FR2360758A1 - Gas turbine for aviation propulsion - has differential gear between turbine and compressor and blower drive shafts - Google Patents

Gas turbine for aviation propulsion - has differential gear between turbine and compressor and blower drive shafts

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Withdrawn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
French (fr)
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/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Withdrawn legal-status Critical Current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
    • 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

Abstract

The turbine has an inlet blower (15) the discharge of which goes partly through a bypass (22) and partly into a high pressure compressor (19). The discharge of the compressor goes to a combustion chamber (30) from which gases go through a turbine (32). The shaft (36) of the turbine drives a sun wheel in an annular differential gear mechanism (34). One output of the differential gear drives the shaft (38) of the blower (15) and the other output drives the shaft (40) of the compressor (19). The use of the differential enables the speeds of the blower and of the compressor to be adjusted according to the imposed load so that they can run at the most efficient speed over a range of operating conditions and duties.
FR7722512A 1976-08-02 1977-07-22 Gas turbine for aviation propulsion - has differential gear between turbine and compressor and blower drive shafts Withdrawn FR2360758A1 (en)

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 (en) 1978-03-03

Family

ID=24853961

Family Applications (1)

Application Number Title Priority Date Filing Date
FR7722512A Withdrawn FR2360758A1 (en) 1976-08-02 1977-07-22 Gas turbine for aviation propulsion - has differential gear between turbine and compressor and blower drive shafts

Country Status (3)

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

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2641332A1 (en) * 1989-01-03 1990-07-06 Gen Electric DOUBLE FLOW TURBOREACTOR COMPRISING A PARTIALLY ACCROPLEGRATED PARTIALLY ACCOUPLED BLOWER DRIVING TURBINE
WO2014023891A1 (en) * 2012-08-09 2014-02-13 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 (en) * 2018-09-21 2020-03-26 Safran Aircraft Engines Turbo-reactor comprising a power supply device
FR3086342A1 (en) * 2018-09-21 2020-03-27 Safran Aircraft Engines REDUCER TURBOREACTOR
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 (en) * 1964-07-20 1969-08-21 Rolls Royce Gas turbine jet engine with two counter-rotating shafts

Patent Citations (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE1301653B (en) * 1964-07-20 1969-08-21 Rolls Royce Gas turbine jet engine with two counter-rotating shafts

Non-Patent Citations (1)

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

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2641332A1 (en) * 1989-01-03 1990-07-06 Gen Electric DOUBLE FLOW TURBOREACTOR COMPRISING A PARTIALLY ACCROPLEGRATED PARTIALLY ACCOUPLED BLOWER DRIVING TURBINE
WO2014023891A1 (en) * 2012-08-09 2014-02-13 Snecma Turbomachine comprising a plurality of fixed radial blades mounted upstream of the fan
FR2994452A1 (en) * 2012-08-09 2014-02-14 Snecma TURBOMACHINE COMPRISING A PLURALITY OF FIXED RADIAL BLADES MOUNTED BEFORE THE BLOWER
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 (en) * 2018-09-21 2020-03-26 Safran Aircraft Engines Turbo-reactor comprising a power supply device
FR3086342A1 (en) * 2018-09-21 2020-03-27 Safran Aircraft Engines REDUCER TURBOREACTOR
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 (en) 1978-02-09

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Legal Events

Date Code Title Description
ST Notification of lapse