GB1340363A - Gas turbine power plants - Google Patents
Gas turbine power plantsInfo
- Publication number
- GB1340363A GB1340363A GB116071A GB116071A GB1340363A GB 1340363 A GB1340363 A GB 1340363A GB 116071 A GB116071 A GB 116071A GB 116071 A GB116071 A GB 116071A GB 1340363 A GB1340363 A GB 1340363A
- Authority
- GB
- United Kingdom
- Prior art keywords
- shaft
- homopolar
- compressor
- rotor
- discs
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Expired
Links
Classifications
-
- H—ELECTRICITY
- H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
- H02K—DYNAMO-ELECTRIC MACHINES
- H02K31/00—Acyclic motors or generators, i.e. DC machines having drum or disc armatures with continuous current collectors
- H02K31/04—Acyclic motors or generators, i.e. DC machines having drum or disc armatures with continuous current collectors with at least one liquid-contact collector
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/10—Adaptations for driving, or combinations with, electric generators
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/02—Blade-carrying members, e.g. rotors
- F01D5/06—Rotors for more than one axial stage, e.g. of drum or multiple disc type; Details thereof, e.g. shafts, shaft connections
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/06—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages
- F02C3/067—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising only axial stages having counter-rotating rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
- F02C3/107—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission
- F02C3/113—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with two or more rotors connected by power transmission with variable power transmission between rotors
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2220/00—Application
- F05D2220/30—Application in turbines
- F05D2220/32—Application in turbines in gas turbines
- F05D2220/327—Application in turbines in gas turbines to drive shrouded, high solidity propeller
-
- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
- Y02T50/00—Aeronautics or air transport
- Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Power Engineering (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
- Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
Abstract
1340363 Homopolar machines SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 11 Jan 1971 [15 Jan 1970] 1160/71 Heading H2A [Also in Division F1] A gas turbine engine comprises a compressor and a turbine, the turbine driving at least one homopolar electrical generator and the compressor being driven by at least one homopolar motor supplied with current from the generator. A number of different homopolar machine constructions are described. First embodiment (Fig. 2).-A number of homopolar motors each driving one stage of a compressor are carried by a stationary shaft structure 5 comprising a centre shaft 11, an intermediate shaft 16 and an outer cylinder 44. The first stage of the compressor comprises blades 120 mounted on a rotor disc 124, 126, 128, the part 128 constituting the armature of a homopolar motor through which current flows axially as indicated by arrow I. The armature is rotatably supported on the shaft 16 by means of films of liquid metal disposed at the surfaces 130, 131, a member 134 being secured on the shaft 16 but electrically insulated therefrom. The films of liquid metal permit the passage of the current I. Superconducting field coils 36, 136 are disposed between the shafts 11 and 16 within a casing 45 having an inlet and outlet 46, 48 for the flow of liquid helium and generate a magnetic flux as indicated by arrows B. The second stage 222 is similar to the first stage except that the magnetic field generated by the field coils 136, 236 flows radially outwardly through the armature 228 whereby the second stage rotates in the opposite direction to the first stage. The remaining compressor stages are similar. Second embodiment (Fig. 3).-A homopolar generating arrangement comprises two rotors 154, 254 driven by respective contra-rotating turbines, as 150, and mounted on the shaft 16 and on a ring member 54 secured on the shaft by means of films, as 161, 162, of liquid metal which allow the flow of current as indicated by arrows I. The superconducting field coils 60, 160, 260, 164, 264 create a magnetic field as indicated by arrows B, and are each disposed within a casing 70 through which liquid helium flows. Third embodiment (Fig. 12).-Rotor members 1124 of a homopolar motor drive a drum 1120 which is rotatably mounted in bearings 1121, 1122 and which supports compressor blades 1119. The stator members 1123 of the motor are mounted on the stationary shaft structure 1128, 1129, 1130, the portion 1130 on which the stator members are mounted being non-conducting. Liquid metal films 1127 are provided between the rotor and stator members and the current flows as indicated by arrows I through the stationary shaft 1129, through the rotor and stator members 1124, 1123, through the stationary shaft 1128 and back through the stationary inner shaft 1111. The field coil which is a superconductor 1125 is mounted on stator structure 1126 and creates a magnetic field as indicated by arrow B. Fourth embodiment (Fig. 13).-Rotor discs 1224 of a homopolar motor carry compressor blades 1219 and are rotatably mounted on a fixed shaft member 1211. Disc members 1223 are fixedly mounted on the shaft and carry superconducting field coils 1225 which generate a magnetic field B; the coils 1225 are disposed within casings 1225a through which liquid helium is circulated. Alternate members 1223 form supports for the rotor discs 1224 by means of rings 1227b of liquid metal which also allow passage of current I. The discs are also supported on the stationary shaft 1211 or central flanges of the dises 1223 by means of rings 1227a of liquid metal. Current flows through the outer stationary shaft member 1212, rotor discs 1224 and stator discs 1223a and 1223b as indicated by arrows I, the current returning through stationary shaft 1211. The stator discs 1223a, 1223b are insulated from the shaft 1211 by a layer of alumina. The current flows in opposite radial directions in adjacent rotor discs and the discs therefore are driven in opposite directions. Fifth embodiment (Fig. 15).-A homopolar generator 14c driven by a compressor supplies power to a homoplar motor 15c driving a fan 1c. The generator comprises a disc 16c connected to an extension 19c of the compressor shaft 20c, the extension being mounted in a bearing 21c. The motor comprises a disc 17c secured to a shaft 23c which is connected at its forward end 22c to the fan rotor 1c; the bearing 25c being supported in fixed structure 27c and the bearing 26c being located within the shaft extension 19c in the plane of the bearing 21c. The field winding 33c is a superconductor.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
FR7001437A FR2076450A5 (en) | 1970-01-15 | 1970-01-15 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1340363A true GB1340363A (en) | 1973-12-12 |
Family
ID=9049087
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB116071A Expired GB1340363A (en) | 1970-01-15 | 1971-01-11 | Gas turbine power plants |
Country Status (4)
Country | Link |
---|---|
US (1) | US3705775A (en) |
DE (1) | DE2101918C3 (en) |
FR (1) | FR2076450A5 (en) |
GB (1) | GB1340363A (en) |
Cited By (8)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5694765A (en) * | 1993-07-06 | 1997-12-09 | Rolls-Royce Plc | Shaft power transfer in gas turbine engines with machines operable as generators or motors |
US5722229A (en) * | 1994-07-30 | 1998-03-03 | Provost; Michael J. | Auxiliary gas turbine engines |
US5867979A (en) * | 1996-03-28 | 1999-02-09 | Rolls-Royce Plc | Gas turbine engine system |
GB2372157A (en) * | 2001-02-09 | 2002-08-14 | Rolls Royce Plc | Integral electrical machine in gas turbine |
EP1800005A2 (en) * | 2004-09-16 | 2007-06-27 | Harris Corporation | Embedded fluid pump using a homopolar motor |
CN110318815A (en) * | 2019-07-18 | 2019-10-11 | 北京动力机械研究所 | A kind of closed cycle turbine electricity generation system ceramic rotor |
CN111636976A (en) * | 2020-06-08 | 2020-09-08 | 清华大学 | A three-channel large thrust-to-weight ratio high-efficiency power propulsion |
RU2808879C1 (en) * | 2023-03-01 | 2023-12-05 | Сергей Юрьевич Негруб | Schematic diagrams of gas turbine engine |
Families Citing this family (93)
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US4591313A (en) * | 1983-12-30 | 1986-05-27 | The Boeing Company | Propeller pitch control system and apparatus |
FR2759734B1 (en) * | 1997-02-20 | 1999-04-09 | Snecma | TURBOMACHINE WITH OPTIMIZED COMPRESSION SYSTEM |
US6261070B1 (en) * | 1998-09-17 | 2001-07-17 | El Paso Natural Gas Company | In-line electric motor driven compressor |
DE10017649A1 (en) * | 1999-08-09 | 2003-08-07 | Frank Wiedenfeld | Continuously variable electromagnetic transmission (SEG) |
US6966174B2 (en) * | 2002-04-15 | 2005-11-22 | Paul Marius A | Integrated bypass turbojet engines for air craft and other vehicles |
EP1534945A4 (en) * | 2002-04-15 | 2006-08-30 | Marius A Paul | Integrated bypass turbojet engines for aircraft and other vehicles |
FR2842565B1 (en) * | 2002-07-17 | 2005-01-28 | Snecma Moteurs | INTEGRATED GENERATOR STARTER FOR TURBOMACHINE |
US6942451B1 (en) | 2003-06-03 | 2005-09-13 | Hamilton Sundstrand Corporation | Damping system for an expendable gas turbine engine |
US7194866B1 (en) | 2003-06-20 | 2007-03-27 | Hamilton Sundstrand Corporation | Static structure for an expendable gas turbine engine |
US8438858B1 (en) | 2003-08-20 | 2013-05-14 | Hamilton Sundstrand Corporation | Rotational system for an expendable gas turbine engine |
US7150431B2 (en) * | 2004-01-14 | 2006-12-19 | Mjd Innovations, L.L.C. | Electrical generator fluid-flow-coolant filtration |
DE102004026367B4 (en) * | 2004-05-29 | 2014-05-28 | MTU Aero Engines AG | turbomachinery |
EP1614855A1 (en) * | 2004-07-05 | 2006-01-11 | Siemens Aktiengesellschaft | Turbomachine and method to operate such a turbomachine |
US7371052B2 (en) * | 2004-08-16 | 2008-05-13 | Harris Corporation | Embedded fluid mixing device using a homopolar motor |
US7874802B2 (en) | 2004-12-01 | 2011-01-25 | United Technologies Corporation | Tip turbine engine comprising turbine blade clusters and method of assembly |
US7883314B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Seal assembly for a fan-turbine rotor of a tip turbine engine |
WO2006059975A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Peripheral combustor for tip turbine engine |
US8561383B2 (en) | 2004-12-01 | 2013-10-22 | United Technologies Corporation | Turbine engine with differential gear driven fan and compressor |
WO2006059996A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Balanced turbine rotor fan blade for a tip turbine engine |
WO2006059978A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Cantilevered tip turbine engine |
US7976273B2 (en) | 2004-12-01 | 2011-07-12 | United Technologies Corporation | Tip turbine engine support structure |
WO2006060011A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Tip turbine engine comprising a nonrotable compartment |
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WO2006059987A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Particle separator for tip turbine engine |
WO2006060004A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Combustor for turbine engine |
US7845157B2 (en) | 2004-12-01 | 2010-12-07 | United Technologies Corporation | Axial compressor for tip turbine engine |
WO2006059971A2 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Tip turbine engine integral fan, combustor, and turbine case |
US9845727B2 (en) | 2004-12-01 | 2017-12-19 | United Technologies Corporation | Tip turbine engine composite tailcone |
WO2006059999A1 (en) | 2004-12-01 | 2006-06-08 | United Technologies Corporation | Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method |
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DE602004019710D1 (en) | 2004-12-01 | 2009-04-09 | United Technologies Corp | REMOTE CONTROL FOR AN ADJUSTABLE STAGE OF A COMPRESSOR FOR A TURBINE ENGINE |
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US7631485B2 (en) * | 2004-12-01 | 2009-12-15 | United Technologies Corporation | Tip turbine engine with a heat exchanger |
US7631480B2 (en) | 2004-12-01 | 2009-12-15 | United Technologies Corporation | Modular tip turbine engine |
US7854112B2 (en) | 2004-12-01 | 2010-12-21 | United Technologies Corporation | Vectoring transition duct for turbine engine |
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US7882695B2 (en) | 2004-12-01 | 2011-02-08 | United Technologies Corporation | Turbine blow down starter for turbine engine |
US8152469B2 (en) | 2004-12-01 | 2012-04-10 | United Technologies Corporation | Annular turbine ring rotor |
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US20100126178A1 (en) * | 2008-10-08 | 2010-05-27 | Searete Llc, A Limited Liability Corporation Of The State Of Delaware | Hybrid propulsive engine including at least one independently rotatable turbine stator |
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US8992161B2 (en) | 2011-08-26 | 2015-03-31 | Honeywell International Inc. | Gas turbine engines including broadband damping systems and methods for producing the same |
US9046001B2 (en) | 2011-08-29 | 2015-06-02 | Honeywell International Inc. | Annular bearing support dampers, gas turbine engines including the same, and methods for the manufacture thereof |
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US10954792B2 (en) * | 2013-03-15 | 2021-03-23 | Sonic Blue Aerospace, Inc. | Superconducting power shaft core |
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US9371776B2 (en) * | 2013-08-20 | 2016-06-21 | Darren Levine | Dual flow air injection intraturbine engine and method of operating same |
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US11342831B2 (en) | 2019-10-07 | 2022-05-24 | Lockheed Martin Corporation | Homopolar turbine |
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GB2610569A (en) | 2021-09-08 | 2023-03-15 | Rolls Royce Plc | An improved gas turbine engine |
GB2610571A (en) | 2021-09-08 | 2023-03-15 | Rolls Royce Plc | An improved gas turbine engine |
GB2610572A (en) | 2021-09-08 | 2023-03-15 | Rolls Royce Plc | An improved gas turbine engine |
GB2610565A (en) | 2021-09-08 | 2023-03-15 | Rolls Royce Plc | An improved gas turbine engine |
GB2610567A (en) | 2021-09-08 | 2023-03-15 | Rolls Royce Plc | An improved gas turbine engine |
GB2610573A (en) * | 2021-09-08 | 2023-03-15 | Rolls Royce Plc | An improved gas turbine engine |
GB2610568A (en) | 2021-09-08 | 2023-03-15 | Rolls Royce Plc | An improved gas turbine engine |
FR3144847A1 (en) * | 2023-01-10 | 2024-07-12 | Safran | Turbomachine with electric transmission |
Family Cites Families (3)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB595357A (en) * | 1944-04-08 | 1947-12-03 | Power Jets Res & Dev Ltd | Improvements in or relating to power plants |
US2914688A (en) * | 1954-01-04 | 1959-11-24 | Baso Inc | Homopolar motor |
US3585398A (en) * | 1969-10-13 | 1971-06-15 | Gen Electric | Brushless excitation of a steam turbine generator utilizing a driver acyclic generator |
-
1970
- 1970-01-15 FR FR7001437A patent/FR2076450A5/fr not_active Expired
-
1971
- 1971-01-11 GB GB116071A patent/GB1340363A/en not_active Expired
- 1971-01-14 US US106380A patent/US3705775A/en not_active Expired - Lifetime
- 1971-01-15 DE DE2101918A patent/DE2101918C3/en not_active Expired
Cited By (12)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5694765A (en) * | 1993-07-06 | 1997-12-09 | Rolls-Royce Plc | Shaft power transfer in gas turbine engines with machines operable as generators or motors |
US5722229A (en) * | 1994-07-30 | 1998-03-03 | Provost; Michael J. | Auxiliary gas turbine engines |
US5867979A (en) * | 1996-03-28 | 1999-02-09 | Rolls-Royce Plc | Gas turbine engine system |
GB2372157A (en) * | 2001-02-09 | 2002-08-14 | Rolls Royce Plc | Integral electrical machine in gas turbine |
US6729140B2 (en) | 2001-02-09 | 2004-05-04 | Rolls-Royce Plc | Electrical machine |
GB2372157B (en) * | 2001-02-09 | 2005-07-06 | Rolls Royce Plc | A gas turbine with an electrical machine |
EP1800005A2 (en) * | 2004-09-16 | 2007-06-27 | Harris Corporation | Embedded fluid pump using a homopolar motor |
EP1800005A4 (en) * | 2004-09-16 | 2010-10-20 | Harris Corp | Embedded fluid pump using a homopolar motor |
CN110318815A (en) * | 2019-07-18 | 2019-10-11 | 北京动力机械研究所 | A kind of closed cycle turbine electricity generation system ceramic rotor |
CN110318815B (en) * | 2019-07-18 | 2022-07-08 | 北京动力机械研究所 | Ceramic rotor of closed-cycle turbine power generation system |
CN111636976A (en) * | 2020-06-08 | 2020-09-08 | 清华大学 | A three-channel large thrust-to-weight ratio high-efficiency power propulsion |
RU2808879C1 (en) * | 2023-03-01 | 2023-12-05 | Сергей Юрьевич Негруб | Schematic diagrams of gas turbine engine |
Also Published As
Publication number | Publication date |
---|---|
DE2101918A1 (en) | 1971-07-22 |
US3705775A (en) | 1972-12-12 |
DE2101918C3 (en) | 1975-08-21 |
DE2101918B2 (en) | 1975-01-09 |
FR2076450A5 (en) | 1971-10-15 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
PCNP | Patent ceased through non-payment of renewal fee |