EP1534945A4 - Turbostrahltriebwerke mit integriertem bypass für flugzeuge und andere fahrzeuge - Google Patents

Turbostrahltriebwerke mit integriertem bypass für flugzeuge und andere fahrzeuge

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Withdrawn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
English (en)
French (fr)
Other versions
EP1534945A2 (de
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/de
Publication of EP1534945A4 publication Critical patent/EP1534945A4/de
Withdrawn legal-status Critical Current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; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D27/00—Arrangement or mounting of power plant in aircraft; Aircraft characterised thereby
    • B64D27/02—Aircraft characterised by the type or position of power plant
    • B64D27/16—Aircraft characterised by the type or position of power plant 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
EP03799749A 2002-04-15 2003-04-09 Turbostrahltriebwerke mit integriertem bypass für flugzeuge und andere fahrzeuge Withdrawn EP1534945A4 (de)

Applications Claiming Priority (13)

Application Number Priority Date Filing Date Title
US292892 1981-08-14
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
US337032 2003-01-06
US10/337,032 US20030192304A1 (en) 2002-04-15 2003-01-06 Integrated bypass turbojet engines for aircraft and other vehicles
US10/383,462 US6966174B2 (en) 2002-04-15 2003-03-06 Integrated bypass turbojet engines for air craft and other vehicles
US383462 2003-03-06
PCT/US2003/010855 WO2004092567A2 (en) 2002-04-15 2003-04-09 Integrated bypass turbojet engines for aircraft and other vehicles

Publications (2)

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

Family

ID=33304243

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03799749A Withdrawn EP1534945A4 (de) 2002-04-15 2003-04-09 Turbostrahltriebwerke mit integriertem bypass für flugzeuge und andere fahrzeuge

Country Status (4)

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

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US7959406B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
EP1834076B1 (de) 2004-12-01 2011-04-06 United Technologies Corporation Turbinenschaufelgruppe eines Fanrotors sowie Verfahren zur Montage einer solchen Gruppe
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
WO2006060011A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
WO2006110123A2 (en) * 2004-12-01 2006-10-19 United Technologies Corporation Vectoring transition duct for turbine engine
US8468795B2 (en) 2004-12-01 2013-06-25 United Technologies Corporation Diffuser aspiration for a tip turbine engine
WO2006059990A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Regenerative turbine blade and vane cooling for a tip turbine engine
WO2006110122A2 (en) 2004-12-01 2006-10-19 United Technologies Corporation Inflatable bleed valve for a turbine engine and a method of operating therefore
EP1828547B1 (de) 2004-12-01 2011-11-30 United Technologies Corporation Turbofantriebwerk mit einer Mehrzahl von einzeln steuerbaren Einlassleitschaufeln und zugehöriges Steuerverfahren
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
DE602004023769D1 (de) * 2004-12-01 2009-12-03 United Technologies Corp Gestapelte ringförmige bauteile für turbinenmotoren
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US8152469B2 (en) 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
WO2006059971A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
WO2006059994A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
WO2006060014A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Starter generator system for a tip turbine engine
WO2006059989A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine support structure
US8807936B2 (en) 2004-12-01 2014-08-19 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
DE602004031986D1 (de) 2004-12-01 2011-05-05 United Technologies Corp Gebläse-turbinen-rotoranordnung für einen spitzenturbinenmotor
WO2006059970A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
DE602004028528D1 (de) 2004-12-01 2010-09-16 United Technologies Corp Tip-Turbinentriebwerk mit mehreren Gebläse- und Turbinenstufen
US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US8096753B2 (en) 2004-12-01 2012-01-17 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
EP1825170B1 (de) 2004-12-01 2009-03-18 United Technologies Corporation Schmiermittel-versorgungssystem für das getriebe eines tip-turbinen-triebwerks
WO2006060003A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
EP1825113B1 (de) 2004-12-01 2012-10-24 United Technologies Corporation Gegenläufiges getriebe für ein tip-turbinen-triebwerk
WO2006059972A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
US7631480B2 (en) * 2004-12-01 2009-12-15 United Technologies Corporation Modular tip turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
US8024931B2 (en) 2004-12-01 2011-09-27 United Technologies Corporation Combustor for turbine engine
US8061968B2 (en) 2004-12-01 2011-11-22 United Technologies Corporation Counter-rotating compressor case and assembly method for tip turbine engine
EP1825112B1 (de) 2004-12-01 2013-10-23 United Technologies Corporation Freigetragene tipturbinentriebwerk
WO2006059985A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Axial compressor for tip turbine engine
WO2006059979A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral case, vane, mount, and mixer
WO2006060006A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine non-metallic tailcone
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
US7921636B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Tip turbine engine and corresponding operating method
WO2006062497A1 (en) 2004-12-04 2006-06-15 United Technologies Corporation Tip turbine engine mount
US7201558B2 (en) 2005-05-05 2007-04-10 United Technologies Corporation Seal arrangement for a fan-turbine rotor assembly
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
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Also Published As

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

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Owner name: PAUL, MARIUS A.

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Inventor name: PAUL, MARIUS A.

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Ipc: F02K 3/068 20060101ALI20060420BHEP

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