FR3108655B1 - Turbomachine à double flux comprenant un dispositif de régulation du débit de fluide de refroidissement - Google Patents

Turbomachine à double flux comprenant un dispositif de régulation du débit de fluide de refroidissement Download PDF

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Publication number
FR3108655B1
FR3108655B1 FR2002873A FR2002873A FR3108655B1 FR 3108655 B1 FR3108655 B1 FR 3108655B1 FR 2002873 A FR2002873 A FR 2002873A FR 2002873 A FR2002873 A FR 2002873A FR 3108655 B1 FR3108655 B1 FR 3108655B1
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France
Prior art keywords
flow
primary
compressor
stream
pressure
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Active
Application number
FR2002873A
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English (en)
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FR3108655A1 (fr
Inventor
Arnaud Nicolas Negri
Thaïs Savanah Liliane Marie Smeets
Didier Jean-Louis Yvon
Frédéric François Jean-Yves Patard
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Safran Aircraft Engines SAS
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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 FR2002873A priority Critical patent/FR3108655B1/fr
Priority to PCT/FR2021/050443 priority patent/WO2021191528A1/fr
Priority to US17/907,141 priority patent/US11873729B2/en
Priority to CN202180020016.7A priority patent/CN115244271A/zh
Priority to EP21718940.6A priority patent/EP4127406A1/fr
Publication of FR3108655A1 publication Critical patent/FR3108655A1/fr
Application granted granted Critical
Publication of FR3108655B1 publication Critical patent/FR3108655B1/fr
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Classifications

    • 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
    • F01D17/141—Final actuators arranged in stator parts varying effective cross-sectional area of nozzles or guide conduits by means of shiftable members or valves obturating part of the flow path
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • 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
    • 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
    • F01D25/08—Cooling; Heating; Heat-insulation
    • F01D25/12—Cooling
    • 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
    • F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
    • F01D5/02—Blade-carrying members, e.g. rotors
    • F01D5/08—Heating, heat-insulating or cooling means
    • F01D5/081—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades
    • F01D5/082—Cooling fluid being directed on the side of the rotor disc or at the roots of the blades on the side of the rotor disc
    • 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
    • F02C7/12—Cooling of plants
    • F02C7/16—Cooling of plants characterised by cooling medium
    • F02C7/18—Cooling of plants characterised by cooling medium the medium being gaseous, e.g. air
    • 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
    • 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
    • F05D2240/00—Components
    • F05D2240/10—Stators
    • F05D2240/12—Fluid guiding means, e.g. 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
    • F05D2240/00—Components
    • F05D2240/20—Rotors
    • 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
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/232—Heat transfer, e.g. cooling characterized by the cooling medium
    • 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
    • F05D2270/00—Control
    • F05D2270/30—Control parameters, e.g. input parameters
    • F05D2270/301—Pressure
    • F05D2270/3015—Pressure differential pressure
    • 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)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

Turbomachine (10) à double flux d’axe longitudinal (X-X’) comprenant une veine primaire (20) dans laquelle circule un flux primaire (F1) à une pression primaire (P3) et une veine secondaire (19) entourant radialement ladite veine primaire (20) et dans laquelle circule un flux secondaire (F2) à une pression secondaire (PS), ladite veine primaire (20) comportant au moins un compresseur (13) configuré pour comprimer le flux primaire (F1), une turbine (15) entraînant en rotation ledit compresseur (13) et une chambre de combustion (14) destinée à recevoir en entrée le flux d’air primaire comprimé par le compresseur (13), ladite turbomachine (10) comprenant en outre un circuit de refroidissement (23) s’étendant entre le compresseur (13) et la turbine (15). Le circuit de refroidissement (23) comprend un dispositif de régulation du débit d’air (30) disposé en amont de la turbine (15) et comprenant au moins une vanne (42) mobile entre une position ouverte et une position fermée en fonction de la différence de pression (ΔP) entre la pression (P3) située entre le compresseur (13) et la chambre de combustion (14) dans la veine primaire (20) et la pression (PS) dans la veine secondaire (19). Figure pour l’abrégé : Fig 2
FR2002873A 2020-03-24 2020-03-24 Turbomachine à double flux comprenant un dispositif de régulation du débit de fluide de refroidissement Active FR3108655B1 (fr)

Priority Applications (5)

Application Number Priority Date Filing Date Title
FR2002873A FR3108655B1 (fr) 2020-03-24 2020-03-24 Turbomachine à double flux comprenant un dispositif de régulation du débit de fluide de refroidissement
PCT/FR2021/050443 WO2021191528A1 (fr) 2020-03-24 2021-03-18 Turbomachine à double flux comprenant un dispositif de régulation du débit de fluide de refroidissement
US17/907,141 US11873729B2 (en) 2020-03-24 2021-03-18 Turbofan engine comprising a device for regulating the flow rate of cooling fluid
CN202180020016.7A CN115244271A (zh) 2020-03-24 2021-03-18 包括用于调节冷却流体的流速的设备的涡轮风扇发动机
EP21718940.6A EP4127406A1 (fr) 2020-03-24 2021-03-18 Turbomachine à double flux comprenant un dispositif de régulation du débit de fluide de refroidissement

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2002873A FR3108655B1 (fr) 2020-03-24 2020-03-24 Turbomachine à double flux comprenant un dispositif de régulation du débit de fluide de refroidissement
FR2002873 2020-03-24

Publications (2)

Publication Number Publication Date
FR3108655A1 FR3108655A1 (fr) 2021-10-01
FR3108655B1 true FR3108655B1 (fr) 2022-07-15

Family

ID=71662006

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2002873A Active FR3108655B1 (fr) 2020-03-24 2020-03-24 Turbomachine à double flux comprenant un dispositif de régulation du débit de fluide de refroidissement

Country Status (5)

Country Link
US (1) US11873729B2 (fr)
EP (1) EP4127406A1 (fr)
CN (1) CN115244271A (fr)
FR (1) FR3108655B1 (fr)
WO (1) WO2021191528A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3106624B1 (fr) * 2020-01-24 2022-02-18 Safran Aircraft Engines dispositif amélioré de détection d’anomalie de refroidissement pour turbomachine d’aéronef
FR3134842A1 (fr) 2022-04-21 2023-10-27 Safran Helicopter Engines Dispositif de refroidissement magnétothermique d’une turbomachine
CN115618652B (zh) 2022-11-28 2023-03-10 成都秦川物联网科技股份有限公司 智慧燃气压缩机运行优化方法、物联网系统、装置及介质

Family Cites Families (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3584458A (en) * 1969-11-25 1971-06-15 Gen Motors Corp Turbine cooling
US4296599A (en) * 1979-03-30 1981-10-27 General Electric Company Turbine cooling air modulation apparatus
GB2246836B (en) * 1981-05-07 1992-05-13 Rolls Royce Fluid flow valve
US4807433A (en) * 1983-05-05 1989-02-28 General Electric Company Turbine cooling air modulation
US6931859B2 (en) * 2003-12-17 2005-08-23 Honeywell International Inc. Variable turbine cooling flow system
US7926289B2 (en) * 2006-11-10 2011-04-19 General Electric Company Dual interstage cooled engine
US7665310B2 (en) * 2006-12-27 2010-02-23 General Electric Company Gas turbine engine having a cooling-air nacelle-cowl duct integral with a nacelle cowl
FR2943094B1 (fr) 2009-03-12 2014-04-11 Snecma Element de rotor avec un passage de fluide et un element d'obturation du passage, turbomachine comportant l'element de rotor.
US8549865B2 (en) * 2010-08-03 2013-10-08 General Electric Company Pressure-actuated plug
FR3062678B1 (fr) * 2017-02-07 2019-04-19 Safran Aircraft Engines Turboreacteur a double flux comprenant une veine intermediaire dediee a l'alimentation en air par des bras radiaux d'un carter d'echappement de ce turboreacteur

Also Published As

Publication number Publication date
US20230107761A1 (en) 2023-04-06
US11873729B2 (en) 2024-01-16
EP4127406A1 (fr) 2023-02-08
CN115244271A (zh) 2022-10-25
FR3108655A1 (fr) 2021-10-01
WO2021191528A1 (fr) 2021-09-30

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