British Patent Abridgments

British Patent Abridgments These details of British Patent Specifications are each nozzle being rotatable about an axis which is taken by permission from 'Abridgments of Specifica­ acutely inclined to the longitudinal axis of the device tions—Patents for Inventions'. Copies of the full and which is intersected by the axis of symmetry of the nozzle at such an angle that in one position of the specifications are obtainable from the Patent Office, nozzle its axis of symmetry is parallel to the longi­ 25 Southampton Buildings, London, W.C.2, price tudinal axis of the device. The illustration shows the 3s. fid. each. rear end plate of a rocket propulsion device, on which arc mounted two pairs of nozzles 40, 42, and 41, 43, 870,182. Air Intakes for Aircraft. United Aircraft which may receive propulsive gases from a common Corporation. September 24, 1958. source or distinct sources. The outlet of each nozzle is An air intake for the power plant of a high speed shown as a full line circle, in the position in which aircraft (described in the embodiment in terms of a the nozzle is nearest the centre line of the device, when wind tunnel model) comprises an upstream opening the axis of symmetry of the nozzle is parallel to the 20 which passes air to a supersonic diffuser portion 22 centre line. The broken lines 44 show for each nozzle and thence through a throat 24 to a subsonic diffuser the area swept out by the nozzle outlet as the nozzle opposite pitching couples, and equal and similar yaw­ 26. The intake is formed by a compression surface is rotated. For pitch control, nozzles 41 and 43 are ing couples. For roll control, nozzles 41 and 43, or 28 which is part-circular in cross-section and forms rotated equally in opposite senses, to produce equal 40 and 42, arc rotated in the same sense. An illustration the major, fixed portion of the intake and by a slidable and opposite yawing couples and equal and similar shows one form of rotatable nozzle, comprising a cowl 30 which is positioned by a further outer fixed pitching couples. For yaw control, nozzles 40 and 42 throat 2 and expansion cone 3 with an outer steel are rotated in opposite senses, t o produce equal and shell 4. A steel ring 6 is welded to the shell 4, and a flange 7 on the ring has a groove 8. An annular boss 9 welded to the rear and closure plate 1 of the propul­ sion unit has a groove 10, the two grooves together with steel balls 11 forming a ball bearing. A sealing ring 15 is provided, and its frictional resistance to rotation is reduced by coating the appropriate surface of ring 6 or boss 9 with P.T.F.E., or making the scaling wall 50 for longitudinal sliding movement to vary the ring of P.T.F.E. The insulating material 5, 16 of the geometry of the leading edge of the air intake. A nozzle is a close fit on the insulation 17 of the closure screw-jack mechanism 60, 62 enclosed in a fairing plate I, to protect the seal. Flange 7 is provided with 74 and operated by a motor 68, effects axial move­ gear teeth 18 for rotation of the nozzle by an electric ment of cowl 30. Boundary layer air on surface 28 or hydraulic motor 19. Alternatively, an arm extending is bled off by a scoop 38 which exhausts through a from the nozzle may be connected to a linear hydraulic passage 40 and boundary layer bleed passages 34, actuator. To enable the axis of the rotation of the 32 arc formed in surface 28 and cowl 30 respectively. nozzle to be normal to the closure plate 1, the plate is made outwardly convex. In another form of nozzle, 875,205. Rocket Propulsion. Imperial Chemical the ring 6 and flange 7 arc replaced by an inset in the Industries Ltd. Dec. 9, 1959. nozzle wall, which is of reinforced plastic material. According to the Provisional Specification, the A rocket propulsion device has one or more pairs moment of inertia of the nozzle about its axis of of nozzles, each nozzle of a pair being diametrically rotation should not be much more than that about its opposite to the other and the nozzles of a pair being axis of symmetry. equidistant from the longitudinal axis of the device, wards directed jet nozzle located above the wing upper surface, the nozzle being disposed to discharge U.S. Patent Specifications a jet stream in a rearward direction above and clear of the wing upper surface. A jet deflector is opera- These details are taken by permission of the Depart­ tivcly associated with the nozzle and is movable be­ ment of Commerce, from the 'Official Gazette of the tween an inoperative position in which it is housed United States Patent Office', Copies of the full speci­ within the wing and an operative position in which it fications arc obtainable from the Commissioner of deflects the jet stream from the rearward direction to a Patents, Washington, D.C., U.S.A., price 25 cents each. direction downwardly inclined therefrom such that the 3,013,752. De-Icing Control. C. K. Rush, assignor stream impinges obliquely on the wing upper surface to National Research Council, a body corporate in whereby the stream spreads out laterally across the Canada. October 1, 1959. surface in a spanwisc sense and leaves the wing In an electro-thermal de-icing system for an aero­ trailing edge as a long thin spanwisc-extending jet foil there are: a heater pad mounted around the lead­ sheets. ing edge of the aerofoil (this heater pad having heater elements forming a parting strip located along the line 3,020,003. Disc Aircraft with Gas Turbine and Ram of stagnation of the aerofoil), heater elements form­ Jet Engines. J. C. M. Frost and C. J. Williams, augmentation component in the power plant, a fuel ing an upper shedding area extending from the upper supply containing fuel for the thrust augmentation assignors to Avro Aircraft Ltd., a corporation of component, and a metallic fuel transfer means con­ Canada. July 2, 1956. nected to the fuel supply and connected to the thrust An aircraft comprises a generally lentiform struc­ augmentation component. The fuel transfer means has ture sheathed by opposed aerofoil surfaces which pro­ a heat exchanger section located in relation to an ex­ vide lift developing surfaces, an air displacement pas­ terior surface of the aircraft. A flow restrictor means is sage within the structure and having an intake and located between the heat exchanger section and the fuel supply, and fuel re-pressurization means arc edge of the parting strip rearwardly along the upper located in the fuel transfer means between the heat surface of the aerofoil and further heater elements exchanger section and the thrust augmentation com­ forming a lower shedding area extending from the ponent. The flow restrictor means and fuel re- lower edge of the parting strip rearwards along the pressurization means substantially reduce the pressure lower surface of the aerofoil. The heater elements of the of fuel transferred through the fuel transfer means. upper and lower shedding areas arc adapted for pcriodic energization so as to loosen the adhesion of ice 3,018,983. Jet Aircraft with Jet Deflector. I. M. to the aerofoil. A temperature-sensitive means is Davidson, assignor to Power Jets (Research and associated with the heater pad and the temperature- Development) Ltd. October 10, 1958. sensitive means has at least two temperature-sensitive An aircraft comprises a wing and this wing has a regions and is adapted to yield data dependent upon wing flap at the wing trailing edge. At least one jet the area and temperature of each of the regions. One engine is mounted on the wing. The engine has a rear­ of the regions is located on the parting strip and another of the regions is located on one of the shed­ having an annularly arranged outlet adjacent the ding areas. Means responsive to the temperature- perimeter of the structure. The air displacement sensitive means exist for controlling the power input passage includes a plurality of generally radially dis­ to the heater elements of only the parting strip posed ducts. Flame tubes are positioned in the ducts whereby the power input is controlled in accordance adjacent to the outlet to eject their products of com­ with the temperature of both the regions of the bustion therethrough. The ducts and the flame tubes temperature-sensitive means. together provide ram jet engines. Means exist in the 3,015,461. High-performance Aircraft. S. Finc- passage to supply air under compression to the ram jet blum, assignor to North American Aviation, Inc. engines, and means exist at the outlet to control selec­ March 7, 1958. tively the flow of the efflux from the outlet to provide An aircraft has a power plant, a fuel-burning thrust a controlled propulsive thrust. 186 Aircraft Engineering http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Aircraft Engineering and Aerospace Technology Emerald Publishing

British Patent Abridgments

Aircraft Engineering and Aerospace Technology, Volume 34 (6): 1 – Jun 1, 1962

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Publisher
Emerald Publishing
Copyright
Copyright © Emerald Group Publishing Limited
ISSN
0002-2667
DOI
10.1108/eb033572
Publisher site
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Abstract

These details of British Patent Specifications are each nozzle being rotatable about an axis which is taken by permission from 'Abridgments of Specifica­ acutely inclined to the longitudinal axis of the device tions—Patents for Inventions'. Copies of the full and which is intersected by the axis of symmetry of the nozzle at such an angle that in one position of the specifications are obtainable from the Patent Office, nozzle its axis of symmetry is parallel to the longi­ 25 Southampton Buildings, London, W.C.2, price tudinal axis of the device. The illustration shows the 3s. fid. each. rear end plate of a rocket propulsion device, on which arc mounted two pairs of nozzles 40, 42, and 41, 43, 870,182. Air Intakes for Aircraft. United Aircraft which may receive propulsive gases from a common Corporation. September 24, 1958. source or distinct sources. The outlet of each nozzle is An air intake for the power plant of a high speed shown as a full line circle, in the position in which aircraft (described in the embodiment in terms of a the nozzle is nearest the centre line of the device, when wind tunnel model) comprises an upstream opening the axis of symmetry of the nozzle is parallel to the 20 which passes air to a supersonic diffuser portion 22 centre line. The broken lines 44 show for each nozzle and thence through a throat 24 to a subsonic diffuser the area swept out by the nozzle outlet as the nozzle opposite pitching couples, and equal and similar yaw­ 26. The intake is formed by a compression surface is rotated. For pitch control, nozzles 41 and 43 are ing couples. For roll control, nozzles 41 and 43, or 28 which is part-circular in cross-section and forms rotated equally in opposite senses, to produce equal 40 and 42, arc rotated in the same sense. An illustration the major, fixed portion of the intake and by a slidable and opposite yawing couples and equal and similar shows one form of rotatable nozzle, comprising a cowl 30 which is positioned by a further outer fixed pitching couples. For yaw control, nozzles 40 and 42 throat 2 and expansion cone 3 with an outer steel are rotated in opposite senses, t o produce equal and shell 4. A steel ring 6 is welded to the shell 4, and a flange 7 on the ring has a groove 8. An annular boss 9 welded to the rear and closure plate 1 of the propul­ sion unit has a groove 10, the two grooves together with steel balls 11 forming a ball bearing. A sealing ring 15 is provided, and its frictional resistance to rotation is reduced by coating the appropriate surface of ring 6 or boss 9 with P.T.F.E., or making the scaling wall 50 for longitudinal sliding movement to vary the ring of P.T.F.E. The insulating material 5, 16 of the geometry of the leading edge of the air intake. A nozzle is a close fit on the insulation 17 of the closure screw-jack mechanism 60, 62 enclosed in a fairing plate I, to protect the seal. Flange 7 is provided with 74 and operated by a motor 68, effects axial move­ gear teeth 18 for rotation of the nozzle by an electric ment of cowl 30. Boundary layer air on surface 28 or hydraulic motor 19. Alternatively, an arm extending is bled off by a scoop 38 which exhausts through a from the nozzle may be connected to a linear hydraulic passage 40 and boundary layer bleed passages 34, actuator. To enable the axis of the rotation of the 32 arc formed in surface 28 and cowl 30 respectively. nozzle to be normal to the closure plate 1, the plate is made outwardly convex. In another form of nozzle, 875,205. Rocket Propulsion. Imperial Chemical the ring 6 and flange 7 arc replaced by an inset in the Industries Ltd. Dec. 9, 1959. nozzle wall, which is of reinforced plastic material. According to the Provisional Specification, the A rocket propulsion device has one or more pairs moment of inertia of the nozzle about its axis of of nozzles, each nozzle of a pair being diametrically rotation should not be much more than that about its opposite to the other and the nozzles of a pair being axis of symmetry. equidistant from the longitudinal axis of the device, wards directed jet nozzle located above the wing upper surface, the nozzle being disposed to discharge U.S. Patent Specifications a jet stream in a rearward direction above and clear of the wing upper surface. A jet deflector is opera- These details are taken by permission of the Depart­ tivcly associated with the nozzle and is movable be­ ment of Commerce, from the 'Official Gazette of the tween an inoperative position in which it is housed United States Patent Office', Copies of the full speci­ within the wing and an operative position in which it fications arc obtainable from the Commissioner of deflects the jet stream from the rearward direction to a Patents, Washington, D.C., U.S.A., price 25 cents each. direction downwardly inclined therefrom such that the 3,013,752. De-Icing Control. C. K. Rush, assignor stream impinges obliquely on the wing upper surface to National Research Council, a body corporate in whereby the stream spreads out laterally across the Canada. October 1, 1959. surface in a spanwisc sense and leaves the wing In an electro-thermal de-icing system for an aero­ trailing edge as a long thin spanwisc-extending jet foil there are: a heater pad mounted around the lead­ sheets. ing edge of the aerofoil (this heater pad having heater elements forming a parting strip located along the line 3,020,003. Disc Aircraft with Gas Turbine and Ram of stagnation of the aerofoil), heater elements form­ Jet Engines. J. C. M. Frost and C. J. Williams, augmentation component in the power plant, a fuel ing an upper shedding area extending from the upper supply containing fuel for the thrust augmentation assignors to Avro Aircraft Ltd., a corporation of component, and a metallic fuel transfer means con­ Canada. July 2, 1956. nected to the fuel supply and connected to the thrust An aircraft comprises a generally lentiform struc­ augmentation component. The fuel transfer means has ture sheathed by opposed aerofoil surfaces which pro­ a heat exchanger section located in relation to an ex­ vide lift developing surfaces, an air displacement pas­ terior surface of the aircraft. A flow restrictor means is sage within the structure and having an intake and located between the heat exchanger section and the fuel supply, and fuel re-pressurization means arc edge of the parting strip rearwardly along the upper located in the fuel transfer means between the heat surface of the aerofoil and further heater elements exchanger section and the thrust augmentation com­ forming a lower shedding area extending from the ponent. The flow restrictor means and fuel re- lower edge of the parting strip rearwards along the pressurization means substantially reduce the pressure lower surface of the aerofoil. The heater elements of the of fuel transferred through the fuel transfer means. upper and lower shedding areas arc adapted for pcriodic energization so as to loosen the adhesion of ice 3,018,983. Jet Aircraft with Jet Deflector. I. M. to the aerofoil. A temperature-sensitive means is Davidson, assignor to Power Jets (Research and associated with the heater pad and the temperature- Development) Ltd. October 10, 1958. sensitive means has at least two temperature-sensitive An aircraft comprises a wing and this wing has a regions and is adapted to yield data dependent upon wing flap at the wing trailing edge. At least one jet the area and temperature of each of the regions. One engine is mounted on the wing. The engine has a rear­ of the regions is located on the parting strip and another of the regions is located on one of the shed­ having an annularly arranged outlet adjacent the ding areas. Means responsive to the temperature- perimeter of the structure. The air displacement sensitive means exist for controlling the power input passage includes a plurality of generally radially dis­ to the heater elements of only the parting strip posed ducts. Flame tubes are positioned in the ducts whereby the power input is controlled in accordance adjacent to the outlet to eject their products of com­ with the temperature of both the regions of the bustion therethrough. The ducts and the flame tubes temperature-sensitive means. together provide ram jet engines. Means exist in the 3,015,461. High-performance Aircraft. S. Finc- passage to supply air under compression to the ram jet blum, assignor to North American Aviation, Inc. engines, and means exist at the outlet to control selec­ March 7, 1958. tively the flow of the efflux from the outlet to provide An aircraft has a power plant, a fuel-burning thrust a controlled propulsive thrust. 186 Aircraft Engineering

Journal

Aircraft Engineering and Aerospace TechnologyEmerald Publishing

Published: Jun 1, 1962

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