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grooves extending across said strip from one end to the other end thereof, and a number of moving blades having roots inserted in said grooves, with generally sloping deflecting baffles secured to said blades and adapted to divide said blades into at least two sections These details and drawings of patents granted in the United States are taken, by permission of the located radially outward of each other, the baffles de Department of Commerce, from the 'Official Gazette of the United States Patent Office'. Printed copies fining a generally predetermined pitch cone, and a number of moving wedge fillers bearing circumferen- of the full specifications can be obtained, price 25 cents each, from the Commissioner of Patents, tially on the stepped cylindrical strips, the fillers of Washington, D.C., U.S.A. They are usually available for inspection at the British Patent Office, successive stepped strips presenting their wedge faces in general conformity with said pitch cone and pitch Southampton Buildings, Chancery Lane, London, W.C.2. ing with the appertaining baffles of the included blades to form said tapered segment. 2,683,961. Variable Frequency Pulse Jet Engine. 2,683,005. Aeroplane with Detachable Cargo Sylvester C. Britton and Robert M. Schirmer, Compartment. Eugene C. Frost, Burbank, Calif., Bartlesville, Okla., assignors to Phillips Petroleum assignor to Lockheed Aircraft Corporation, Burbank, Company. Application May 27, 1949. Calif. Application January 18, 1951. The process of operating a jet aircraft having a jet An aeroplane and detachable suspended cargo engine containing a valve bank which stalls in the pod combination having a tricycle landing gear ar open position when the rate of pulsations in said en rangement comprising a nose landing gear carried gine exceeds a predetermined frequency, and which beneath the front end of the pod, main landing gears engine is then adapted for operation as a ram jet, said attached to the aeroplane itself, means for shifting the engine being provided with a telescopic tail pipe for ground contact point of said main landing gears from varying the length to diameter ratio and thereby behind to in front of the centre of gravity of said com varying the rate of pulsations of said engine, which bination, and a tail wheel carried by the aeroplane comprises the steps of starting said engine with the tail itself for co-operation with said main landing gears pipe in extended position, telescoping said tail pipe when the latter are shifted ahead of the centre of progressively with increasing velocity as the aircraft liquid fuel to the auxiliary burner, a liquid-operated servo-mechanism for determining the quantity of liquid fuel supplied to the auxiliary burner, control means responsive to the air pressure at the blower inlet, additional control means responsive to the gas pressure in the jet pipe between the turbine and the auxiliary burner, and a control member responsive to becomes airborne and the reaction of the jet of said the combined action of the two control means for engine increases the longitudinal velocity of said air controlling the action of said servo-mechanism. craft, and when said velocity exceeds a predetermined gravity, whereby to provide for ground manoeuvring 2,683,494. Propeller. Roland Chilton, Glen Rock, minimum velocity needed for a ram jet operation of and flight of the aeroplane component of the com N.J. Application December 24, 1949. said engine, further telescoping said tail pipe and bination when the cargo pod has been removed. thereby increasing the rate of pulsation of said engine to the point at which said valve bank stalls in open 2,683,018. Turbine Rotor with Ceramic Blades. position and said engine operates as a ram jet. Christian Schörner, Augsburg, Germany, assignor to A pulse jet engine comprising in combination a Maschinenfabrik Augsburg-Nurnberg A. G., Augs cylindrical body composed of a plurality of concentric burg, Germany. Application September 2, 1949. relatively telescopic pipes, a fuel distributor in one of Application Germany October 1, 1948. said pipes, a pulse jet valve bank controlling flow of A gas turbine adapted for high temperature opera fluids through one of said pipes, a fuel igniter in one tion comprising a steel rotor, ceramic blades mounted of said pipes, and a motor disposed and connected radially around the rim of said rotor with the inner to move said pipes in telescopic relation from an ex end of said blades disposed toward the axis of said tended relation to a contracted relation, there being at rotor, a first pair of seating surfaces at the inner ends least three of said telescopic pipes slidably connected of said blades bevelled in the direction from the axis in series, said motor comprising a hydraulic cylinder of said blades toward said inner end, a pair of corre secured to an end one of said pipes in said series, a spondingly bevelled seating surfaces in said rotor for piston slidably disposed in said cylinder, and a piston engaging said first pair of surfaces on said blades to rod secured to said piston and to the other end one of resist centrifugal force components, a second pair of said pipes in said series. seating surfaces on said blade outwardly of said first pair and adjacent said rotor rim, said second pair of 2,684,122. Helicopter Rotor Structure. John A. seating surfaces being bevelled in an opposite direc Perry, Phoenix, Ariz. Application January 24, 1952. tion from said first pair, resilient members on said rotor rim adjacent said second pair of seating sur In combination, a propeller blade having an aero faces, said resilient members having seating surfaces foil portion and a root portion for mounting in a hub socket, said portions being united by a shank of flat section disposed at right angles to a chord of said blade thereby flexible for edgewise deflexion of said blade, a cuff embracing said shank, means to con strain said cuff to rock with blade deflexion and damping means between the inboard end of said cuff and said hub. 2,683,583. Blade Attachment. George J. Huebner, Jnr., Detroit, and David M. Borden, Huntington correspondingly bevelled to said second pair for en Woods, Mich., assignors to Chrysler Corporation, gagement therewith to urge said blade outwardly from Highland Park, Michigan. Application Sept. 1, 1948. said rotor, said two pairs of oppositely directed seating In a gas turbine power plant incorporating elastic surfaces on said blade co-operating with said corre fluid utilizing apparatus having an annular flow pas spondingly bevelled surfaces in said rotor for main sage defined by the combination of a cylindrical outer taining firm and substantially vibrationless engage In a helicopter rotor structure, a vertical drive shaft, casing, a hollow rotor having a tapered segment in ment of said blade in said rotor during thermal diametrically disposed trunnions fixed on said drive the outer face, the rotor comprising a succession of expansion and axial movement of said blades with shaft, a rotor hub pivotally mounted on said trun stepped cylindrical strips on said tapered segment respect to said rotor. nions for rocking movement on the diametral axis of alternating with conjoined strips integral therewith said trunnions, a plurality of rotor blades, hinge pin having straight grooves at the periphery disposed at 2,683,349. Jet Engine Combustion System having members fixed on said rotor hub having a diametral acute angles to the length of the respective strip, said Burner in the Jet Pipe and Controlling Means Therefor. axis at right angles to and lying in the same plane with Owen Napier Lawrence, Dorridge, England, assignor the axis of said trunnions, hinge pieces pivotally to Joseph Lucas Limited, Birmingham, England. mounted on said hinge pin members for rocking Application October 27, 1950. Application Great movement about the diametral axis of said hinge pin Britain November 17, 1949. members, pivot shafts carried on said hinge pieces having substantially vertically disposed axes offset A jet-engine combustion system having in com from the axis of said hinge pin members connected bination an elongated combustion chamber, a main to support said blades to allow horizontal swinging burner in the combustion chamber, a blower for movement of said blades in a plane substantially at supplying air under pressure to one end of the com right angles to the axis of rotation of said drive shaft, bustion chamber, a turbine at the other end of the and means to secure said blades to said pivot shafts combustion chamber, a jet pipe extending from the with said blade axes located above said plane defined last mentioned end of the combustion chamber, an by said diametral axes. auxiliary burner in the jet pipe, means for supplying Aircraft Engineering
Aircraft Engineering and Aerospace Technology – Emerald Publishing
Published: Oct 1, 1954
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