GB1341241A - Power plants for the jet propulsion of aircraft - Google Patents

Power plants for the jet propulsion of aircraft

Info

Publication number
GB1341241A
GB1341241A GB115971A GB115971A GB1341241A GB 1341241 A GB1341241 A GB 1341241A GB 115971 A GB115971 A GB 115971A GB 115971 A GB115971 A GB 115971A GB 1341241 A GB1341241 A GB 1341241A
Authority
GB
United Kingdom
Prior art keywords
compressor
turbine
homopolar
generator
motors
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
Application number
GB115971A
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Safran Aircraft Engines SAS
Original Assignee
SNECMA SAS
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by SNECMA SAS filed Critical SNECMA SAS
Publication of GB1341241A publication Critical patent/GB1341241A/en
Expired legal-status Critical Current

Links

Classifications

    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K44/00—Machines in which the dynamo-electric interaction between a plasma or flow of conductive liquid or of fluid-borne conductive or magnetic particles and a coil system or magnetic field converts energy of mass flow into electrical energy or vice versa
    • H02K44/08—Magnetohydrodynamic [MHD] generators
    • 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
    • F02K—JET-PROPULSION PLANTS
    • F02K5/00—Plants including an engine, other than a gas turbine, driving a compressor or a ducted fan
    • H—ELECTRICITY
    • H02—GENERATION; CONVERSION OR DISTRIBUTION OF ELECTRIC POWER
    • H02K—DYNAMO-ELECTRIC MACHINES
    • H02K44/00—Machines in which the dynamo-electric interaction between a plasma or flow of conductive liquid or of fluid-borne conductive or magnetic particles and a coil system or magnetic field converts energy of mass flow into electrical energy or vice versa
    • H02K44/28—Association of MHD generators with conventional generators
    • 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)
  • Power Engineering (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Control Of Eletrric Generators (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Connection Of Motors, Electrical Generators, Mechanical Devices, And The Like (AREA)
  • Superconductive Dynamoelectric Machines (AREA)

Abstract

1341241 Homopolar machines; MHD power plant SOC NATIONALE D'ETUDE ET DE CONSTRUCTION DE MOTEURS D'AVIATION 11 Jan 1971 [15 Jan 1970] 1159/71 Heading H2A [Also in Division F1] An aircraft jet propulsion plant comprises at least one mechanical compressor for compressing a flow of gas, heating or combustion means for raising the compressed gas flow to a high temperature and a jet pipe through which the gas flow escapes to atmosphere, at least part of the energy for driving the compressor being taken from the high temperature gas flow, at least under certain conditions of operation, by means of an MHD generator, the conversion channel of which, carrying the gas flow, is located downstream of the heating or combustion means. In the embodiment shown in Fig. 9, a compressor 501a, 501b, 501c is followed by a combustion chamber 602, a turbine 601, a combustion chamber 502 and an MHD generator 503 having a superconducting field winding. At take-off and at low speeds, the compressor elements 501a, 501b, 501c are driven mainly by homopolar electric motors 505b connected in series or, as shown, in parallel to a homopolar generator 605 driven by the turbine 601 and having a superconducting field winding. At high speeds, the compressor elements are driven mainly or wholly by homopolar electric motors 505a connected in series to the electrodes 508, 509 of the MHD generator, and the turbine may then act as a compressor. The relative contributions of the two generators 503, 605 are controlled by varying their respective field currents. Instead of separate motors 505a, 505b, a single motor for each compressor element may be provided, the generator driven by the turbine then being connected in parallel with the MHD generator. The connection between the turbine and the compressor may instead be a mechanical one. The turbine and the combustion chamber may be omitted. As shown in Fig. 10, the homopolar motors 505a, 505b have a common superconducting field winding 525. Each motor 505a comprises three rotating discs and three stationary discs interconnected by contacts each preferably formed by a ring of liquid metal, as described in Specification 1160/71. The motors 505a are connected to the MHD generator by annular conductors 511, 512, the latter being formed partly by a stator of the turbine 601. Each motor 505b comprises a single rotating disc connected to annular conductors 611, 612 by annular liquid metal contacts, the conductor 612 being branched off to the motors 505b (not shown) via compressor stator rings 513c. The armature 624 of the homopolar generator driven by the turbine is integral with the turbine-rotor 619 and is connected to the conductors 611, 612 by annular liquid metal contacts 627a, 627b. Two superconducting field windings 625a, 625b carrying currents in the same sense form a substantially axial magnetic field in the region of a disc-like portion 624b of the armature 624. Another superconducting field winding 625c carrying current in the opposite direction forms, in conjunction with the windings 625a, 625b, a substantially radial magnetic field in the region of a cylindrical portion 624a of the armature 624. The compressor may comprise a series of contra-rotating, blade rings each having a disc which forms the armature of an individual homopolar motor as described in Specification 1,340,363.
GB115971A 1970-01-15 1971-01-11 Power plants for the jet propulsion of aircraft Expired GB1341241A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR7001440A FR2085190B1 (en) 1970-01-15 1970-01-15

Publications (1)

Publication Number Publication Date
GB1341241A true GB1341241A (en) 1973-12-19

Family

ID=9049090

Family Applications (1)

Application Number Title Priority Date Filing Date
GB115971A Expired GB1341241A (en) 1970-01-15 1971-01-11 Power plants for the jet propulsion of aircraft

Country Status (4)

Country Link
US (1) US3678306A (en)
DE (1) DE2101919C3 (en)
FR (1) FR2085190B1 (en)
GB (1) GB1341241A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2638239C1 (en) * 2016-12-21 2017-12-12 Дмитрий Дмитриевич Кожевников Direct flow turboretactive detonation engine (dftde)
WO2020117205A1 (en) * 2018-12-04 2020-06-11 Llc Look For The Power Rotary internal combustion engine

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* Cited by examiner, † Cited by third party
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US4418294A (en) * 1982-07-02 1983-11-29 Rahman Muhammed A Supersonic MHD generator system
US4663932A (en) * 1982-07-26 1987-05-12 Cox James E Dipolar force field propulsion system
US4891600A (en) * 1982-07-26 1990-01-02 Cox James E Dipole accelerating means and method
US4450361A (en) * 1982-08-26 1984-05-22 Holt James F Coupling of MHD generator to gas turbine
US5087215A (en) * 1990-03-08 1992-02-11 Leonid Simuni Ocean-going vessel and method for increasing the speed
US5219672A (en) * 1991-08-12 1993-06-15 Tacticon Corporation Metal/air battery cell and assembly therefor
US5183222A (en) * 1991-08-12 1993-02-02 Tacticon Corp. Electric powered tip-driven fan with metal/air battery assembly therefor
US5269137A (en) * 1991-12-20 1993-12-14 United Technologies Corporation Gas turbine elements bearing coke inhibiting coatings of alumina
US5264244A (en) * 1991-12-20 1993-11-23 United Technologies Corporation Inhibiting coke formation by coating gas turbine elements with alumina
US5324544A (en) * 1991-12-20 1994-06-28 United Technologies Corporation Inhibiting coke formation by coating gas turbine elements with alumina-silica sol gel
US5336560A (en) * 1991-12-20 1994-08-09 United Technologies Corporation Gas turbine elements bearing alumina-silica coating to inhibit coking
US6419538B1 (en) 1998-11-10 2002-07-16 Arizona Board Of Regents Marine propulsion system and method using an in-situ generated water plasma
US6644014B2 (en) * 2000-09-30 2003-11-11 Anthony Italo Provitola Electric thruster and thrust augmenter
US6696774B1 (en) * 2001-06-01 2004-02-24 Steven J. Schneider Magnetohydrodynamic power extraction and flow conditioning in a gas flow turbine
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
US7371052B2 (en) * 2004-08-16 2008-05-13 Harris Corporation Embedded fluid mixing device using a homopolar motor
US7578661B2 (en) * 2004-09-16 2009-08-25 Harris Corporation Embedded fluid pump using a homopolar motor
US8636241B2 (en) 2005-04-20 2014-01-28 Richard H. Lugg Hybrid jet/electric VTOL aircraft
US7602096B2 (en) * 2005-05-03 2009-10-13 Patrick Craig Muldoon Magnetic gas engine and method of extracting work
US8720205B2 (en) * 2005-09-09 2014-05-13 Richard H. Lugg Advanced hypersonic magnetic jet/electric turbine engine (AHMJET)
US20080175703A1 (en) * 2007-01-09 2008-07-24 Sonic Blue Aerospace Electric turbine bypass fan and compressor for hybrid propulsion
US7870719B2 (en) * 2006-10-13 2011-01-18 General Electric Company Plasma enhanced rapidly expanded gas turbine engine transition duct
US7870720B2 (en) * 2006-11-29 2011-01-18 Lockheed Martin Corporation Inlet electromagnetic flow control
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
US20100083632A1 (en) * 2008-10-08 2010-04-08 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Hybrid propulsive engine including at least one independently rotatable compressor rotor
US20100108806A1 (en) * 2008-10-08 2010-05-06 Searete Llc, A Limited Liability Corporation Of The State Of Delaware Hybrid propulsive engine including at least one independently rotatable propeller/fan
US8099944B2 (en) * 2008-10-08 2012-01-24 The Invention Science Fund I, Llc Hybrid propulsive engine including at least one independently rotatable propeller/fan
FR2988435B1 (en) * 2012-03-23 2016-03-18 Snecma IGNITION BOX FOR IGNITION SEGREGATION TURBOJUSTER
US9296288B2 (en) * 2012-05-07 2016-03-29 Separation Design Group Llc Hybrid radiant energy aircraft engine
WO2014150377A1 (en) * 2013-03-15 2014-09-25 Embry-Riddle Aeronautical University, Inc. Electrically coupled counter-rotation for gas turbine compressors
US20160362998A1 (en) * 2013-11-26 2016-12-15 Ge Aviation Systems Llc Generator for an aircraft
US20170037534A1 (en) 2015-08-07 2017-02-09 North Carolina State University Direct conversion of h-bn into c-bn and structures for a variety of applications
FR3040838B1 (en) 2015-09-04 2017-09-22 Turbomeca MAGNETOHYDRODYNAMIC GENERATOR
US10507913B2 (en) 2016-06-15 2019-12-17 North Carolina State University Hypersonic aircraft having homopolar motor with graded resistance
BE1024492B1 (en) * 2016-08-12 2018-03-12 Safran Aero Boosters S.A. ARAB A VARIABLE ORIENTATION OF AXIAL TURBOMACHINE COMPRESSOR
GB201807773D0 (en) * 2018-05-14 2018-06-27 Rolls Royce Plc Aircraft propulsion system
US11342831B2 (en) 2019-10-07 2022-05-24 Lockheed Martin Corporation Homopolar turbine
US11867137B1 (en) * 2021-10-25 2024-01-09 Jesse LaSalle McQueen Jet engine having electrically powered superheating section

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* Cited by examiner, † Cited by third party
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GB738511A (en) * 1953-02-28 1955-10-12 Nicholas S Japolsky Improvements in or relating to internal combustion engines
US2914688A (en) * 1954-01-04 1959-11-24 Baso Inc Homopolar motor
US3309546A (en) * 1963-03-14 1967-03-14 Babcock & Wilcox Co Apparatus for the generation of electric energy
GB1118041A (en) * 1964-07-07 1968-06-26 Conch Int Methane Ltd Improvements in and relating to thermal power plants
US3527055A (en) * 1968-04-15 1970-09-08 Jose Dominguez Rego Magnetoplasmadynamic jet engine
US3585398A (en) * 1969-10-13 1971-06-15 Gen Electric Brushless excitation of a steam turbine generator utilizing a driver acyclic generator

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
RU2638239C1 (en) * 2016-12-21 2017-12-12 Дмитрий Дмитриевич Кожевников Direct flow turboretactive detonation engine (dftde)
WO2020117205A1 (en) * 2018-12-04 2020-06-11 Llc Look For The Power Rotary internal combustion engine

Also Published As

Publication number Publication date
FR2085190A1 (en) 1971-12-24
DE2101919C3 (en) 1978-12-21
FR2085190B1 (en) 1973-12-07
DE2101919B2 (en) 1978-04-20
DE2101919A1 (en) 1971-07-22
US3678306A (en) 1972-07-18

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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