EP1534945A4 - Turboreacteurs a derivation integree destines a des aeronefs et a d'autres vehicules - Google Patents

Turboreacteurs a derivation integree destines a des aeronefs et a d'autres vehicules

Info

Publication number
EP1534945A4
EP1534945A4 EP03799749A EP03799749A EP1534945A4 EP 1534945 A4 EP1534945 A4 EP 1534945A4 EP 03799749 A EP03799749 A EP 03799749A EP 03799749 A EP03799749 A EP 03799749A EP 1534945 A4 EP1534945 A4 EP 1534945A4
Authority
EP
European Patent Office
Prior art keywords
aircraft
vehicles
turbojet engines
integrated bypass
bypass turbojet
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.)
Withdrawn
Application number
EP03799749A
Other languages
German (de)
English (en)
Other versions
EP1534945A2 (fr
Inventor
Marius A Paul
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.)
PAUL Marius A
Original Assignee
Individual
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
Priority claimed from US10/292,892 external-priority patent/US6733436B2/en
Priority claimed from US10/337,032 external-priority patent/US20030192304A1/en
Priority claimed from US10/383,462 external-priority patent/US6966174B2/en
Application filed by Individual filed Critical Individual
Publication of EP1534945A2 publication Critical patent/EP1534945A2/fr
Publication of EP1534945A4 publication Critical patent/EP1534945A4/fr
Withdrawn legal-status Critical Current

Links

Classifications

    • 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
    • F02C3/045—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor having compressor and turbine passages in a single rotor-module
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C29/00—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft
    • B64C29/0008—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded
    • B64C29/0041—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors
    • B64C29/0075—Aircraft capable of landing or taking-off vertically, e.g. vertical take-off and landing [VTOL] aircraft having its flight directional axis horizontal when grounded the lift during taking-off being created by jet motors the motors being tiltable relative to the fuselage
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plants in aircraft; Aircraft characterised by the type or position of power plants
    • B64D27/02—Aircraft characterised by the type or position of power plants
    • B64D27/16—Aircraft characterised by the type or position of power plants of jet type
    • 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
    • F01D5/022—Blade-carrying members, e.g. rotors with concentric rows of axial blades
    • 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
    • F02C3/073—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 the compressor and turbine stages being concentric
    • 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
    • F02C3/08—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor the compressor comprising at least one radial stage
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/077—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type the plant being of the multiple flow type, i.e. having three or more flows
    • 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
    • Y02T50/40—Weight reduction
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
EP03799749A 2002-04-15 2003-04-09 Turboreacteurs a derivation integree destines a des aeronefs et a d'autres vehicules Withdrawn EP1534945A4 (fr)

Applications Claiming Priority (13)

Application Number Priority Date Filing Date Title
US292892 1999-04-16
US37261802P 2002-04-15 2002-04-15
US372618P 2002-04-15
US37473702P 2002-04-23 2002-04-23
US374737P 2002-04-23
US40546002P 2002-08-23 2002-08-23
US405460P 2002-08-23
US10/292,892 US6733436B2 (en) 2002-07-09 2002-11-12 Detachable combination instrument for health-care and treatment
US10/337,032 US20030192304A1 (en) 2002-04-15 2003-01-06 Integrated bypass turbojet engines for aircraft and other vehicles
US337032 2003-01-06
US383462 2003-03-06
US10/383,462 US6966174B2 (en) 2002-04-15 2003-03-06 Integrated bypass turbojet engines for air craft and other vehicles
PCT/US2003/010855 WO2004092567A2 (fr) 2002-04-15 2003-04-09 Turboreacteurs a derivation integree destines a des aeronefs et a d'autres vehicules

Publications (2)

Publication Number Publication Date
EP1534945A2 EP1534945A2 (fr) 2005-06-01
EP1534945A4 true EP1534945A4 (fr) 2006-08-30

Family

ID=33304243

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03799749A Withdrawn EP1534945A4 (fr) 2002-04-15 2003-04-09 Turboreacteurs a derivation integree destines a des aeronefs et a d'autres vehicules

Country Status (4)

Country Link
EP (1) EP1534945A4 (fr)
AU (1) AU2003299459A1 (fr)
CA (1) CA2484580A1 (fr)
WO (1) WO2004092567A2 (fr)

Families Citing this family (50)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1825128B1 (fr) 2004-12-01 2011-03-02 United Technologies Corporation Refroidissement régénératif des aubes et pales de turbine pour moteur à turbine d'extrémité
EP1825111B1 (fr) 2004-12-01 2011-08-31 United Technologies Corporation Carter de compresseur à rotation inverse pour un moteur à turbine en bout
US8641367B2 (en) 2004-12-01 2014-02-04 United Technologies Corporation Plurality of individually controlled inlet guide vanes in a turbofan engine and corresponding controlling method
US8561383B2 (en) 2004-12-01 2013-10-22 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
EP1828574B1 (fr) 2004-12-01 2010-11-03 United Technologies Corporation Ensemble de boite de vitesses a couplage proximal pour moteur de turbine a pression d'entree
EP1819907A2 (fr) 2004-12-01 2007-08-22 United Technologies Corporation Pale de ventilateur comprenant une section de diffuseur integrale et une section de pale de turbine a aube destine a une moteur a turbine a aube
WO2006059981A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Joint hydraulique pour boite de vitesses de moteur a turbine d'extremite
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
WO2006059994A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Ensemble de joint pour rotor de turbine-ventilateur de moteur de turbine a pression d’entree
WO2006059997A2 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Elements annulaires de rotor de turbine
EP2333286A1 (fr) * 2004-12-01 2011-06-15 United Technologies Corporation Vectorisation de conduite de transition pour moteur de turbine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
WO2006060004A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Dispositif de combustion pour moteur de turbine
WO2006060011A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Moteur a turbine de pointe comprenant un compartiment non rotatif
WO2006059977A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Moteur a turbine de bout et procede de mise en oeuvre correspondant
US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
WO2006059987A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Séparateur de particules pour moteur à turbine en bout
DE602004019710D1 (de) 2004-12-01 2009-04-09 United Technologies Corp Fernbetätigung für eine verstellbare stufe eines verdichters für einen turbinenmotor
EP1841959B1 (fr) 2004-12-01 2012-05-09 United Technologies Corporation Ailettes de rotor de soufflante pour moteur a turbine en bout
WO2006059971A2 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Logement de moteur a turbine integrant un ventilateur, un combustor, et une turbine
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
WO2006059980A2 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Aspiration par diffuseur pour moteur a turbine d'extremite
DE602004031986D1 (de) 2004-12-01 2011-05-05 United Technologies Corp Gebläse-turbinen-rotoranordnung für einen spitzenturbinenmotor
WO2006110125A2 (fr) * 2004-12-01 2006-10-19 United Technologies Corporation Elements annulaires empiles pour moteurs a turbine
DE602004016059D1 (de) 2004-12-01 2008-10-02 United Technologies Corp Tip-turbinentriebwerk mit wärmetauscher
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
US7631480B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Modular tip turbine engine
WO2006060009A1 (fr) 2004-12-01 2006-06-08 United Technologies Corporation Moteur à aubes de turbine comprenant des groupes d'aubes et une disposition de blocage de fixation radial pour ceux-ci
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
WO2006059975A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Foyer peripherique pour moteur a turbine de bout
WO2006059985A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Compresseur axial pour moteur a turbine de bout
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
EP1825177B1 (fr) 2004-12-01 2012-01-25 United Technologies Corporation Purgeur gonflable destine a un moteur a turbine et methode de reglage d'air de purge
WO2006060000A1 (fr) * 2004-12-01 2006-06-08 United Technologies Corporation Ensemble aubes de guidage d'admission de soufflante variable, turbomachine dotee d'un tel ensemble et procede de commande correspondant
EP1825116A2 (fr) 2004-12-01 2007-08-29 United Technologies Corporation Refroidissement par ejecteur de l'enveloppe exterieure d'un moteur a turbine de bout
EP1831519B1 (fr) 2004-12-01 2010-08-04 United Technologies Corporation Moteur à turbine en bout avec étages soufflante et turbine multiples
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
WO2006062497A1 (fr) 2004-12-04 2006-06-15 United Technologies Corporation Bâti moteur à turbine en bout de pale
US7201558B2 (en) 2005-05-05 2007-04-10 United Technologies Corporation Seal arrangement for a fan-turbine rotor assembly
RU2332332C2 (ru) * 2006-04-20 2008-08-27 Иннокентий Михайлович Большанин Самолет с вертикальными взлетом и посадкой
US20130019585A1 (en) * 2007-05-11 2013-01-24 Brian Merry Variable fan inlet guide vane for turbine engine
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
CN107813947A (zh) * 2017-11-27 2018-03-20 大连理工大学 一种利用排气续航的混合动力无人飞行器
US10989408B2 (en) 2018-09-13 2021-04-27 Raytheon Technologies Corporation Additive integral combustor expansion spring
CN111332477B (zh) * 2020-02-21 2022-09-20 中国电子科技集团公司第二十九研究所 一种逆升压涡轮旁路控制装置及方法
US11549463B2 (en) * 2021-02-22 2023-01-10 General Electric Company Compact low-pressure compressor
CN116677498B (zh) * 2023-08-03 2023-10-17 中国航发四川燃气涡轮研究院 基于氢能的新型高超声速组合发动机

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US2611241A (en) * 1946-03-19 1952-09-23 Packard Motor Car Co Power plant comprising a toroidal combustion chamber and an axial flow gas turbine with blade cooling passages therein forming a centrifugal air compressor
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Title
No further relevant documents disclosed *

Also Published As

Publication number Publication date
WO2004092567A2 (fr) 2004-10-28
AU2003299459A1 (en) 2004-11-04
CA2484580A1 (fr) 2004-10-28
WO2004092567A3 (fr) 2005-04-07
EP1534945A2 (fr) 2005-06-01

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Inventor name: PAUL, MARIUS A.

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