WO2005017332A3 - Moteur de turbine a gaz a chambre de combustion rotative - Google Patents

Moteur de turbine a gaz a chambre de combustion rotative Download PDF

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Publication number
WO2005017332A3
WO2005017332A3 PCT/US2004/000641 US2004000641W WO2005017332A3 WO 2005017332 A3 WO2005017332 A3 WO 2005017332A3 US 2004000641 W US2004000641 W US 2004000641W WO 2005017332 A3 WO2005017332 A3 WO 2005017332A3
Authority
WO
WIPO (PCT)
Prior art keywords
rotating
gas turbine
combustion system
turbine engine
design
Prior art date
Application number
PCT/US2004/000641
Other languages
English (en)
Other versions
WO2005017332A2 (fr
Inventor
Keogh Rory
Original Assignee
Keogh Rory
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 Keogh Rory filed Critical Keogh Rory
Publication of WO2005017332A2 publication Critical patent/WO2005017332A2/fr
Publication of WO2005017332A3 publication Critical patent/WO2005017332A3/fr

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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
    • F02C3/14—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant
    • F02C3/16—Gas-turbine plants characterised by the use of combustion products as the working fluid characterised by the arrangement of the combustion chamber in the plant the combustion chambers being formed at least partly in the turbine rotor or in an other rotating part of the plant
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/56—Combustion chambers having rotary flame tubes
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

L'invention concerne une conception de moteur de turbine à gaz mettant en oeuvre un système de combustion rotatif, ce qui permet de simplifier la conception et d'améliorer l'efficacité et la densité de puissance par rapport aux petites turbines à gaz antérieures. Cette nouvelle conception comprend une hélice radiale couplée à un système de combustion rotatif. L'écoulement provenant dudit système pénètre dans une tuyère de turbine rotative, puis quitte le cadre de référence rotatif et est diffusé dans un diffuseur radial immobile. Le système de combustion est géométriquement fixe par rapport à l'hélice et aux aubes de la tuyère de turbine, toutes les aubes présentant la même vitesse de rotation autour d'un axe de rotation commun. La présente invention peut être mise en oeuvre grâce à la possibilité de concevoir et de construire un système de combustion suffisamment petit pour s'ajuster à l'intérieur du circuit d'écoulement d'une hélice rotative. Ce système de combustion rotatif permet également de ne plus avoir besoin de la plupart des composants non rotatifs ou immobiles à l'intérieur du moteur de la turbine à gaz. L'invention permet ainsi de réduire le coût du moteur et d'éliminer la baisse d'efficacité et de puissance de sortie liée à l'utilisation de composants immobiles.
PCT/US2004/000641 2003-01-10 2004-01-12 Moteur de turbine a gaz a chambre de combustion rotative WO2005017332A2 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
US43939003P 2003-01-10 2003-01-10
US60/439,390 2003-01-10

Publications (2)

Publication Number Publication Date
WO2005017332A2 WO2005017332A2 (fr) 2005-02-24
WO2005017332A3 true WO2005017332A3 (fr) 2005-06-09

Family

ID=34192965

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/US2004/000641 WO2005017332A2 (fr) 2003-01-10 2004-01-12 Moteur de turbine a gaz a chambre de combustion rotative

Country Status (1)

Country Link
WO (1) WO2005017332A2 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
NO326633B1 (no) 2006-12-28 2009-01-26 Age Jorgen Skomsvold Fremgangsmate og anordning for motor- og kompresjonsprosess
DE102010048434B4 (de) 2010-10-15 2017-08-10 Baltico Gmbh Turbinenradanordnung für eine Gas- oder Dampfturbine
EP2992199B1 (fr) * 2013-04-29 2017-03-22 Xeicle Limited Ensemble rotor pour moteur à cycle ouvert, et moteur à cycle ouvert

Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3417564A (en) * 1967-04-19 1968-12-24 John G. Call Jet engine with relatively rotatable combustion means, intake manifold and exhaust manifold
US3469396A (en) * 1966-07-02 1969-09-30 Shigeru Onishi Gas turbine
US3557551A (en) * 1968-09-26 1971-01-26 Gordon Keith Colin Campbell Gas turbine engine with rotating combustion chamber
US4724670A (en) * 1983-01-07 1988-02-16 Josie M. Greer, Administratrix Turbine engine
US5960625A (en) * 1998-08-21 1999-10-05 Zdvorak, Sr.; Edward H. Constant volume combustion turbine with plurality flow turbine wheels

Patent Citations (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3469396A (en) * 1966-07-02 1969-09-30 Shigeru Onishi Gas turbine
US3417564A (en) * 1967-04-19 1968-12-24 John G. Call Jet engine with relatively rotatable combustion means, intake manifold and exhaust manifold
US3557551A (en) * 1968-09-26 1971-01-26 Gordon Keith Colin Campbell Gas turbine engine with rotating combustion chamber
US4724670A (en) * 1983-01-07 1988-02-16 Josie M. Greer, Administratrix Turbine engine
US5960625A (en) * 1998-08-21 1999-10-05 Zdvorak, Sr.; Edward H. Constant volume combustion turbine with plurality flow turbine wheels

Also Published As

Publication number Publication date
WO2005017332A2 (fr) 2005-02-24

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