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Month in the Patent Office

Month in the Patent Office carrying the impeller 24, a spring 77 being provided adjacent the dog clutch; the spindle 75 abuts via washer 76 with the priming valve 55. The pump 11 can thus easily be removed without disturbing the impeller 24, and in case of seizing, the shaft is arranged These abstracts of British Patent Specifications are taken, by permission, from the officially prepared to break at its weakest point between the pump and abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, impeller leaving the shaft 26 carrying the impeller 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies running undamaged. During priming, fuel is pumped by a priming pump into an inlet 10 and passes through of the full specifications are obtainable at the same address, price 1s. each. the hollow spindle 75 and valve 55 to the engine. Specifications 566,323 and 576,261 also are referred to. 603,487. Variable-pitch propellers. Armstrong Siddeley Motors, Ltd, W. H. Lindsey, and B. H. 604,728. Regulating. Cierva Autogiro Co., Ltd., Slatter. Feb. 28, 1946, No. 6,216. (Class 114.) and C. G. Pullin. Dec. 3, 1945, No. 32599. In a constant speed, variable pitch propeller an The throttle valve 15 of a helicopter engine is over-ride device is automatically brought into opera­ operated by a hand lever 16, through rods 17, 18 tion to move the blades to the feathering position connected together by a sleeve 19 having internal right when the power unit stops, and means are provided by and left-hand threads engaging corresponding threads which the over-ride is automatically put out of action 20, 21 on the rods. The sleeve 19 is secured to a lever 22 when an attempt is made to start the power unit by constituting the follower of a cam 23 which is rotated 'wind-milling', and by which the over-ride is auto­ by a pulley 24 to vary the throttle setting when a cable matically restored when the speed rises to that at which 4 is operated to vary the thrust of a torque-reaction the unit should be self-operating. When the power unit compensating jet or airscrew. stops a governor 23 allows a spring 22 to force a valve 19 to the left, thereby allowing motive fluid from a pipe 12 to flow into the left-hand end of a cylinder 16 to operate a plunger 15 which moves the propeller blades 13 to the minimum pitch position. The resultant change of torque acting on a torque meter 39 closes a switch 37 to complete an electrical circuit for actuating a solenoid 35 controlling a valve 34 which allows motive fluid to be applied from pipe 31 to the spring- segment 27 connected by a universal joint 26 with the loaded plunger 28 of the over-ride device. The plunger upper end of the rod 23. The radii of the segments are moves the valve 19 to the right, allowing fluid into the respectively greater than the distances of the joints right-hand end of cylinder 16, thereby moving the 26 and 30 from their point of contact, so that move­ blades to the feathering poistion. The circuit may also 604,991. Protective devices for aircraft. A. H. Tilt- ment of the flying control member in any direction be completed by the pilot closing the fuel isolator man, M. Langley, W. G. Glendinning and A. M. from the neutral position causes a downward move­ valve 36. To start the power unti by wind-milling, ment of the rod 23 and a rotation of the sleeve 19 to Maclennan. Dec. 11, 1945, No. 33,475. ignition switch 46 of the power unit is closed, the increase the throttle setting. Protective apparatus for aircraft, particularly for govenor controlled switch 47 being already closed. A effecting the release of extinguishing medium, the solenoid 45 then opens a switch 44 and breaks the closing of fuel cocks or the control of electric circuits 604,134. Regulating. H. M. Hobson (Aircraft and circuit to the solenoid 35 so that the valve 34 closes to •in case of a fire risk and also applicable for giving a Motor) Components, Ltd., and L. S. Greenland. Feb cut-off the supply of fluid to the over-ride plunger. warning of the incipient collapse of structural mem­ 12, 1945, No. 3,450. The spring 22 is thus able to move the valve 19 to the bers, electrical conductors or power plant components A centrifugal impeller 24 and a detachably coupled left with the result that the blades are moved from the of the aircraft, comprises a closed system of pipes 14 fuel pump 11 are built into the metering unit to reduce feathered position to cause 'wind-milling'. If at a which are secured to the members which are liable to pressure losses in the fuel lines in a fuel supply system predetermined speed the unit does not then become overstrain or collapse in use or to rupture on impact. of the type described in Specification 586,259, in which self-operating, its governor will open the switch 47 The pipes are maintained above or below atmospheric fuel under pressure is fed by the pump to a metering causing switch 44 to close to complete the circuit to pressure and are connected to a pressure-sensitive orifice whose area is dependent upon boost pressure the solenoid 35. The valve 34 will be raised to bring device 13, such as an electric switch, which operates and exhaust back pressure (or atmospheric pressure) the over-ride into operation, causing plunger 28 to the protective or warning devices shown as extin­ and in which the metering pressure is maintained move valve 19 so that the propeller blades are moved guishers 11, if the pipe system is opened to atmos­ proportional to the square of the engine speed by to the feathered position. phere. The system includes frangible bulbs 26b—26e means of the centrifugal impeller. To the front of the at exposed points which will fracture on impact, and housing 57 containing the diaphragm 16, Bourdon rupturable sections 26a and 26f which are rigidly unit 45, centrifugal impeller 24, and pressure-actuated secured to structural members so as to break if the capsules 34, 35 controlling the metering orifice 13, is member collapses or distorts. The sections may be of fitted a fuel pump body 63 containing the fuel pump brittle material anchored at each end or may consist assembly 65 located in position by a cover-plate 66 of an opening in the piping closed by a disc or plug and screwed ring 70. the pump 11 has two gear-wheels adapted to be broken or torn-out if the structural 72, 73 mounted on spindles 74, 75. The spindle 74 member distorts. The piping may normally be kept engages via a dog clutch 25 with the driving shaft 26 at a standard pressure by a compressed gas reservoir 16 or a pump connected to it by a 'bleeder' tube. The switch 13, FIG . 2, which may be replaced by a valve or other pressure-sensitive actuator, comprises contacts 21, 22 held apart by a diaphragm 18 responsive to the pressure in the piping, and closed by a spring 21a when the piping is opened. 603,844. Valve gear. Cierva Autogiro Co., Ltd. and C. G. Pullin. Oct. 31, 1945, No . 28,884. The throttle 15 of a helicopter engine is operated by a hand lever 10 through a push-pull-rod made in two parts 13, 14 having oppositely-threaded end por­ tions 17, 18 engaged by corresponding internal threads of a sleeve 19 splined to a cylindrical member 20. The latter is rotatable about the axis of the rod 13, 14 and is secured to a lever connected to a rod 23 slidable in a support 24 against the action of a spring 25. The flying control member 29 of the helicopter is univers­ ally mounted at 30 and is formed with a spherical segment 28 in rolling engagement with a similar February 1951 5 9 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 23 (2): 1 – Feb 1, 1951

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb032003
Publisher site
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Abstract

carrying the impeller 24, a spring 77 being provided adjacent the dog clutch; the spindle 75 abuts via washer 76 with the priming valve 55. The pump 11 can thus easily be removed without disturbing the impeller 24, and in case of seizing, the shaft is arranged These abstracts of British Patent Specifications are taken, by permission, from the officially prepared to break at its weakest point between the pump and abridgments classified in Groups. Sets of Group abridgments can be obtained from the Patent Office, impeller leaving the shaft 26 carrying the impeller 25 Southampton Buildings, W.C.2, sheet by sheet as issued, at a subscription of 10s. per Group. Copies running undamaged. During priming, fuel is pumped by a priming pump into an inlet 10 and passes through of the full specifications are obtainable at the same address, price 1s. each. the hollow spindle 75 and valve 55 to the engine. Specifications 566,323 and 576,261 also are referred to. 603,487. Variable-pitch propellers. Armstrong Siddeley Motors, Ltd, W. H. Lindsey, and B. H. 604,728. Regulating. Cierva Autogiro Co., Ltd., Slatter. Feb. 28, 1946, No. 6,216. (Class 114.) and C. G. Pullin. Dec. 3, 1945, No. 32599. In a constant speed, variable pitch propeller an The throttle valve 15 of a helicopter engine is over-ride device is automatically brought into opera­ operated by a hand lever 16, through rods 17, 18 tion to move the blades to the feathering position connected together by a sleeve 19 having internal right when the power unit stops, and means are provided by and left-hand threads engaging corresponding threads which the over-ride is automatically put out of action 20, 21 on the rods. The sleeve 19 is secured to a lever 22 when an attempt is made to start the power unit by constituting the follower of a cam 23 which is rotated 'wind-milling', and by which the over-ride is auto­ by a pulley 24 to vary the throttle setting when a cable matically restored when the speed rises to that at which 4 is operated to vary the thrust of a torque-reaction the unit should be self-operating. When the power unit compensating jet or airscrew. stops a governor 23 allows a spring 22 to force a valve 19 to the left, thereby allowing motive fluid from a pipe 12 to flow into the left-hand end of a cylinder 16 to operate a plunger 15 which moves the propeller blades 13 to the minimum pitch position. The resultant change of torque acting on a torque meter 39 closes a switch 37 to complete an electrical circuit for actuating a solenoid 35 controlling a valve 34 which allows motive fluid to be applied from pipe 31 to the spring- segment 27 connected by a universal joint 26 with the loaded plunger 28 of the over-ride device. The plunger upper end of the rod 23. The radii of the segments are moves the valve 19 to the right, allowing fluid into the respectively greater than the distances of the joints right-hand end of cylinder 16, thereby moving the 26 and 30 from their point of contact, so that move­ blades to the feathering poistion. The circuit may also 604,991. Protective devices for aircraft. A. H. Tilt- ment of the flying control member in any direction be completed by the pilot closing the fuel isolator man, M. Langley, W. G. Glendinning and A. M. from the neutral position causes a downward move­ valve 36. To start the power unti by wind-milling, ment of the rod 23 and a rotation of the sleeve 19 to Maclennan. Dec. 11, 1945, No. 33,475. ignition switch 46 of the power unit is closed, the increase the throttle setting. Protective apparatus for aircraft, particularly for govenor controlled switch 47 being already closed. A effecting the release of extinguishing medium, the solenoid 45 then opens a switch 44 and breaks the closing of fuel cocks or the control of electric circuits 604,134. Regulating. H. M. Hobson (Aircraft and circuit to the solenoid 35 so that the valve 34 closes to •in case of a fire risk and also applicable for giving a Motor) Components, Ltd., and L. S. Greenland. Feb cut-off the supply of fluid to the over-ride plunger. warning of the incipient collapse of structural mem­ 12, 1945, No. 3,450. The spring 22 is thus able to move the valve 19 to the bers, electrical conductors or power plant components A centrifugal impeller 24 and a detachably coupled left with the result that the blades are moved from the of the aircraft, comprises a closed system of pipes 14 fuel pump 11 are built into the metering unit to reduce feathered position to cause 'wind-milling'. If at a which are secured to the members which are liable to pressure losses in the fuel lines in a fuel supply system predetermined speed the unit does not then become overstrain or collapse in use or to rupture on impact. of the type described in Specification 586,259, in which self-operating, its governor will open the switch 47 The pipes are maintained above or below atmospheric fuel under pressure is fed by the pump to a metering causing switch 44 to close to complete the circuit to pressure and are connected to a pressure-sensitive orifice whose area is dependent upon boost pressure the solenoid 35. The valve 34 will be raised to bring device 13, such as an electric switch, which operates and exhaust back pressure (or atmospheric pressure) the over-ride into operation, causing plunger 28 to the protective or warning devices shown as extin­ and in which the metering pressure is maintained move valve 19 so that the propeller blades are moved guishers 11, if the pipe system is opened to atmos­ proportional to the square of the engine speed by to the feathered position. phere. The system includes frangible bulbs 26b—26e means of the centrifugal impeller. To the front of the at exposed points which will fracture on impact, and housing 57 containing the diaphragm 16, Bourdon rupturable sections 26a and 26f which are rigidly unit 45, centrifugal impeller 24, and pressure-actuated secured to structural members so as to break if the capsules 34, 35 controlling the metering orifice 13, is member collapses or distorts. The sections may be of fitted a fuel pump body 63 containing the fuel pump brittle material anchored at each end or may consist assembly 65 located in position by a cover-plate 66 of an opening in the piping closed by a disc or plug and screwed ring 70. the pump 11 has two gear-wheels adapted to be broken or torn-out if the structural 72, 73 mounted on spindles 74, 75. The spindle 74 member distorts. The piping may normally be kept engages via a dog clutch 25 with the driving shaft 26 at a standard pressure by a compressed gas reservoir 16 or a pump connected to it by a 'bleeder' tube. The switch 13, FIG . 2, which may be replaced by a valve or other pressure-sensitive actuator, comprises contacts 21, 22 held apart by a diaphragm 18 responsive to the pressure in the piping, and closed by a spring 21a when the piping is opened. 603,844. Valve gear. Cierva Autogiro Co., Ltd. and C. G. Pullin. Oct. 31, 1945, No . 28,884. The throttle 15 of a helicopter engine is operated by a hand lever 10 through a push-pull-rod made in two parts 13, 14 having oppositely-threaded end por­ tions 17, 18 engaged by corresponding internal threads of a sleeve 19 splined to a cylindrical member 20. The latter is rotatable about the axis of the rod 13, 14 and is secured to a lever connected to a rod 23 slidable in a support 24 against the action of a spring 25. The flying control member 29 of the helicopter is univers­ ally mounted at 30 and is formed with a spherical segment 28 in rolling engagement with a similar February 1951 5 9

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Feb 1, 1951

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