi).] Regulating.—In aircraft engines having means covering secured to the booms and providing a for automatically varying the opening of the closure for their open sides. The booms may throttl e valve in accordance with the discharge be formed of flanged quadrantal members pressure of the supercharging-blower, means 10 rivete d to plates 12 t o which bracing members are provided whereby the hand - actuated throttle-lever may be used to increase the super­ *These abstracts of complete specifications of Patents recently charging pressure above the normal maximum, published are specially compiled, by permission of B.M. Stationery Office, from abridgements appearing in the Patent Journal. Printed for example when taking off from the ground. copies of the full specifications can be obtained from the Patent Fig. 1 shows an auxiliary throttle 1 in the Office, 25, Southampton Buildings, London, W.C.2, price one shilling each. induction pipe controlled by a piston relay 2, Except where otherwise stated, the specification is unaccompanied th e movements of which are controlled by a by drawings if none is reproduced. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

Month in the Patent Office

Aircraft Engineering and Aerospace Technology , Volume 2 (11): 1 – Nov 1, 1930

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb029343
Publisher site
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Abstract

296 AIRCRAFT ENGINEERING November, 1930 A Selection of the More Important Aircraft and Engine Specifications Published Recently 330,990 . Internal-combustion Engines. 13 are riveted, a sheet-metal covering 16 being piston valve 3 actuated by an aneroid device 4. riveted to the outer flanges of the booms. The Darby, M. O., Regent House, Kingsway, Lon­ The valve 3 controls the connection of passages structur e may be reinforced by channel section don, and Sidney, A. A., 22, Lodge Road, Croy­ 9, 10, with the inlet and delivery sides of the ribs 17, 18, at right-angles to the booms, fixed blower a t 12, 13, and has a longitudinal passage don. Mirch 23, 1929, No. 9425. [Class 7 (iii).] on the inside and outside of the covering. 14 which balances the valve and connects the Cylinders receiving liquid fuel.—The com­ Eithe r of these ribs may be omitted or discon­ bustion chamber of a compression-ignition tinued at certain points, the rib 18 being shown engine has a concentric truncated conical discontinued at the parts where the booms are extension E° of the combustion chamber, an secured. To keep the stress at different sec­ auxiliary combustion chamber C being provided within the extension, into which chamber the tions constant, the booms may be laminated by adding an extra thickness to either or both fuel is directly injected through a nozzle G. of the quadrantal sections where necessary. According to the Provisional Specification a wing or other structure may be built up on seven girders having hollow tubular booms formed of flanged curved strips riveted together or interlocked and braced together by channel members and gusset plates, as described in Specification 309,110. Extra thicknesses of metal are applied singly or in pairs where required. The curved strips may be formed as The auxiliary chamber C is provided with single arcs or corrugated. The ribs comprise openings D communicating with the extension upper and lower formers supporting a fabric E 6 , a deflecting portion A of the chamber being covering. arranged directly opposite the nozzle and in a position where it is subjected to the maximum 332,642 . Aircraft. Feddon, A. H . R., and hea t so tha t the fuel impinging on the deflector Bristol Aeroplane Co., Ltd., Filton House, may be vaporized or partial combustion may be Bristol. April 26, 1929, No. 13037. [Class 4.] effected. Alternative forms and constructions casing 15 of the aneroid to the blower delivery. Propelling.—A propeller shaft 4 is driven of the auxiliary chamber are described ; it may The .setting of the valve 3 to determine the from an engine shaft 3 through epicyclic reduc­ be formed by a flat perforated plate which is pressure at which the relay conies into action secured across the upper portion of the cylinder is adjusted manually by means of a ported extension, the centre of the plate being im­ sleeve 7 surrounding the valve, this sleeve perforated to provide a deflector ; or a flat being moved longitudinally by a screw 20 deflecting-plate may be held in alignment with having an arm 16 connected to the hand-lever the injection nozzle by means of a plurality of 6 of the main throttle 5. After this throttle radial heat-conducting arms formed integral has been fully opened against a stop 50, further with the deflector, these arms being bolted or movement of the lever 6 in a gated slot is otherwise secured to the wall of the extension allowed against the pressure of a spring 17, and E6. A plurality of injector nozzles with de­ this further movement adjusts the screw 20. flecting and vaporizing plates may be em­ I n a modification, the additional movement of ployed in each combustion chamber. th e lever 6 takes place laterally. In another form of apparatus, the lever 6 during a part of 332,568 . Aircraft. Bristol Aeroplane Co., its movement adjusts the regulation 25 of the Ltd., and Pollard, H. J., Filton House, Bristol. aneroid device. In a modification, the piston Feb . 21, 1929, No. 5810. [Class 4.] tion gearing 5, 6, 8, of which the sun pinion 8 valve itself may be adjusted. is connected to the gear-casing by a free-wheel Planes, construction of; framework.—An aeroplane wing or other light metal structure clutch, comprising rollers 12 engaging inclined comprises a number of girders, each constituted surfaces on a ring 10. Normally the pinion 8 is prevented from rotating by the clutch, but by a pair of oppositely-directed channel-shaped as soon as the propeller overruns the engine booms braced together with their open sides shaft the pinion 8 can rotate in the same outermost, and forming the main-strength direction as the propeller. A removable pin members of the structure, and a sheet-metal may be inserted to lock the pinion 8 when it is desired to start the engine by turning the propeller. 332,672 . Internal-combustion Engines. Taylor, W. L., and Bargman, J. F., Royal Air­ craft Establishment, South Farnborough, Hampshire. May 16, 1929, No. 15324. [Class 7 (vi).] Regulating.—In aircraft engines having means covering secured to the booms and providing a for automatically varying the opening of the closure for their open sides. The booms may throttl e valve in accordance with the discharge be formed of flanged quadrantal members pressure of the supercharging-blower, means 10 rivete d to plates 12 t o which bracing members are provided whereby the hand - actuated throttle-lever may be used to increase the super­ *These abstracts of complete specifications of Patents recently charging pressure above the normal maximum, published are specially compiled, by permission of B.M. Stationery Office, from abridgements appearing in the Patent Journal. Printed for example when taking off from the ground. copies of the full specifications can be obtained from the Patent Fig. 1 shows an auxiliary throttle 1 in the Office, 25, Southampton Buildings, London, W.C.2, price one shilling each. induction pipe controlled by a piston relay 2, Except where otherwise stated, the specification is unaccompanied th e movements of which are controlled by a by drawings if none is reproduced.

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Nov 1, 1930

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