FR3092133B1 - Improved turbomachine comprising a thermal machine. - Google Patents

Improved turbomachine comprising a thermal machine. Download PDF

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Publication number
FR3092133B1
FR3092133B1 FR1900802A FR1900802A FR3092133B1 FR 3092133 B1 FR3092133 B1 FR 3092133B1 FR 1900802 A FR1900802 A FR 1900802A FR 1900802 A FR1900802 A FR 1900802A FR 3092133 B1 FR3092133 B1 FR 3092133B1
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FR
France
Prior art keywords
turbomachine
thermal machine
machine
improved turbomachine
improved
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.)
Active
Application number
FR1900802A
Other languages
French (fr)
Other versions
FR3092133A1 (en
Inventor
Clément Georges Henri Gorce
Emelian Charles François Vsevolod Evgueny Tichtchenko
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.)
Safran Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
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 Safran Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1900802A priority Critical patent/FR3092133B1/en
Publication of FR3092133A1 publication Critical patent/FR3092133A1/en
Application granted granted Critical
Publication of FR3092133B1 publication Critical patent/FR3092133B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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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
    • 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
    • F02C7/26—Starting; Ignition
    • F02C7/268—Starting drives for the rotor, acting directly on the rotor of the gas turbine to be started
    • F02C7/27—Fluid drives
    • 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
    • F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
    • F01D15/08—Adaptations for driving, or combinations with, pumps
    • 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
    • F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
    • F01D25/34—Turning or inching gear
    • 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
    • F02C7/32—Arrangement, mounting, or driving, of auxiliaries
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • 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
    • F05D2260/00—Function
    • F05D2260/85—Starting
    • 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)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Turbomachine améliorée comprenant une machine thermique . Turbomachine (1) comprenant un carter fixe, une chambre de combustion (4) fixe et un arbre haute pression (20) mobile en rotation par rapport au carter, la turbomachine (1) étant caractérisée en ce qu’elle comprend une machine thermique (8) comprenant un réservoir de fluide (81), un actionneur (82), un échangeur thermique (83) et un compresseur (84), ladite machine thermique (8) étant adaptée pour entrainer l’arbre haute pression (20) en rotation lorsque la turbomachine (1) n’est pas en fonctionnement. Figure pour l’abrégé : Fig. 1.Improved turbomachine comprising a thermal machine. Turbomachine (1) comprising a fixed casing, a fixed combustion chamber (4) and a high pressure shaft (20) movable in rotation with respect to the casing, the turbomachine (1) being characterized in that it comprises a thermal machine ( 8) comprising a fluid reservoir (81), an actuator (82), a heat exchanger (83) and a compressor (84), said heat machine (8) being adapted to drive the high pressure shaft (20) in rotation when the turbomachine (1) is not in operation. Figure for the abstract: Fig. 1.

FR1900802A 2019-01-29 2019-01-29 Improved turbomachine comprising a thermal machine. Active FR3092133B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1900802A FR3092133B1 (en) 2019-01-29 2019-01-29 Improved turbomachine comprising a thermal machine.

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1900802A FR3092133B1 (en) 2019-01-29 2019-01-29 Improved turbomachine comprising a thermal machine.
FR1900802 2019-01-29

Publications (2)

Publication Number Publication Date
FR3092133A1 FR3092133A1 (en) 2020-07-31
FR3092133B1 true FR3092133B1 (en) 2021-07-16

Family

ID=67875501

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1900802A Active FR3092133B1 (en) 2019-01-29 2019-01-29 Improved turbomachine comprising a thermal machine.

Country Status (1)

Country Link
FR (1) FR3092133B1 (en)

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2903451B1 (en) * 2006-07-07 2008-09-12 Snecma Sa TURBOMOTEUR WITH ALTERNATOR AND METHOD OF TRANSMITTING MOTION TO ALTERNATOR
FR2920482B1 (en) * 2007-08-30 2009-10-30 Snecma Sa VENTILATION AND PRESSURIZATION OF COMPONENTS IN A TURBOMACHINE
FR2921423B1 (en) * 2007-09-25 2014-04-25 Snecma DUAL BODY TURBOMACHINE WITH DOUBLE POWER CAPACITY
JP2015028333A (en) * 2013-07-30 2015-02-12 畑中　武史 Net zero energy propulsion method for aircraft and net zero energy aircraft
US10273883B2 (en) * 2016-02-26 2019-04-30 The Boeing Company Engine accessory drives systems and methods

Also Published As

Publication number Publication date
FR3092133A1 (en) 2020-07-31

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