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FR3115568B1 - Ensemble de turbine de turbomachine - Google Patents

Ensemble de turbine de turbomachine Download PDF

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Publication number
FR3115568B1
FR3115568B1 FR2011002A FR2011002A FR3115568B1 FR 3115568 B1 FR3115568 B1 FR 3115568B1 FR 2011002 A FR2011002 A FR 2011002A FR 2011002 A FR2011002 A FR 2011002A FR 3115568 B1 FR3115568 B1 FR 3115568B1
Authority
FR
France
Prior art keywords
exhaust
annular wall
connecting member
cone
turbine assembly
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
FR2011002A
Other languages
English (en)
Other versions
FR3115568A1 (fr
Inventor
Eric Conete
Benoit Carrere
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 Ceramics SA
Original Assignee
Safran Ceramics SA
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 Safran Ceramics SA filed Critical Safran Ceramics SA
Priority to FR2011002A priority Critical patent/FR3115568B1/fr
Publication of FR3115568A1 publication Critical patent/FR3115568A1/fr
Application granted granted Critical
Publication of FR3115568B1 publication Critical patent/FR3115568B1/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
    • F02K1/04—Mounting of an exhaust cone in the jet pipe
    • 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
    • F02K1/78—Other construction of jet pipes
    • F02K1/80—Couplings or connections
    • 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
    • F02K1/78—Other construction of jet pipes
    • F02K1/80—Couplings or connections
    • F02K1/805—Sealing devices therefor, e.g. for movable parts of jet pipes or nozzle flaps
    • 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
    • F05D2230/64—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins
    • F05D2230/642—Assembly methods using positioning or alignment devices for aligning or centring, e.g. pins using maintaining alignment while permitting differential dilatation
    • 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
    • F05D2260/94—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF]
    • F05D2260/941—Functionality given by mechanical stress related aspects such as low cycle fatigue [LCF] of high cycle fatigue [HCF] particularly aimed at mechanical or thermal stress reduction
    • 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
    • F05D2260/96—Preventing, counteracting or reducing vibration or noise
    • 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
    • F05D2300/00—Materials; Properties thereof
    • F05D2300/60—Properties or characteristics given to material by treatment or manufacturing
    • F05D2300/603—Composites; e.g. fibre-reinforced
    • F05D2300/6033—Ceramic matrix composites [CMC]

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Gasket Seals (AREA)

Abstract

Ensemble de turbine de turbomachine d’axe longitudinal comprenant un carter d’échappement (30), un cône d’éjection (40) agencé en aval du carter d’échappement (30), le cône d’éjection (30) comprenant une paroi annulaire externe (42) d’écoulement d’un flux d’air primaire et un caisson acoustique (44) agencé radialement à l’intérieur de ladite paroi annulaire externe (42), le caisson acoustique (44) comprenant au moins une paroi annulaire radialement interne (46), un organe de liaison (50) intercalé longitudinalement entre le carter d’échappement (30) et la paroi annulaire interne (46) du cône d’éjection (40), l’organe de liaison (50) étant fixé au carter d’échappement (30) et à la paroi annulaire interne (46), dans lequel un joint d’étanchéité (80) annulaire est porté par l’organe de liaison (50), la paroi annulaire externe (42) étant en appui radial, au niveau d’une extrémité amont, sur le joint d’étanchéité (80). Figure de l’abrégé : Figure 3
FR2011002A 2020-10-27 2020-10-27 Ensemble de turbine de turbomachine Active FR3115568B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2011002A FR3115568B1 (fr) 2020-10-27 2020-10-27 Ensemble de turbine de turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2011002 2020-10-27
FR2011002A FR3115568B1 (fr) 2020-10-27 2020-10-27 Ensemble de turbine de turbomachine

Publications (2)

Publication Number Publication Date
FR3115568A1 FR3115568A1 (fr) 2022-04-29
FR3115568B1 true FR3115568B1 (fr) 2023-06-30

Family

ID=73793501

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2011002A Active FR3115568B1 (fr) 2020-10-27 2020-10-27 Ensemble de turbine de turbomachine

Country Status (1)

Country Link
FR (1) FR3115568B1 (fr)

Family Cites Families (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2949820B1 (fr) * 2009-09-04 2011-10-14 Aircelle Sa Ensemble structurant pour une tuyere d'ejection.
US9732701B2 (en) * 2014-05-12 2017-08-15 Rohr, Inc. Center body attachment system
FR3084917B1 (fr) * 2018-08-09 2021-04-16 Safran Ceram Ensemble pour une tuyere d'ejection de turbomachine

Also Published As

Publication number Publication date
FR3115568A1 (fr) 2022-04-29

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