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FR2360758A1 - Moteur a turbine a gaz d'avion - Google Patents

Moteur a turbine a gaz d'avion

Info

Publication number
FR2360758A1
FR2360758A1 FR7722512A FR7722512A FR2360758A1 FR 2360758 A1 FR2360758 A1 FR 2360758A1 FR 7722512 A FR7722512 A FR 7722512A FR 7722512 A FR7722512 A FR 7722512A FR 2360758 A1 FR2360758 A1 FR 2360758A1
Authority
FR
France
Prior art keywords
turbine
compressor
differential gear
blower
drive shafts
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Withdrawn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
FR7722512A
Other languages
English (en)
Inventor
Arthur Paul Adamson
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of FR2360758A1 publication Critical patent/FR2360758A1/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Withdrawn legal-status Critical Current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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/36—Power transmission arrangements between the different shafts of the gas turbine plant, or between the gas-turbine plant and the power user
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
    • F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/327—Application in turbines in gas turbines to drive shrouded, high solidity propeller
    • 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)
  • Supercharger (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Moteur dans lequel on peut moduler l'extraction d'énergie par le compresseur et la soufflante. Il comprend un train d'engrenages différentiel 34 interposé entre la turbine 32, d'une part, et le compresseur 16 et la soufflante 14, d'autre part ce train d'engrenages différentiel commandant les vitesses de rotation relatives de telle sorte que la vitesse de la turbine est égale à la somme de la vitesse de rotation du compresseur multipliée par une constante et de la vitesse de rotation de la soufflante multipliée par une constante. L'invention cet applicable notamment aux réacteurs d'avion.
FR7722512A 1976-08-02 1977-07-22 Moteur a turbine a gaz d'avion Withdrawn FR2360758A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US71042376A 1976-08-02 1976-08-02

Publications (1)

Publication Number Publication Date
FR2360758A1 true FR2360758A1 (fr) 1978-03-03

Family

ID=24853961

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7722512A Withdrawn FR2360758A1 (fr) 1976-08-02 1977-07-22 Moteur a turbine a gaz d'avion

Country Status (3)

Country Link
JP (1) JPS5331011A (fr)
DE (1) DE2733986A1 (fr)
FR (1) FR2360758A1 (fr)

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2641332A1 (fr) * 1989-01-03 1990-07-06 Gen Electric Turboreacteur a double flux comportant une turbine d'entrainement de soufflante contrarotative partiellement accouplee par un engrenage
WO2014023891A1 (fr) * 2012-08-09 2014-02-13 Snecma Turbomachine comportant une pluralité d'aubes radiales fixes montées en amont de la soufflante
US9879561B2 (en) 2012-08-09 2018-01-30 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
US9885291B2 (en) 2012-08-09 2018-02-06 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
WO2020058652A1 (fr) * 2018-09-21 2020-03-26 Safran Aircraft Engines Turboréacteur comprenant un dispositif d'apport de puissance
FR3086342A1 (fr) * 2018-09-21 2020-03-27 Safran Aircraft Engines Turboreacteur a reducteur
US11421603B2 (en) 2018-09-21 2022-08-23 Safran Aircraft Engines Turbojet with step-down mechanism

Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1301653B (de) * 1964-07-20 1969-08-21 Rolls Royce Gasturbinenstrahltriebwerk mit zwei gegenlaeufig rotierenden Wellen

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1301653B (de) * 1964-07-20 1969-08-21 Rolls Royce Gasturbinenstrahltriebwerk mit zwei gegenlaeufig rotierenden Wellen

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
EXBK/68 *

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2641332A1 (fr) * 1989-01-03 1990-07-06 Gen Electric Turboreacteur a double flux comportant une turbine d'entrainement de soufflante contrarotative partiellement accouplee par un engrenage
WO2014023891A1 (fr) * 2012-08-09 2014-02-13 Snecma Turbomachine comportant une pluralité d'aubes radiales fixes montées en amont de la soufflante
FR2994452A1 (fr) * 2012-08-09 2014-02-14 Snecma Turbomachine comportant une pluralite d'aubes radiales fixes montees en amont de la soufflante
US9835044B2 (en) 2012-08-09 2017-12-05 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
US9879561B2 (en) 2012-08-09 2018-01-30 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
US9885291B2 (en) 2012-08-09 2018-02-06 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
WO2020058652A1 (fr) * 2018-09-21 2020-03-26 Safran Aircraft Engines Turboréacteur comprenant un dispositif d'apport de puissance
FR3086342A1 (fr) * 2018-09-21 2020-03-27 Safran Aircraft Engines Turboreacteur a reducteur
EP3853466A1 (fr) * 2018-09-21 2021-07-28 Safran Aircraft Engines Turboréacteur comprenant un dispositif d'apport de puissance
US11421603B2 (en) 2018-09-21 2022-08-23 Safran Aircraft Engines Turbojet with step-down mechanism
US11891967B2 (en) 2018-09-21 2024-02-06 Safran Aircraft Engines Turbofan comprising a power supply device to drive the compressor

Also Published As

Publication number Publication date
JPS5331011A (en) 1978-03-23
DE2733986A1 (de) 1978-02-09

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Legal Events

Date Code Title Description
ST Notification of lapse