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EP1534945A4 - Integrated bypass turbojet engines for aircraft and other vehicles - Google Patents

Integrated bypass turbojet engines for aircraft and other vehicles

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Withdrawn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)
French (fr)
Other versions
EP1534945A2 (en
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/en
Publication of EP1534945A4 publication Critical patent/EP1534945A4/en
Withdrawn legal-status Critical Current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 Integrated bypass turbojet engines for aircraft and other vehicles Withdrawn EP1534945A4 (en)

Applications Claiming Priority (13)

Application Number Priority Date Filing Date Title
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
US292892 2002-11-12
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
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 (en) 2002-04-15 2003-04-09 Integrated bypass turbojet engines for aircraft and other vehicles

Publications (2)

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

Family

ID=33304243

Family Applications (1)

Application Number Title Priority Date Filing Date
EP03799749A Withdrawn EP1534945A4 (en) 2002-04-15 2003-04-09 Integrated bypass turbojet engines for aircraft and other vehicles

Country Status (4)

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

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EP1841959B1 (en) 2004-12-01 2012-05-09 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
DE602004031470D1 (en) * 2004-12-01 2011-03-31 United Technologies Corp TRANSITION CHANNEL WITH MEANS FOR FLOW VECTOR INFLUENCE ON A GAS TURBINE
EP1828547B1 (en) 2004-12-01 2011-11-30 United Technologies Corporation Turbofan comprising a plurality of individually controlled inlet guide vanes and corresponding controlling method
EP1828683B1 (en) 2004-12-01 2013-04-10 United Technologies Corporation Combustor for turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
WO2006059980A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Diffuser aspiration for a tip turbine engine
DE602004031679D1 (en) 2004-12-01 2011-04-14 United Technologies Corp Regenerative cooling of a guide and blade for a tipturbine engine
US7631485B2 (en) 2004-12-01 2009-12-15 United Technologies Corporation Tip turbine engine with a heat exchanger
EP1828568B1 (en) 2004-12-01 2011-03-23 United Technologies Corporation Fan-turbine rotor assembly for a tip turbine engine
EP1825177B1 (en) 2004-12-01 2012-01-25 United Technologies Corporation Inflatable bleed valve for turbine engine and method of controlling bleed air
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
WO2006059986A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine and operating method with reverse core airflow
DE602004023769D1 (en) * 2004-12-01 2009-12-03 United Technologies Corp STACKED RINGING COMPONENTS FOR TURBINE ENGINES
WO2006059970A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
WO2006060012A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
EP1831520B1 (en) 2004-12-01 2009-02-25 United Technologies Corporation Tip turbine engine and corresponding operating method
EP1828545A2 (en) 2004-12-01 2007-09-05 United Technologies Corporation Annular turbine ring rotor
US8365511B2 (en) 2004-12-01 2013-02-05 United Technologies Corporation Tip turbine engine integral case, vane, mount and mixer
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
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
EP1831519B1 (en) 2004-12-01 2010-08-04 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
WO2006059995A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Gearbox lubrication supply system for a tip turbine engine
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
DE602004032186D1 (en) 2004-12-01 2011-05-19 United Technologies Corp Turbine blade group of a fan rotor and method for assembling such a group
DE602004027766D1 (en) 2004-12-01 2010-07-29 United Technologies Corp HYDRAULIC SEAL FOR A GEARBOX OF A TOP TURBINE ENGINE
US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US7959406B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
WO2006060011A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
WO2006060006A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine non-metallic tailcone
WO2006059994A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
EP1825113B1 (en) 2004-12-01 2012-10-24 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
EP1825112B1 (en) 2004-12-01 2013-10-23 United Technologies Corporation Cantilevered tip turbine engine
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
EP1831530B1 (en) 2004-12-01 2009-02-25 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
WO2006059989A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine support structure
US8061968B2 (en) 2004-12-01 2011-11-22 United Technologies Corporation Counter-rotating compressor case and assembly method for tip turbine engine
WO2006059988A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Modular tip turbine engine
US7980054B2 (en) 2004-12-01 2011-07-19 United Technologies Corporation Ejector cooling of outer case for tip turbine engine
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 (en) * 2017-11-27 2018-03-20 大连理工大学 A kind of hybrid power unmanned vehicle using exhaust continuation of the journey
US10989408B2 (en) 2018-09-13 2021-04-27 Raytheon Technologies Corporation Additive integral combustor expansion spring
CN111332477B (en) * 2020-02-21 2022-09-20 中国电子科技集团公司第二十九研究所 Reverse boosting turbine bypass control device and method
US11549463B2 (en) * 2021-02-22 2023-01-10 General Electric Company Compact low-pressure compressor
CN116677498B (en) * 2023-08-03 2023-10-17 中国航发四川燃气涡轮研究院 Novel hypersonic combined engine based on hydrogen energy

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Also Published As

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

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AX Request for extension of the european patent

Extension state: AL LT LV MK

RAP1 Party data changed (applicant data changed or rights of an application transferred)

Owner name: PAUL, MARIUS A.

RIN1 Information on inventor provided before grant (corrected)

Inventor name: PAUL, MARIUS A.

RIC1 Information provided on ipc code assigned before grant

Ipc: F02K 3/068 20060101ALI20060420BHEP

Ipc: F02C 1/00 20060101AFI20050413BHEP

A4 Supplementary search report drawn up and despatched

Effective date: 20060731

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Effective date: 20061020

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