FR3117151B1 - Ensemble de turbomachine - Google Patents

Ensemble de turbomachine Download PDF

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Publication number
FR3117151B1
FR3117151B1 FR2012917A FR2012917A FR3117151B1 FR 3117151 B1 FR3117151 B1 FR 3117151B1 FR 2012917 A FR2012917 A FR 2012917A FR 2012917 A FR2012917 A FR 2012917A FR 3117151 B1 FR3117151 B1 FR 3117151B1
Authority
FR
France
Prior art keywords
annular wall
outer annular
downstream
upstream
ejection
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
FR2012917A
Other languages
English (en)
Other versions
FR3117151A1 (fr
Inventor
Eric Conete
Benoit Carrere
Thomas Vandellos
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 FR2012917A priority Critical patent/FR3117151B1/fr
Priority to PCT/FR2021/052133 priority patent/WO2022123142A1/fr
Publication of FR3117151A1 publication Critical patent/FR3117151A1/fr
Application granted granted Critical
Publication of FR3117151B1 publication Critical patent/FR3117151B1/fr
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
    • 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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/40—Movement of components
    • F05D2250/41—Movement of components with one degree of freedom
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Exhaust Silencers (AREA)

Abstract

Ensemble de turbomachine d’axe longitudinal comprenant :- un carter d’échappement (30) de turbine,- un cône d’éjection (40) agencé en aval du carter d’échappement (30) et comprenant une partie amont (40a) et une partie aval (40b), la partie amont (40a) du cône d’éjection (40) comprenant une paroi annulaire externe (42) d’écoulement d’un flux d’air primaire, la paroi annulaire externe (42) étant reliée, à l’amont, au carter d’échappement (30) de la turbine et, à l’aval, à la partie aval (40b) du cône d’éjection (40), la partie amont (40a) du cône d’éjection (40) comprenant en outre un caisson acoustique (50) annulaire agencé radialement à l’intérieur de la paroi annulaire externe (42), le caisson acoustique comprenant une pluralité de caissons acoustiques élémentaires (60) distribués circonférentiellement autour de l’axe longitudinal, chaque caisson acoustique élémentaire (60) étant relié à la paroi annulaire externe (42) par au moins une liaison flexible. Figure de l’abrégé : Figure 3
FR2012917A 2020-12-09 2020-12-09 Ensemble de turbomachine Active FR3117151B1 (fr)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR2012917A FR3117151B1 (fr) 2020-12-09 2020-12-09 Ensemble de turbomachine
PCT/FR2021/052133 WO2022123142A1 (fr) 2020-12-09 2021-11-30 Ensemble de turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2012917 2020-12-09
FR2012917A FR3117151B1 (fr) 2020-12-09 2020-12-09 Ensemble de turbomachine

Publications (2)

Publication Number Publication Date
FR3117151A1 FR3117151A1 (fr) 2022-06-10
FR3117151B1 true FR3117151B1 (fr) 2023-01-13

Family

ID=75108453

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2012917A Active FR3117151B1 (fr) 2020-12-09 2020-12-09 Ensemble de turbomachine

Country Status (2)

Country Link
FR (1) FR3117151B1 (fr)
WO (1) WO2022123142A1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US12565866B2 (en) 2022-08-02 2026-03-03 General Electric Company Gas turbine engine with third stream
US12559249B2 (en) * 2023-01-03 2026-02-24 Rohr, Inc. Engine exhaust center body with acoustic attenuation
US20250207542A1 (en) * 2023-12-22 2025-06-26 Rohr, Inc. Acoustic engine exhaust center body with tapered inner skin

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8025122B2 (en) * 2008-11-06 2011-09-27 The Boeing Company Acoustically treated exhaust centerbody for jet engines and associated methods
DE102011008920A1 (de) * 2011-01-19 2012-07-19 Rolls-Royce Deutschland Ltd & Co Kg Schallabsorber, insbesondere für einen Gasturbinenabgaskonus und Verfahren zu dessen Herstellung
FR2987079B1 (fr) * 2012-02-17 2017-02-10 Snecma Propulsion Solide Cone d'echappement avec systeme d'attenuation acoustique
FR3061933B1 (fr) * 2017-01-18 2019-08-16 Airbus Operations Structure interne d'un conduit d'ejection primaire
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
WO2022123142A1 (fr) 2022-06-16
FR3117151A1 (fr) 2022-06-10

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