FR3109408B1 - PNEUMATICALLY ADJUSTABLE DILUTION RATE TURBOMACHINE - Google Patents

PNEUMATICALLY ADJUSTABLE DILUTION RATE TURBOMACHINE Download PDF

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Publication number
FR3109408B1
FR3109408B1 FR2003969A FR2003969A FR3109408B1 FR 3109408 B1 FR3109408 B1 FR 3109408B1 FR 2003969 A FR2003969 A FR 2003969A FR 2003969 A FR2003969 A FR 2003969A FR 3109408 B1 FR3109408 B1 FR 3109408B1
Authority
FR
France
Prior art keywords
turbomachine
stream
dilution rate
inflatable chamber
pneumatically adjustable
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
FR2003969A
Other languages
French (fr)
Other versions
FR3109408A1 (en
Inventor
Pierrot Guillou
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 FR2003969A priority Critical patent/FR3109408B1/en
Priority to PCT/FR2021/050660 priority patent/WO2021214402A1/en
Publication of FR3109408A1 publication Critical patent/FR3109408A1/en
Application granted granted Critical
Publication of FR3109408B1 publication Critical patent/FR3109408B1/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
    • 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
    • F02K3/075—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 controlling flow ratio between flows
    • 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
    • F01D17/00—Regulating or controlling by varying flow
    • F01D17/10—Final actuators
    • F01D17/12—Final actuators arranged in stator parts
    • F01D17/14—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits
    • 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
    • F02C9/00—Controlling gas-turbine plants; Controlling fuel supply in air- breathing jet-propulsion plants
    • F02C9/16—Control of working fluid flow
    • F02C9/20—Control of working fluid flow by throttling; by adjusting vanes
    • 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
    • F05D2220/80—Application in supersonic vehicles excluding hypersonic vehicles or ram, scram or rocket propulsion
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

L'invention concerne une turbomachine (1), dans laquelle un flux d’entrée (F) est séparé en un premier flux (Fp) circulant au travers d’une première veine (16) et un second flux (Fs) circulant au travers d’une seconde veine (17), et comprenant un générateur de gaz (2) alimenté par le premier flux et entraînant un compresseur (4). La turbomachine (1) comporte un dispositif pneumatique (19) comprenant une chambre gonflable délimitée par une enveloppe élastiquement déformable, et des moyens de gonflage (31, 32) configurés pour ajuster une pression interne au sein de la chambre gonflable. La chambre gonflable est configurée de sorte qu’un accroissement de la pression interne conduit le dispositif pneumatique (19) à restreindre une section de passage (X) du second flux dans la seconde veine (17). Figure pour l’abrégé : Fig.1The invention relates to a turbomachine (1), in which an inlet stream (F) is separated into a first stream (Fp) circulating through a first vein (16) and a second stream (Fs) circulating through a second stream (17), and comprising a gas generator (2) powered by the first flow and driving a compressor (4). The turbomachine (1) comprises a pneumatic device (19) comprising an inflatable chamber delimited by an elastically deformable envelope, and inflation means (31, 32) configured to adjust an internal pressure within the inflatable chamber. The inflatable chamber is configured such that an increase in the internal pressure causes the pneumatic device (19) to restrict a passage section (X) of the second flow in the second vein (17). Figure for abstract: Fig.1

FR2003969A 2020-04-21 2020-04-21 PNEUMATICALLY ADJUSTABLE DILUTION RATE TURBOMACHINE Active FR3109408B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR2003969A FR3109408B1 (en) 2020-04-21 2020-04-21 PNEUMATICALLY ADJUSTABLE DILUTION RATE TURBOMACHINE
PCT/FR2021/050660 WO2021214402A1 (en) 2020-04-21 2021-04-15 Turbine engine having a pneumatically modulated bypass ratio

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2003969 2020-04-21
FR2003969A FR3109408B1 (en) 2020-04-21 2020-04-21 PNEUMATICALLY ADJUSTABLE DILUTION RATE TURBOMACHINE

Publications (2)

Publication Number Publication Date
FR3109408A1 FR3109408A1 (en) 2021-10-22
FR3109408B1 true FR3109408B1 (en) 2022-10-28

Family

ID=71784210

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2003969A Active FR3109408B1 (en) 2020-04-21 2020-04-21 PNEUMATICALLY ADJUSTABLE DILUTION RATE TURBOMACHINE

Country Status (2)

Country Link
FR (1) FR3109408B1 (en)
WO (1) WO2021214402A1 (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR1552119A (en) * 1967-11-17 1969-01-03
FR2685385B1 (en) * 1991-12-24 1995-03-31 Snecma VARIABLE CYCLE PROPULSION ENGINE FOR SUPERSONIC AIRCRAFT.
EP2064433B1 (en) * 2006-10-12 2013-11-20 United Technologies Corporation Gas turbine engine system and corresponding method for controlling a bypass airflow
US9010126B2 (en) * 2008-02-20 2015-04-21 United Technologies Corporation Gas turbine engine with variable area fan nozzle bladder system
US10260427B2 (en) * 2013-03-15 2019-04-16 United Technologies Corporation Variable area bypass nozzle
FR3077847B1 (en) * 2018-02-09 2020-02-14 Safran Nacelles SHUTTER INVERTER FOR PROPULSIVE AIRCRAFT ASSEMBLY

Also Published As

Publication number Publication date
FR3109408A1 (en) 2021-10-22
WO2021214402A1 (en) 2021-10-28

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