WO2004092567A3 - Integrated bypass turbojet engines for aircraft and other vehicles - Google Patents

Integrated bypass turbojet engines for aircraft and other vehicles Download PDF

Info

Publication number
WO2004092567A3
WO2004092567A3 PCT/US2003/010855 US0310855W WO2004092567A3 WO 2004092567 A3 WO2004092567 A3 WO 2004092567A3 US 0310855 W US0310855 W US 0310855W WO 2004092567 A3 WO2004092567 A3 WO 2004092567A3
Authority
WO
WIPO (PCT)
Prior art keywords
aircraft
vehicles
turbojet engines
integrated bypass
bypass turbojet
Prior art date
Application number
PCT/US2003/010855
Other languages
French (fr)
Other versions
WO2004092567A2 (en
Inventor
Paul A Marius
Original Assignee
Paul A Marius
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 Paul A Marius filed Critical Paul A Marius
Priority to EP03799749A priority Critical patent/EP1534945A4/en
Priority to CA002484580A priority patent/CA2484580A1/en
Priority to AU2003299459A priority patent/AU2003299459A1/en
Publication of WO2004092567A2 publication Critical patent/WO2004092567A2/en
Publication of WO2004092567A3 publication Critical patent/WO2004092567A3/en

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

Abstract

A turbo jet engine comprises a fan unit (10a) which combines a fan (11a), centrifugal compressor cells (11b), and turbine blades (11c). Air flowing through the centrifugal compressor cells (11b) is supplied to a peripheral combustor (12), and air flowing through the fan (11a) cools the air flowing through the compressor cells (11b) and bypasses the combustor (12). Turbine exhaust and bypass air are then ejected through a common nozzle (9).
PCT/US2003/010855 2002-04-15 2003-04-09 Integrated bypass turbojet engines for aircraft and other vehicles WO2004092567A2 (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
EP03799749A EP1534945A4 (en) 2002-04-15 2003-04-09 Integrated bypass turbojet engines for aircraft and other vehicles
CA002484580A CA2484580A1 (en) 2002-04-15 2003-04-09 Integrated bypass turbojet engines for aircraft and other vehicles
AU2003299459A AU2003299459A1 (en) 2002-04-15 2003-04-09 Integrated bypass turbojet engines for aircraft and other vehicles

Applications Claiming Priority (12)

Application Number Priority Date Filing Date Title
US37261802P 2002-04-15 2002-04-15
US60/372,618 2002-04-15
US37473702P 2002-04-23 2002-04-23
US60/374,737 2002-04-23
US40546002P 2002-08-23 2002-08-23
US60/405,460 2002-08-23
US10,292,892 2002-11-12
US10/292,892 US6733436B2 (en) 2002-07-09 2002-11-12 Detachable combination instrument for health-care and treatment
US10/337,032 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
US10/383,462 2003-03-06

Publications (2)

Publication Number Publication Date
WO2004092567A2 WO2004092567A2 (en) 2004-10-28
WO2004092567A3 true WO2004092567A3 (en) 2005-04-07

Family

ID=33304243

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2003/010855 WO2004092567A2 (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)

Cited By (30)

* Cited by examiner, † Cited by third party
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US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
US7878762B2 (en) 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
US7883314B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
US7887296B2 (en) 2004-12-01 2011-02-15 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
US7921636B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Tip turbine engine and corresponding operating method
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7927075B2 (en) 2004-12-01 2011-04-19 United Technologies Corporation Fan-turbine rotor assembly for a tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7959406B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a 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
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
US8104257B2 (en) 2004-12-01 2012-01-31 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
US8152469B2 (en) 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US8807936B2 (en) 2004-12-01 2014-08-19 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow

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WO2006059988A1 (en) * 2004-12-01 2006-06-08 United Technologies Corporation Modular tip turbine engine
US7607286B2 (en) 2004-12-01 2009-10-27 United Technologies Corporation Regenerative turbine blade and vane cooling for a tip turbine engine
US9845727B2 (en) 2004-12-01 2017-12-19 United Technologies Corporation Tip turbine engine composite tailcone
EP1828546B1 (en) 2004-12-01 2009-10-21 United Technologies Corporation Stacked annular components for turbine engines
EP1825111B1 (en) 2004-12-01 2011-08-31 United Technologies Corporation Counter-rotating compressor case for a tip turbine engine
WO2006059980A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Diffuser aspiration for a tip turbine engine
US9003759B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Particle separator for tip turbine engine
WO2006059979A1 (en) 2004-12-01 2006-06-08 United Technologies Corporation Tip turbine engine integral case, vane, mount, and mixer
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
WO2006059970A2 (en) 2004-12-01 2006-06-08 United Technologies Corporation Turbine engine with differential gear driven fan and compressor
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
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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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
US2694291A (en) * 1948-02-07 1954-11-16 Henning C Rosengart Rotor and combustion chamber arrangement for gas turbines
US3112610A (en) * 1961-02-27 1963-12-03 Joseph J Jerger Constant pressure shrouded propeller
US3283509A (en) * 1963-02-21 1966-11-08 Messerschmitt Boelkow Blohm Lifting engine for vtol aircraft
US3603082A (en) * 1970-02-18 1971-09-07 Curtiss Wright Corp Combustor for gas turbine having a compressor and turbine passages in a single rotor element
US3606210A (en) * 1969-11-06 1971-09-20 Ralph E Busby Engine mounting for vtol aircraft and the like
US3705775A (en) * 1970-01-15 1972-12-12 Snecma Gas turbine power plants
US3892069A (en) * 1971-11-05 1975-07-01 Robert Julian Hansford Propulsion units
US3899886A (en) * 1973-11-19 1975-08-19 Gen Motors Corp Gas turbine engine control
US4860537A (en) * 1986-08-29 1989-08-29 Brandt, Inc. High bypass ratio counterrotating gearless front fan engine

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Publication number Priority date Publication date Assignee Title
US2404767A (en) * 1941-10-28 1946-07-23 Armstrong Siddeley Motors Ltd Jet propulsion plant
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
US2694291A (en) * 1948-02-07 1954-11-16 Henning C Rosengart Rotor and combustion chamber arrangement for gas turbines
US3112610A (en) * 1961-02-27 1963-12-03 Joseph J Jerger Constant pressure shrouded propeller
US3283509A (en) * 1963-02-21 1966-11-08 Messerschmitt Boelkow Blohm Lifting engine for vtol aircraft
US3606210A (en) * 1969-11-06 1971-09-20 Ralph E Busby Engine mounting for vtol aircraft and the like
US3705775A (en) * 1970-01-15 1972-12-12 Snecma Gas turbine power plants
US3603082A (en) * 1970-02-18 1971-09-07 Curtiss Wright Corp Combustor for gas turbine having a compressor and turbine passages in a single rotor element
US3892069A (en) * 1971-11-05 1975-07-01 Robert Julian Hansford Propulsion units
US3899886A (en) * 1973-11-19 1975-08-19 Gen Motors Corp Gas turbine engine control
US4860537A (en) * 1986-08-29 1989-08-29 Brandt, Inc. High bypass ratio counterrotating gearless front fan engine

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Cited By (32)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7959532B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Hydraulic seal for a gearbox of a tip turbine engine
US8033092B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Tip turbine engine integral fan, combustor, and turbine case
US7874163B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Starter generator system for a tip turbine engine
US7874802B2 (en) 2004-12-01 2011-01-25 United Technologies Corporation Tip turbine engine comprising turbine blade clusters and method of assembly
US7878762B2 (en) 2004-12-01 2011-02-01 United Technologies Corporation Tip turbine engine comprising turbine clusters and radial attachment lock arrangement therefor
US7883315B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan rotor of a tip turbine engine
US7845157B2 (en) 2004-12-01 2010-12-07 United Technologies Corporation Axial compressor for tip turbine engine
US7882695B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Turbine blow down starter for turbine engine
US7883314B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Seal assembly for a fan-turbine rotor of a tip turbine engine
US7887296B2 (en) 2004-12-01 2011-02-15 United Technologies Corporation Fan blade with integral diffuser section and tip turbine blade section for a tip turbine engine
US7921636B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Tip turbine engine and corresponding operating method
US7921635B2 (en) 2004-12-01 2011-04-12 United Technologies Corporation Peripheral combustor for tip turbine engine
US7927075B2 (en) 2004-12-01 2011-04-19 United Technologies Corporation Fan-turbine rotor assembly for a tip turbine engine
US7934902B2 (en) 2004-12-01 2011-05-03 United Technologies Corporation Compressor variable stage remote actuation for turbine engine
US9541092B2 (en) 2004-12-01 2017-01-10 United Technologies Corporation Tip turbine engine with reverse core airflow
US7937927B2 (en) 2004-12-01 2011-05-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7882694B2 (en) 2004-12-01 2011-02-08 United Technologies Corporation Variable fan inlet guide vane assembly for gas turbine engine
US7976273B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Tip turbine engine support structure
US7976272B2 (en) 2004-12-01 2011-07-12 United Technologies Corporation Inflatable bleed valve for a 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
US8033094B2 (en) 2004-12-01 2011-10-11 United Technologies Corporation Cantilevered tip turbine engine
US7854112B2 (en) 2004-12-01 2010-12-21 United Technologies Corporation Vectoring transition duct for turbine engine
US8083030B2 (en) 2004-12-01 2011-12-27 United Technologies Corporation Gearbox lubrication supply system for a tip engine
US8104257B2 (en) 2004-12-01 2012-01-31 United Technologies Corporation Tip turbine engine with multiple fan and turbine stages
US8152469B2 (en) 2004-12-01 2012-04-10 United Technologies Corporation Annular turbine ring rotor
US8757959B2 (en) 2004-12-01 2014-06-24 United Technologies Corporation Tip turbine engine comprising a nonrotable compartment
US8807936B2 (en) 2004-12-01 2014-08-19 United Technologies Corporation Balanced turbine rotor fan blade for a tip turbine engine
US8950171B2 (en) 2004-12-01 2015-02-10 United Technologies Corporation Counter-rotating gearbox for tip turbine engine
US7959406B2 (en) 2004-12-01 2011-06-14 United Technologies Corporation Close coupled gearbox assembly for a tip turbine engine
US9003768B2 (en) 2004-12-01 2015-04-14 United Technologies Corporation Variable fan inlet guide vane assembly, turbine engine with such an assembly and corresponding controlling method
US8967945B2 (en) 2007-05-22 2015-03-03 United Technologies Corporation Individual inlet guide vane control for tip turbine engine

Also Published As

Publication number Publication date
EP1534945A2 (en) 2005-06-01
WO2004092567A2 (en) 2004-10-28
AU2003299459A1 (en) 2004-11-04
CA2484580A1 (en) 2004-10-28
EP1534945A4 (en) 2006-08-30

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