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1. 发明专利

GB620602A Improvements in rotary heat-exchangers 未知
公开(公告)号：GB620602A
公开(公告)日：1949-03-28
申请号：GB2514746
申请日：1946-08-22
申请人： ROBERT WILLIAM CORBITT , SAMUEL FREDERICK POTTINGER
IPC分类号： F28D19/04
摘要： 620,602. Regenerators &c. CORBITT, R. W., and POTTINGER, S. F. Aug. 22, 1946, No. 25147. [Class 64(i)] A rotary-drum heat exchanger includes a drum constructed in two concentric parts with poor thermal conductivity between them, the parts being maintained substantially at the temperatures of the adjacent stationary parts so that sealing between rotary and stationary parts is facilitated. The device comprises an outer casing 10 within which an inner casing 14 is mounted by flanges 14a engaging splines 17 on the outer casing, relative thermal expansion of the casings being thus possible. The flanges 14a are doubled and of such a shape that the outer flange is substantially at the temperature of the outer casing while the inner flange is at a higher temperature. The inner casing has axial openings 15, 16 at its ends and is divided into two spaces by a partition 18. The outer casing has radial openings 11, 12. Hot gas enters the opening 15, passes through apertures 19 in the inner casing, and leaves the outer casing through the opening 12, while the air to be heated enters at 11 and leaves the inner casing at 16. A rotatable drum structure surrounds the inner casing and comprises an inner drum 24 and an outer drum 23 secured to end rings 21, 22 and spaced apart radially so that they are thermally insulated from one another, the inner drum always being traversed by hot gas or heated air, and the outer drum by cooled gas or cold air. The sealing means between the rotary and stationary parts comprise piston rings 28, 29 and sealing strips 32, 33. On account of the twopart drum construction, the temperature differences at the seals are small and clearances may therefore be reduced. The drums contain rolls of wire gauze, (not shown), and rotate on rollers 25 mounted on the outer casing, one of the rings 21 being formed with rack teeth which are engaged by a pinion 27 to drive the drum assembly.

2. 发明专利

GB589281A Improved means for damping torsional vibrations 未知
公开(公告)号：GB589281A
公开(公告)日：1947-06-17
申请号：GB1136243
申请日：1943-07-13
申请人： ROBERT WILLIAM CORBITT
IPC分类号： F16F15/10
摘要： 589,281. Motor power plant. CORBITT, R. W. July 13, 1943, No. 11362. [Classes 110 (i) and 110 (iii)] [Also in Groups XXVII and XXXII] In an aero-engine particularly of, the fuel injection type having a crank-shaft 1 driving a propeller 4, in order to damp torsional vibration in the crank-shaft and its connection to the propeller, a centrifugal supercharger 5 is driven from the crank-shaft solely through a free-wheel clutch 8 so as to permit the supercharger to over-run the crank-shaft, and/or the whole power output of an exhaust turbine 9 is transmitted to the crank-shaft through a free-wheel clutch 11 arranged to permit the crank-shaft to over-run the turbine. As shown, the crank-shaft drives the propeller 4 through reduction gearing 2,. 3 and the supercharger through speed-increasing gearing 6, 7, the drive to the supercharger being stiffer than the drive to the propeller so that the clutch 8 operates before any torque reversal in the drive to the propeller. The turbine 9 is connected to the crank-shaft through gearing 10, 6 and the clutch 11 is arranged oppositely to the clutch 8 so that the crank-shaft can over-run the turbine. Hence, when the driving speed is affected by torsional vibration, the damping effect is produced by the supercharger varying the load on the engine or by the turbine providing a variable supply of additional power to the crank-shaft.

3. 发明专利

GB554166A Improvements in or relating to centrifugal pumps and compressors 未知
公开(公告)号：GB554166A
公开(公告)日：1943-06-23
申请号：GB1642941
申请日：1941-12-19
申请人： ROBERT WILLIAM CORBITT
IPC分类号： F04D29/44

4. 发明专利

GB538133A Improvements in or relating to driving and controlling mechanism for pumps 未知
公开(公告)号：GB538133A
公开(公告)日：1941-07-22
申请号：GB125940
申请日：1940-01-20
申请人： ARTHUR JOHN ROWLEDGE , ROBERT WILLIAM CORBITT
IPC分类号： F02M59/28 , F02M59/44
摘要： 538,133. Fuel injection &c. pumps. ROWLEDGE, A. J., and CORBITT, R. W. Jan. 20, 1940, No. 1259. [Class 102 (i)] In a fuel injection or like pump in which one or more plungers are positively driven on both the delivery and suction strokes, and a control member operates on the plungers to vary the delivery of the pump, one or a pair of breaking pieces are arranged between the control member and the plunger so that, if the plunger seizes, continued movement of the driving member will sever the breaking piece and disconnect the control gear from the plunger. In the form shown, the plunger 10 has an extension 11 to which is connected by diametral pins 16 a sleeve 14 which is rotatably coupled to a control member 19. Delivery and suction strokes of the plunger are effected by a cross-head 13 engaging, respectively, the end 12 of the extension 11 and a flange 17 on the sleeve 14. The breaking point is produced by forming gaps 20 in the sleeve between the member 19 and the pins 16. In modifications, the pins 16 may be small so as to shear easily, a flange on a weakened sleeve may be riveted to a flange on the extension 11, or the latter itself may be formed with a weakened section.

5. 发明专利

GB618760A Improvements in or relating to gas-turbine fuel-systems 未知
公开(公告)号：GB618760A
公开(公告)日：1949-02-25
申请号：GB2277747
申请日：1946-09-30
申请人： DONALD LOUIS MORDELL , ROBERT WILLIAM CORBITT
IPC分类号： F02C6/00
摘要： 618,760. Gas turbine plant ; jet propulsion plant. MORDELL, D. L., and CORBITT, R. W. Sept. 30, 1946, Nos. 22777/47 (divided out of 618,479), and 23027/47. [Class 110 (iii)] In a gas turbine plant having one or more reheat stages into which fuel is injected the atomization of the fuel in the injector is assisted by air or combustion gas taken from a point in the engine which is at a higher pressure than that in the reheat stage. The plant shown, Fig. 1, comprises an axial flow compressor 12 supplying air to the main combustion chambers 13 which supplies combustion gases to a turbine 15 driving the compressor, reheat chambers 16 in which fuel is injected by nozzles 20 and a further turbine 17 mounted on the same shaft 10, from which power may be taken, as the turbine 15. The nozzles 20 are supplied with fuel through a pipe 19 and air through a pipe connected to the outlet of the compressor 12. The nozzles 20, Fig. 2, comprise a fuel supply duct 21 leading into a swirl chamber 22 through a series of helical grooves 23 in a swirl nozzle 24. To obtain good atomization at low fuel flows, air is injected in the swirl chamber 22 from the supply pipe through a series of tangential plots 27 in a plate 28 encircling the chamber 22. The supply of air passing through the pipe may be controlled by an automatic valve under the control of the fuel pressure so that the air supply is cut-off at high fuel flows. Alternatively, the air supply may be operative over the whole range of fuel flows in which case the air supply is cut-off when the fuel supply to the injection- 20 is cut-off. Instead of air, combustion gases tapped off from the combustion chamber 13 may be used, in which case, the fuel is preheated before leaving the injector. The invention may be applied to a jet propulsion engine to reheat the gases before they enter the propulsion nozzle. The fuel injector 20 may then be mounted on the apex of the exhaust bullet and supplied with air from the compressor diffuser or combustion gases from the combustion chamber. The fuel injector may be enclosed in a flame tube. According to the second Provisional Specification the invention may be applied to a gas turbine power plant in which there is a high pressure turbine driving a high pressure compressor and supplying useful output and a low pressure turbine driving a low pressure compressor. The gases are reheated between the turbines and, if desired, the compressed air from the high pressure compressor may be pre-heated before passing into the main combustion chamber in a heat-exchanger heated by the exhaust gases of the high pressure turbine before they pass into the re-heat chamber. In another arrangement described in the Specification referred to the invention is applied to a multistage turbine in which the re-heat chambers are formed by the spaces between the fixed guide blades which spaces are enlarged if necessary.

6. 发明专利

GB549457A Improvements in or relating to rotary pumps and compressors for fluids 未知
公开(公告)号：GB549457A
公开(公告)日：1942-11-23
申请号：GB643041
申请日：1941-05-19
申请人： ROBERT WILLIAM CORBITT
IPC分类号： F04D29/52 , F04D29/56

7. 发明专利

GB542009A Improvements in or relating to liquid-cooling systems for sleevevalve internal-combustion engines 未知
公开(公告)号：GB542009A
公开(公告)日：1941-12-22
申请号：GB1053840
申请日：1940-06-18
申请人： ARTHUR JOHN ROWLEDGE , HARRY WOOD , ROBERT WILLIAM CORBITT
IPC分类号： F01P3/02
摘要： 542,009. Cooling cylinders. ROWLEDGE, A. J., WOOD, H., and CORBITT, R. W. June 18, 1940, No. 10538. [Class 7 (ii)] In two-stroke, liquidcooled, sleeve-valve engines, means are provided for obtaining a highvelocity flow of coolant over the cylinder walls above the exhaust ports, and a lower velocity flow over the central part of the end wall of the combustion chamber. Fig. 3 shows the invention applied to an engine with a combustion chamber extension 17, the flow of coolant around which is resisted by restricted openings 24 and baffles 20, whereas a free flow is provided through the part 23 of the jacket above the exhaust ports 16. The upper part 19 of the jacket is preferably formed separate from the lower jacket 12. The holding-down bolts for the cylinders pass through bosses formed in the jackets between the cylinders. In a V-engine a' cooling-pump is provided for each bank of cylinders, and the discharge pipes from the cylinder heads lead to a single header between the cylinder banks.

8. 发明专利

GB492044A Sparking plugs 未知
公开(公告)号：GB492044A
公开(公告)日：1938-09-14
申请号：GB757337
申请日：1937-03-15
申请人： ROBERT WILLIAM CORBITT
IPC分类号： H01T13/22 , H01T13/46
摘要： 492,044. Sparking - plugs. CORBITT, R. W. March 15, 1937, No. 7573. [Class 7 (iv)] Two separately insulated conductors A, connected to different sources of current, are mounted within and discharge to the same casing. They may be parallel. or inclined, may be conically seated, or may be supported by spacing washers C, C . In a modification, Fig. 5, siamesed insulators E are used. An insulating sleeve F surrounds the outer end of the insulators E and is formed with cavities for receiving spring-pressed plungers secured to the current leads G . An aluminium distance piece G with a single hole at the top and a pair in the lower surface guides the ends. Arcuate sparking terminals J are formed on the casing and on a bridge-piece J.

9. 发明专利

GB622411A Improvements relating to gas-turbine-engines 未知
公开(公告)号：GB622411A
公开(公告)日：1949-05-02
申请号：GB770947
申请日：1947-03-20
申请人： ROBERT WILLIAM CORBITT
IPC分类号： F23R3/38
摘要： 622,411. Liquid-fuel burners. CORBITT, R. W. March 20, 1947, No. 7709. [Class 75(i)] [Also in Group XXVI] In a gas turbine plant the working fluid is reheated between stages of the turbine and in plant used for jet-propulsion, the reheating may take place after the turbine. In the former case, Fig. 1, the reheating takes place after the first running blades 19 and before the stator blades 18. Fuel carried through a blade 18 by pipe 25 and duct 27 is delivered from a pipe 28 against the face of a turbine disc 11 radially within a sharp-edged annular lip 29. The fuel is thrown from this lip in a fine spray through an annular chamber defined by a stationary wall 30 where it is burnt with working-fluid brought into the chamber by scoop-like parts of the wall 30. A similar arrangement may be provided on the downstream side of the turbine rotor at the beginning of the exhaust duct for heating the exhaust gases when they are used in a propulsion jet. The single lip 29 may be replaced by a ring secured to the rotor and having two annular grooves. The fuel is delivered to the inner groove and passes from it through radial holes into the outer groove from which it is thrown in a fine spray.

10. 发明专利

GB619236A Improvements in or relating to centrifugal compressors 未知
公开(公告)号：GB619236A
公开(公告)日：1949-03-07
申请号：GB2871846
申请日：1946-09-25
申请人： ROBERT WILLIAM CORBITT , CHRISTOPHER AINSWORTH DAVIS , ROBERT CLARKSON PLUMB , DAVID OMRI DAVIES
IPC分类号： F04D29/28
摘要： 619,236. Centrifugal pumps. CORBITT, R. W., DAVIS, C. A., PLUMB, R. C., and DAVIES, D. O. Sept. 25, 1946, No. 28718. [Class 110 (i)] A rotor for a centrifugal pump has rotor blades 11 and an associated single set of rotating inlet-guide-vanes 12 wherein each rotor blade 11 has a corresponding inlet-guide-vane 12 which is displaced circumferentially from alignment with its associated rotor blade 11. This displacement may be one-third the angular distance between the leading edges of adjacent rotor-blades and in the direction of rotation. The leading edges of rotor blades and the trailing edges of the inlet-guide-vanes may be chamfered to prevent turbulence. Fixed swirlvanes 16 may also be used to enable a total swirl deflection of 90 degrees to be obtained, equal swirl deflection being obtained in each of the three sets of vanes. Specification 568,575 is referred to.

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