FR3005693B1 - Turbomachine d'aeronef a double flux comprenant une virole inter-veine a maintien aval simplifie - Google Patents

Turbomachine d'aeronef a double flux comprenant une virole inter-veine a maintien aval simplifie

Info

Publication number
FR3005693B1
FR3005693B1 FR1354384A FR1354384A FR3005693B1 FR 3005693 B1 FR3005693 B1 FR 3005693B1 FR 1354384 A FR1354384 A FR 1354384A FR 1354384 A FR1354384 A FR 1354384A FR 3005693 B1 FR3005693 B1 FR 3005693B1
Authority
FR
France
Prior art keywords
violine
vein
inter
double
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
FR1354384A
Other languages
English (en)
Other versions
FR3005693A1 (fr
Inventor
Fabrice Cretin
Yvan Guezel
Francois Marie Paul Marlin
Thierry Georges Paul Papin
Alain Marc Lucien Bromann
Damien Lourit
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 FR1354384A priority Critical patent/FR3005693B1/fr
Priority to US14/272,911 priority patent/US9528441B2/en
Priority to GB1408390.1A priority patent/GB2517820B/en
Publication of FR3005693A1 publication Critical patent/FR3005693A1/fr
Application granted granted Critical
Publication of FR3005693B1 publication Critical patent/FR3005693B1/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
    • F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
    • 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
    • F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
    • F01D25/243—Flange connections; Bolting arrangements
    • 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
    • F02C7/20—Mounting or supporting of plant; Accommodating heat expansion or creep
    • 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
    • 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
    • F02K3/072—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 counter-rotating, e.g. fan 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
    • F05D2230/00—Manufacture
    • F05D2230/60—Assembly methods
    • 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
    • F05D2260/00—Function
    • F05D2260/30—Retaining components in desired mutual position
    • 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
    • F05D2260/30—Retaining components in desired mutual position
    • F05D2260/31—Retaining bolts or nuts
    • 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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0318—Processes
    • Y10T137/0402—Cleaning, repairing, or assembling
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T137/00—Fluid handling
    • Y10T137/0536—Highspeed fluid intake means [e.g., jet engine intake]

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)
FR1354384A 2013-05-16 2013-05-16 Turbomachine d'aeronef a double flux comprenant une virole inter-veine a maintien aval simplifie Active FR3005693B1 (fr)

Priority Applications (3)

Application Number Priority Date Filing Date Title
FR1354384A FR3005693B1 (fr) 2013-05-16 2013-05-16 Turbomachine d'aeronef a double flux comprenant une virole inter-veine a maintien aval simplifie
US14/272,911 US9528441B2 (en) 2013-05-16 2014-05-08 Aircraft turbofan comprising an intermediate ring with simplified downstream support
GB1408390.1A GB2517820B (en) 2013-05-16 2014-05-12 Aircraft turbofan comprising an intermediate ring with simplified downstream support

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1354384A FR3005693B1 (fr) 2013-05-16 2013-05-16 Turbomachine d'aeronef a double flux comprenant une virole inter-veine a maintien aval simplifie

Publications (2)

Publication Number Publication Date
FR3005693A1 FR3005693A1 (fr) 2014-11-21
FR3005693B1 true FR3005693B1 (fr) 2017-12-22

Family

ID=48795776

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1354384A Active FR3005693B1 (fr) 2013-05-16 2013-05-16 Turbomachine d'aeronef a double flux comprenant une virole inter-veine a maintien aval simplifie

Country Status (3)

Country Link
US (1) US9528441B2 (fr)
FR (1) FR3005693B1 (fr)
GB (1) GB2517820B (fr)

Families Citing this family (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE102014119673A1 (de) 2014-12-29 2016-06-30 Rolls-Royce Deutschland Ltd & Co Kg Gehäusevorrichtung für eine Verdichterstufe einer mehrstufig ausgeführten Verdichtervorrichtung und Verfahren zur Herstellung einer Gehäusevorrichtung
US10156243B2 (en) 2015-05-04 2018-12-18 Safran Aero Boosters Sa Composite splitter lip for axial turbomachine compressor
GB201517171D0 (en) * 2015-09-29 2015-11-11 Rolls Royce Plc A casing for a gas turbine engine and a method of manufacturing such a casing
FR3078100B1 (fr) 2018-02-16 2020-03-20 Safran Aircraft Engines Couronne aubagee pour stator de turbomachine dont les aubes sont reliees a la virole externe par appui conique et pion frangible

Family Cites Families (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6220012B1 (en) * 1999-05-10 2001-04-24 General Electric Company Booster recirculation passageway and methods for recirculating air
US6766639B2 (en) * 2002-09-30 2004-07-27 United Technologies Corporation Acoustic-structural LPC splitter
US6905303B2 (en) * 2003-06-30 2005-06-14 General Electric Company Methods and apparatus for assembling gas turbine engines
FR2889863B1 (fr) * 2005-08-22 2007-11-02 Snecma Compresseur comportant une pluralite de caissons reconstituant un volume annulaire de separation de flux dans une turbomachine.
EP1801389B1 (fr) * 2005-12-23 2008-08-20 Techspace aero Isolation acoustique d'un stator de compresseur basse pression
FR2902142B1 (fr) * 2006-06-09 2008-09-05 Snecma Sa Systeme de decharge d'un compresseur a basse pression de turbomachine
US7832193B2 (en) * 2006-10-27 2010-11-16 General Electric Company Gas turbine engine assembly and methods of assembling same
US8292574B2 (en) * 2006-11-30 2012-10-23 General Electric Company Advanced booster system
US7967571B2 (en) * 2006-11-30 2011-06-28 General Electric Company Advanced booster rotor blade
US7955046B2 (en) * 2007-09-25 2011-06-07 United Technologies Corporation Gas turbine engine front architecture modularity
FR2944839B1 (fr) 2009-04-22 2014-05-09 Snecma Carter intermediaire de turbomachine d'aeronef comprenant des bras structuraux de raccord a fonctions mecanique et aerodynamique dissociees
FR2956876B1 (fr) 2010-02-26 2012-10-19 Snecma Module structural et aerodynamique d'un carter de turbomachine et structure de carter comportant une pluralite d'un tel module
FR2977635B1 (fr) 2011-07-04 2017-03-24 Snecma Dispositif d'arbre d'entrainement d'une turbomachine
FR2978196B1 (fr) 2011-07-20 2016-12-09 Snecma Aubes de turbomachine comprenant une plaque rapportee sur une partie principale
US8402741B1 (en) * 2012-01-31 2013-03-26 United Technologies Corporation Gas turbine engine shaft bearing configuration
US9366185B2 (en) * 2012-09-28 2016-06-14 United Technologies Corporation Flexible connection between a wall and a case of a turbine engine

Also Published As

Publication number Publication date
GB201408390D0 (en) 2014-06-25
US20150159554A1 (en) 2015-06-11
US9528441B2 (en) 2016-12-27
FR3005693A1 (fr) 2014-11-21
GB2517820A (en) 2015-03-04
GB2517820B (en) 2019-12-11

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