FR2973443B1 - Capot primaire poreux pour turboreacteur - Google Patents

Capot primaire poreux pour turboreacteur

Info

Publication number
FR2973443B1
FR2973443B1 FR1152634A FR1152634A FR2973443B1 FR 2973443 B1 FR2973443 B1 FR 2973443B1 FR 1152634 A FR1152634 A FR 1152634A FR 1152634 A FR1152634 A FR 1152634A FR 2973443 B1 FR2973443 B1 FR 2973443B1
Authority
FR
France
Prior art keywords
turboreactor
primary cover
porous primary
porous
cover
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
FR1152634A
Other languages
English (en)
Other versions
FR2973443A1 (fr
Inventor
Matthieu Leyko
Julien Szydlowski
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 FR1152634A priority Critical patent/FR2973443B1/fr
Priority to US13/434,163 priority patent/US20120247083A1/en
Publication of FR2973443A1 publication Critical patent/FR2973443A1/fr
Application granted granted Critical
Publication of FR2973443B1 publication Critical patent/FR2973443B1/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
    • 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
    • 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
    • F01D25/14—Casings modified therefor
    • 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
    • F02K3/06—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 with front fan
    • 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
    • F05D2260/202—Heat transfer, e.g. cooling by film cooling
    • 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)
FR1152634A 2011-03-30 2011-03-30 Capot primaire poreux pour turboreacteur Active FR2973443B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR1152634A FR2973443B1 (fr) 2011-03-30 2011-03-30 Capot primaire poreux pour turboreacteur
US13/434,163 US20120247083A1 (en) 2011-03-30 2012-03-29 Porous core cowling for a turbojet engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1152634A FR2973443B1 (fr) 2011-03-30 2011-03-30 Capot primaire poreux pour turboreacteur

Publications (2)

Publication Number Publication Date
FR2973443A1 FR2973443A1 (fr) 2012-10-05
FR2973443B1 true FR2973443B1 (fr) 2016-07-22

Family

ID=44548626

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1152634A Active FR2973443B1 (fr) 2011-03-30 2011-03-30 Capot primaire poreux pour turboreacteur

Country Status (2)

Country Link
US (1) US20120247083A1 (fr)
FR (1) FR2973443B1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3009339B1 (fr) * 2013-07-30 2018-01-26 Safran Aircraft Engines Turbomachine comprenant un dispositif de refroidissement du pylone
US11746726B2 (en) 2020-05-05 2023-09-05 Rohr, Inc. Aircraft propulsion system nozzle with internal flow passage
CN113606045B (zh) * 2021-07-15 2022-07-12 南京航空航天大学 一种大涵道比涡扇发动机核心舱通风结构及其通风方法

Family Cites Families (18)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2959917A (en) * 1959-04-06 1960-11-15 Boeing Co Sound suppressor for jet engines
US4773593A (en) * 1987-05-04 1988-09-27 United Technologies Corporation Coolable thin metal sheet
GB2244673B (en) * 1990-06-05 1993-09-01 Rolls Royce Plc A perforated sheet and a method of making the same
US5720434A (en) * 1991-11-05 1998-02-24 General Electric Company Cooling apparatus for aircraft gas turbine engine exhaust nozzles
US5307637A (en) * 1992-07-09 1994-05-03 General Electric Company Angled multi-hole film cooled single wall combustor dome plate
US5778676A (en) * 1996-01-02 1998-07-14 General Electric Company Dual fuel mixer for gas turbine combustor
US6227800B1 (en) * 1998-11-24 2001-05-08 General Electric Company Bay cooled turbine casing
US7328580B2 (en) * 2004-06-23 2008-02-12 General Electric Company Chevron film cooled wall
US7614235B2 (en) * 2005-03-01 2009-11-10 United Technologies Corporation Combustor cooling hole pattern
FR2892152B1 (fr) * 2005-10-19 2007-11-23 Airbus France Sas Turbomoteur a bruit de jet attenue
GB0607773D0 (en) * 2006-04-20 2006-05-31 Rolls Royce Plc A gas turbine engine
FR2904663B1 (fr) * 2006-08-01 2012-02-03 Snecma Turbomachine a double flux a variation artificielle de sa section de col
US7797945B2 (en) * 2006-09-06 2010-09-21 Honeywell International Inc. Bleed valve outlet flow deflector
WO2008045055A1 (fr) * 2006-10-12 2008-04-17 United Technologies Corporation Moteur à turboréacteur à structure interne fixée comprenant des passages carénés
EP2074323B1 (fr) * 2006-10-12 2012-11-21 United Technologies Corporation Turboréacteur à double flux présentant une surface de sortie de tuyère de dilution variable et procédé permettant de le faire fonctionner
FR2916808B1 (fr) * 2007-05-31 2013-02-22 Airbus France Turbomoteur a double flux a tuyere de flux chaud perfectionnee.
FR2921977B1 (fr) * 2007-10-08 2012-09-21 Airbus France Turbomoteur a double flux pour aeronef
US8141366B2 (en) * 2008-08-19 2012-03-27 United Technologies Corporation Gas turbine engine with variable area fan nozzle

Also Published As

Publication number Publication date
US20120247083A1 (en) 2012-10-04
FR2973443A1 (fr) 2012-10-05

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