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FR2980531B1 - Capot primaire de turboreacteur double flux comportant une couronne tournante a micro-jets - Google Patents

Capot primaire de turboreacteur double flux comportant une couronne tournante a micro-jets

Info

Publication number
FR2980531B1
FR2980531B1 FR1158477A FR1158477A FR2980531B1 FR 2980531 B1 FR2980531 B1 FR 2980531B1 FR 1158477 A FR1158477 A FR 1158477A FR 1158477 A FR1158477 A FR 1158477A FR 2980531 B1 FR2980531 B1 FR 2980531B1
Authority
FR
France
Prior art keywords
micro
double flow
primary cover
rotating crown
jets
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
FR1158477A
Other languages
English (en)
Other versions
FR2980531A1 (fr
Inventor
Alexandre Alfred Gaston Vuillemin
Sebastien Jean-Paul Aeberli
Guillaume Bodard
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
SNECMA 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 SNECMA SAS filed Critical SNECMA SAS
Priority to FR1158477A priority Critical patent/FR2980531B1/fr
Priority to US14/346,602 priority patent/US9617954B2/en
Priority to PCT/FR2012/052123 priority patent/WO2013041818A1/fr
Priority to GB1406230.1A priority patent/GB2509442B/en
Publication of FR2980531A1 publication Critical patent/FR2980531A1/fr
Application granted granted Critical
Publication of FR2980531B1 publication Critical patent/FR2980531B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F02K1/34—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for attenuating noise
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/28—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow
    • F02K1/30—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto using fluid jets to influence the jet flow for varying effective area of jet pipe or nozzle
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/38—Introducing air inside the jet
    • 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
    • F02K3/025—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 by-pass flow being at least partly used to create an independent thrust component
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/38—Introducing air inside the jet
    • F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/46—Nozzles having means for adding air to the jet or for augmenting the mixing region between the jet and the ambient air, e.g. for silencing
    • 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
    • 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)
FR1158477A 2011-09-23 2011-09-23 Capot primaire de turboreacteur double flux comportant une couronne tournante a micro-jets Active FR2980531B1 (fr)

Priority Applications (4)

Application Number Priority Date Filing Date Title
FR1158477A FR2980531B1 (fr) 2011-09-23 2011-09-23 Capot primaire de turboreacteur double flux comportant une couronne tournante a micro-jets
US14/346,602 US9617954B2 (en) 2011-09-23 2012-09-24 Primary cowl of a turbofan comprising a rotating ring having micro-jets
PCT/FR2012/052123 WO2013041818A1 (fr) 2011-09-23 2012-09-24 Capot primaire de turboréacteur double flux comportant une couronne tournante a micro-jets
GB1406230.1A GB2509442B (en) 2011-09-23 2012-09-24 Primary cowl of a turbofan comprising a rotating ring having micro-jets

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1158477A FR2980531B1 (fr) 2011-09-23 2011-09-23 Capot primaire de turboreacteur double flux comportant une couronne tournante a micro-jets

Publications (2)

Publication Number Publication Date
FR2980531A1 FR2980531A1 (fr) 2013-03-29
FR2980531B1 true FR2980531B1 (fr) 2016-06-03

Family

ID=47071346

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1158477A Active FR2980531B1 (fr) 2011-09-23 2011-09-23 Capot primaire de turboreacteur double flux comportant une couronne tournante a micro-jets

Country Status (4)

Country Link
US (1) US9617954B2 (fr)
FR (1) FR2980531B1 (fr)
GB (1) GB2509442B (fr)
WO (1) WO2013041818A1 (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2975135B1 (fr) * 2011-05-12 2016-07-22 Snecma Cone arriere de turboreacteur tournant a micro-jets
GB201412189D0 (en) * 2014-07-09 2014-08-20 Rolls Royce Plc A nozzle arrangement for a gas turbine engine
RU2728577C2 (ru) * 2018-10-03 2020-07-31 Акционерное общество "Объединенная двигателестроительная корпорация" (АО "ОДК") Турбореактивный двухконтурный двигатель с раздельным истечением потоков из сопел
US12258923B2 (en) 2023-03-13 2025-03-25 General Electric Company Cowl assembly for a propulsor

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7065957B2 (en) * 2000-05-05 2006-06-27 The Boeing Company Segmented mixing device for jet engines and aircraft
AU2002211367A1 (en) 2000-10-02 2002-04-15 Rohr, Inc. Apparatus, method and system for gas turbine engine noise reduction
US7055329B2 (en) * 2003-03-31 2006-06-06 General Electric Company Method and apparatus for noise attenuation for gas turbine engines using at least one synthetic jet actuator for injecting air
US7377108B2 (en) * 2004-04-09 2008-05-27 The Boeing Company Apparatus and method for reduction jet noise from single jets
FR2904663B1 (fr) * 2006-08-01 2012-02-03 Snecma Turbomachine a double flux a variation artificielle de sa section de col
US7681399B2 (en) * 2006-11-14 2010-03-23 General Electric Company Turbofan engine cowl assembly and method of operating the same

Also Published As

Publication number Publication date
GB2509442B (en) 2017-08-16
GB2509442A (en) 2014-07-02
FR2980531A1 (fr) 2013-03-29
WO2013041818A1 (fr) 2013-03-28
GB201406230D0 (en) 2014-05-21
US9617954B2 (en) 2017-04-11
US20140245715A1 (en) 2014-09-04

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Owner name: SAFRAN AIRCRAFT ENGINES, FR

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