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over-rich mixture to the reciprocating engine at altitude or to inject additional fuel into the air Month in the Patent Office delivered from the compressor 18. 610,584. Cylinders. Bristol Aeroplane Co., Ltd., These abstracts of British Patent Specifications are taken, by permission, from the officially prepared H. C. Mansell and H. N. Gorrell, April 10, 1946, No. abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, 11,064. (Class 7 (ii)) 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies of the full specifications are obtainable at the same address, price 1s. each A linkwork mechanism for operating two controls, such as the elevators and rudder of an aircraft, or two controls of a vehicle, from a single operating member comprises an articulated parallelogram 2, 3,4, 7, one side 2 carrying a handle 1 for the operator, 609,245. Controlling aircraft. G. O. Suppancic and whilst two adjacent sides 4, 7 are fixed on concentric Longitudinally-extending cooling fins 12 are G. V. Lachmann. March 8, 1946, No. 7,338. (Class 4.) actuating shafts 8, 9 for the two controls respectively. arranged in groups 19, in which the fins arc parallel to A differential control mechanism, which may be These shafts preferably carry levers 11, 10 for con one another; the fins in a group can thus be produced used for the controls of aircraft, comprises two driven nexion to the respective controls by any suitable simultaneously, e.g. machining with a gang cutter. shafts 20, 21 which are separately connected to a driv means. Actuation of the handle 1 in a direction along They are very thin and closely spaced, and associated ing shaft 22 through two universal jointed arranged in the length of the side 2 operates shaft 9 whilst actua in at least ten groups. In a sleeve-valve engine, they parallel, the out-of-phase F of the joints bearing such a tion in a transverse direction operates shaft 8. A double are interrupted at the ports 17, 18. Each exhaust or relation to the fixed angle Φ between the axes of the handle may be provided on the side 2 for a two- admission pipe is attached by a nut and a double- driving and driven shafts that a constant motion handed grip and the length of the shafts 8 and 9 may coned packing to a union 23, which is neither bolted imparted to the driving shaft produces relatively be varied as required to displace suitably the levers to a cylinder or screwed therein, and retained by a asymmetrical differential motions of the driven shafts. 10,11 from the plane of the parallelgoram. dowel-pin not shown. In one embodiment illustrated, the driving shaft 22 has integral therewith a double yoke 231, carrying pivots such as 234 on which are carried the links 26, 27 which connect through single yokes 242, 252 integral with the coaxial driven shafts 21, 20 respect ively. 610,495. Aircraft propelling plant. S. G. Hooker. April 8, 1946, No. 10807. (Class 4.) A power plant comprises a gas turbine driving a rotary air compressor delivering air at its delivery pressure to the turbine, a load driven by the turbine, the torque reaction of which is variable to enable the speed of the turbine and the delivery pressure of the compressor to be varied and a reciprocating engine driving a separate load arranged to exhaust to the gas turbine against the back pressure of the compressor 609,292. Aircraft controls. Blackburn Aircraft, delivery. In the plant shown, a gas turbine 17 which 610,695. Aircraft ventilating and de-icing systems. Ltd, P. G. E. Hand, and K. A. Whitworth. Oct. 8, drives a rotary air compressor 18 supplying air to the S. G. Hooker and H. Pearson. April 15, 1946, No. 1946, No . 29,962. (Class 4.), turbine and a variable-pitch propeller 14 is combined 11502. (Class 4.) A push-pull sliding and rockable tube 4 with an with a reciprocating engine 10 which exhausts into An aircraft is provided with means for supplying air operating handle 5 is guided by a fixed housing 3 and the pipe 19 connecting the compressor 18 and turbine to a pressure cabin and/or de-icing ducts comprising carries at the end a housing 6, within which the tube 17 and drives a separate propeller 11. The speed of the an air compressor driven by a gas-turbine taking its can rotate and which moves under control by fixed turbine 17 and, indirectly, the pressure at the discharge combustion air from the cabin and/or ducts. In the guides with the push-pull motion of the tube for of the compressor is controlled by varying the pitch of form shown in FIG. 1, a centrifugal compressor 8 operating the elevators through a pivoted lever 16 the propeller 14. Since the reciprocating engine 10 delivers air to the cabin 7 through a duct 10, the air connected by links to the housing 6. Rocking move exhausts against the back pressure of the compressor passing from the cabin to the combustion chamber or delivery, the output from this engine will also be con ment of the tube 4 for operating the ailerons is com chambers 12 of a gas-turbine 14 driving the com trolled by the pitch of the propeller 14. The pitch of municated by collapsible linkage 8, 9 connected pressor. The turbine exhaust is discharged through a the propeller 14 may be controlled by a variable- between the end of the tube and a pivoted arm 10 jet pipe 15, furnishing propulsive thrust for the air datum constant speed unit, and datum speed of which connected by levers 11, 12 to rod 14. Rudder control craft. The fuel is supplied through a pipe 13, and may may be adjusted either manually by reference to a is exerted through pedals 18 carried on pivoted be controlled by means responsive to the pressure of gauge indicating the back, pressure in the reciprocating levers 19 connected at their upper ends to triangular the cabin air and/or of the ambient air. Fio. 3 shows levers 22 on shaft 23; one of levers 22 is fast on the engine exhaust or automatically by an altitude an alternative arrangement enabling the cabin 7 to be shaft and the other is loose, each of these levers being responsive device. The arrangement is such that at ventilated while the aircraft is on the ground. A bye- connected by a link 30 to a balance lever 31 for ensur ground level the front propeller 14 is adjusted to pass duct 22 connects the duct 10 and the turbine com ing equal and opposite movements of the pedals. The maximum coarse pitch so that the turbine 17 and com bustion chamber(s) 12, valves 24, 25 being provided accompanying rotation of shaft 23 causes operation pressor 18 run at their slowest speed and lowest out in the respective ducts and operated by the cabin door of the rudder through arm 26, link- 27 and triangular put. The reciprocating engine 10 then exhausts 23, the opening of which causes closing of the valve 24 against a mimimum back pressure and develops its lever 28. The pivots 20 of levers 19 are simultaneously and opening of the valve 25. The temperature of the maximum power. As the aircraft gains altitude, the movable for adjusting the pedal positions to suit the air may be controlled by heat exchangers, while in the propeller 14 is set to a fine pitch, the turbine 17 gains pilots. case of air for cabin ventilation water injection may be speed and develops more power whilst the increase in employed to control its humidity. According to the back pressure on the reciprocating engine lessens the Provisional Specification a second stage compressor 609,412. Controlling aircraft. Soc. Nationale de power developed by it. In a modification, two or more may be provided arranged to take in air from the Constructions Acronautiques de Sud-Est. March 13, turbine-driven compressors 17, 18 are employed to cabin and deliver it to the turbine combustion cham 1946, No. 7,846. Convention date, Sept. 13, 1945. drive the propeller 14. It may be desirable to supply an bers), to augment the thrust. (Class 4.) July 1951 215
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Jul 1, 1951
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