FR3117548B1 - DEVICE FOR DRIVING A MAIN AIR FLOW FOR AN AIRCRAFT TURBOMACHINE - Google Patents

DEVICE FOR DRIVING A MAIN AIR FLOW FOR AN AIRCRAFT TURBOMACHINE Download PDF

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Publication number
FR3117548B1
FR3117548B1 FR2013168A FR2013168A FR3117548B1 FR 3117548 B1 FR3117548 B1 FR 3117548B1 FR 2013168 A FR2013168 A FR 2013168A FR 2013168 A FR2013168 A FR 2013168A FR 3117548 B1 FR3117548 B1 FR 3117548B1
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FR
France
Prior art keywords
air flow
pipe
main air
driving
aircraft turbomachine
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
FR2013168A
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French (fr)
Other versions
FR3117548A1 (en
Inventor
Thomas Alexandre Guerin
Mathieu Pierre Cladiere
Jacques Demolis
Nicolas Christophe Perra
Frédéric Ripolles
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 Helicopter Engines SAS
Original Assignee
Safran Helicopter 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.)
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Publication date
Application filed by Safran Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to FR2013168A priority Critical patent/FR3117548B1/en
Publication of FR3117548A1 publication Critical patent/FR3117548A1/en
Application granted granted Critical
Publication of FR3117548B1 publication Critical patent/FR3117548B1/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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • F02C7/05—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles
    • F02C7/052—Air intakes for gas-turbine plants or jet-propulsion plants having provisions for obviating the penetration of damaging objects or particles with dust-separation devices
    • 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
    • F05D2260/60—Fluid transfer
    • F05D2260/601—Fluid transfer using an ejector or a jet pump

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Jet Pumps And Other Pumps (AREA)

Abstract

Dispositif (110) d’entraînement d’un flux d’air principal (F1) pour une turbomachine (22) d’aéronef, ce dispositif comportant : - une première conduite (112) d’écoulement d’un flux d’air principal (F1), - une pluralité d’éjecteurs (114) d’un flux d’air secondaire (F2) situés à l’intérieur de la première conduite (112) et configurés pour éjecter un flux d’air secondaire (F2) et forcer l’écoulement du flux d’air principal (F1) dans cette première conduite (112), et - une seconde conduite (116) d’échappement située en sortie des éjecteurs (114) et raccordée à la première conduite (112), caractérisé en ce que ladite seconde conduite (116) comprend : - un embout tubulaire (116a) raccordé à la première conduite (112), et - un corps central (116b) situé à l’intérieur de l’embout (116a) et relié à cet embout par des bras de liaison (116c). Figure pour l'abrégé : Figure 5Device (110) for driving a main air flow (F1) for an aircraft turbomachine (22), this device comprising: - a first pipe (112) for flowing a main air flow (F1), - a plurality of ejectors (114) of a secondary air flow (F2) located inside the first pipe (112) and configured to eject a secondary air flow (F2) and force the flow of the main air flow (F1) in this first pipe (112), and - a second exhaust pipe (116) located at the outlet of the ejectors (114) and connected to the first pipe (112), characterized in that said second pipe (116) comprises: - a tubular endpiece (116a) connected to the first pipe (112), and - a central body (116b) located inside the endpiece (116a) and connected to this end piece by connecting arms (116c). Figure for abstract: Figure 5

FR2013168A 2020-12-14 2020-12-14 DEVICE FOR DRIVING A MAIN AIR FLOW FOR AN AIRCRAFT TURBOMACHINE Active FR3117548B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2013168A FR3117548B1 (en) 2020-12-14 2020-12-14 DEVICE FOR DRIVING A MAIN AIR FLOW FOR AN AIRCRAFT TURBOMACHINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2013168A FR3117548B1 (en) 2020-12-14 2020-12-14 DEVICE FOR DRIVING A MAIN AIR FLOW FOR AN AIRCRAFT TURBOMACHINE
FR2013168 2020-12-14

Publications (2)

Publication Number Publication Date
FR3117548A1 FR3117548A1 (en) 2022-06-17
FR3117548B1 true FR3117548B1 (en) 2023-09-08

Family

ID=74347410

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2013168A Active FR3117548B1 (en) 2020-12-14 2020-12-14 DEVICE FOR DRIVING A MAIN AIR FLOW FOR AN AIRCRAFT TURBOMACHINE

Country Status (1)

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FR (1) FR3117548B1 (en)

Family Cites Families (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4928480A (en) * 1988-03-04 1990-05-29 General Electric Company Separator having multiple particle extraction passageways
US6139423A (en) * 1999-05-14 2000-10-31 Sikorsky Aircraft Corporation Noise reducing bleed air heat ejection device for a heating system
DE102006017004B3 (en) * 2006-04-11 2007-10-25 Airbus Deutschland Gmbh Device for mixing fresh air and heating air and use thereof in a ventilation system of an aircraft
US9790856B2 (en) 2012-10-19 2017-10-17 Snecma Jet pump for depressurizing lubrication chambers of a turbomachine, having independent double injectors
FR3011583B1 (en) 2013-10-03 2018-01-12 Safran Aircraft Engines JET TRUMP FOR DEPRESSURIZING LUBRICATING ENCLOSURES OF A COAXIAL INDEPENDENT INJECTOR TURBOMACHINE
FR3022588B1 (en) 2014-06-24 2016-06-24 Snecma COOLING DEVICE FOR A TURBOMACHINE
FR3087239B1 (en) 2018-10-10 2023-03-31 Safran Electrical & Power SYSTEM AND METHOD FOR COOLING THE BRAKES OF AN AIRCRAFT LANDING GEAR

Also Published As

Publication number Publication date
FR3117548A1 (en) 2022-06-17

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