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FR3028289B1 - Turbomachine d'aeronef comprenant un boitier d'admission d'air a profil aerodynamique variable - Google Patents

Turbomachine d'aeronef comprenant un boitier d'admission d'air a profil aerodynamique variable Download PDF

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Publication number
FR3028289B1
FR3028289B1 FR1460717A FR1460717A FR3028289B1 FR 3028289 B1 FR3028289 B1 FR 3028289B1 FR 1460717 A FR1460717 A FR 1460717A FR 1460717 A FR1460717 A FR 1460717A FR 3028289 B1 FR3028289 B1 FR 3028289B1
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France
Prior art keywords
wall
opening
air
box
downstream
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Active
Application number
FR1460717A
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English (en)
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FR3028289A1 (fr
Inventor
Stephane Warnet
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.)
Airbus Operations SAS
Original Assignee
Airbus Operations SAS
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Publication date
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Priority to FR1460717A priority Critical patent/FR3028289B1/fr
Priority to US14/928,302 priority patent/US10001062B2/en
Publication of FR3028289A1 publication Critical patent/FR3028289A1/fr
Application granted granted Critical
Publication of FR3028289B1 publication Critical patent/FR3028289B1/fr
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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
    • F02C7/12—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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • 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
    • 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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
    • 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
    • F02C7/14—Cooling of plants of fluids in the plant, e.g. lubricant or fuel
    • 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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/02—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes
    • B64D2033/0266—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants
    • B64D2033/0286—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of combustion air intakes specially adapted for particular type of power plants for turbofan engines
    • 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
    • F05D2260/221—Improvement of heat transfer
    • 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)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Geometry (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

L'invention concerne une turbomachine d'aéronef comprenant un conduit de soufflante (30) comprenant une paroi, un écoulement d'air transitant, en utilisation, via le conduit de soufflante ; un passage d'air (120) arrangée dans la paroi et comprenant une ouverture d'entrée d'air au niveau de la paroi, le passage d'air étant conçu pour recevoir une partie de l'écoulement de l'air du conduit de soufflante (30) au travers de ladite ouverture ; la turbomachine comprenant un boitier d'admission d'air (300) agencé au-dessus de l'ouverture d'entrée d'air et fixé à la paroi, ledit boitier étant arrangé pour intercepter une partie de l'écoulement de l'air dans le conduit de soufflante (30), ledit boitier comprenant successivement, dans le sens (F) d'écoulement de l'air, une paroi amont puis une paroi aval, le boitier comprenant en outre une ouverture amont (301) et une ouverture aval (302) arrangées respectivement sur la paroi amont et la paroi aval, l'intérieur du boitier étant en communication fluidique avec l'ouverture d'entrée d'air, le boitier (300) comprenant en outre un moyen d'obturation mobile entre : • une position dite ouverte, dans laquelle le moyen d'obturation ferme complètement l'ouverture aval et libère complètement l'ouverture d'entrée d'air; et • une position dite fermée, dans laquelle le moyen d'obturation libère complètement l'ouverture aval et ferme complètement l'ouverture d'entrée d'air. Le boitier a ainsi un profil aérodynamique variable et adapté en fonction des besoins en air d'un système utilisateur afin de ne pas impacter inutilement les performances aérodynamiques de la turbomachine.
FR1460717A 2014-11-06 2014-11-06 Turbomachine d'aeronef comprenant un boitier d'admission d'air a profil aerodynamique variable Active FR3028289B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1460717A FR3028289B1 (fr) 2014-11-06 2014-11-06 Turbomachine d'aeronef comprenant un boitier d'admission d'air a profil aerodynamique variable
US14/928,302 US10001062B2 (en) 2014-11-06 2015-10-30 Aircraft turbine engine comprising an air intake housing with a variable aerodynamic profile

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1460717 2014-11-06
FR1460717A FR3028289B1 (fr) 2014-11-06 2014-11-06 Turbomachine d'aeronef comprenant un boitier d'admission d'air a profil aerodynamique variable

Publications (2)

Publication Number Publication Date
FR3028289A1 FR3028289A1 (fr) 2016-05-13
FR3028289B1 true FR3028289B1 (fr) 2019-12-27

Family

ID=52627320

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1460717A Active FR3028289B1 (fr) 2014-11-06 2014-11-06 Turbomachine d'aeronef comprenant un boitier d'admission d'air a profil aerodynamique variable

Country Status (2)

Country Link
US (1) US10001062B2 (fr)
FR (1) FR3028289B1 (fr)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11066992B2 (en) 2018-05-03 2021-07-20 Airbus Operations Sas Aircraft propulsion assembly comprising a cold bleed air intake device with variable aerodynamic profile

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US10040560B2 (en) * 2015-09-30 2018-08-07 The Boeing Company Trailing edge core compartment vent for an aircraft engine
US10189572B2 (en) * 2016-05-02 2019-01-29 The Boeing Company Systems and methods for preventing ice formation on portions of an aircraft
GB201705802D0 (en) * 2017-04-11 2017-05-24 Rolls Royce Plc Inlet duct
GB201902795D0 (en) * 2019-03-01 2019-04-17 Rolls Royce Plc Geared gas turbine engine
GB2599688B (en) * 2020-10-09 2023-08-16 Rolls Royce Plc An improved turbofan gas turbine engine
FR3117149B1 (fr) * 2020-12-03 2022-10-21 Safran Aircraft Engines Ecope pour une turbomachine d’aeronef

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4250703A (en) * 1979-03-15 1981-02-17 Avco Corporation Swinging door particle separator and deicing system
US4418879A (en) * 1980-12-29 1983-12-06 The Boeing Company Scoop and inlet for auxiliary power units and method
US4782658A (en) * 1987-05-07 1988-11-08 Rolls-Royce Plc Deicing of a geared gas turbine engine
GB2308866B (en) * 1996-01-04 1999-09-08 Rolls Royce Plc Ducted fan gas turbine engine with secondary duct
US7014144B2 (en) * 2003-07-22 2006-03-21 Honeywell International, Inc. Dual action inlet door and method for use thereof
DE102009011635A1 (de) * 2009-03-04 2010-09-09 Rolls-Royce Deutschland Ltd & Co Kg Luftleitelement eines Laufspalteinstellungssystems einer Fluggasturbine
DE102011011879A1 (de) * 2011-02-21 2012-08-23 Airbus Operations Gmbh Kühllufteinlass, Triebwerkzapfluftsystem und Verfahren zum Betreiben eines Kühllufteinlasses

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11066992B2 (en) 2018-05-03 2021-07-20 Airbus Operations Sas Aircraft propulsion assembly comprising a cold bleed air intake device with variable aerodynamic profile

Also Published As

Publication number Publication date
FR3028289A1 (fr) 2016-05-13
US20160131038A1 (en) 2016-05-12
US10001062B2 (en) 2018-06-19

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