FR3117151B1 - TURBOMACHINE SET - Google Patents

TURBOMACHINE SET 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
French (fr)
Other versions
FR3117151A1 (en
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/en
Priority to PCT/FR2021/052133 priority patent/WO2022123142A1/en
Publication of FR3117151A1 publication Critical patent/FR3117151A1/en
Application granted granted Critical
Publication of FR3117151B1 publication Critical patent/FR3117151B1/en
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 3A longitudinal axis turbomachine assembly comprising:- a turbine exhaust casing (30),- an exhaust cone (40) arranged downstream of the exhaust casing (30) and comprising an upstream part (40a) and a downstream part (40b), the upstream part (40a) of the ejection cone (40) comprising an outer annular wall (42) for the flow of a flow of primary air, the outer annular wall (42) being connected , upstream, to the exhaust casing (30) of the turbine and, downstream, to the downstream part (40b) of the ejection cone (40), the upstream part (40a) of the ejection (40) further comprising an annular acoustic box (50) arranged radially inside the outer annular wall (42), the acoustic box comprising a plurality of elementary acoustic boxes (60) distributed circumferentially around the longitudinal axis , each elementary acoustic box (60) being connected to the outer annular wall (42) by at least one flexible connection. Abstract Figure: Figure 3

FR2012917A 2020-12-09 2020-12-09 TURBOMACHINE SET Active FR3117151B1 (en)

Priority Applications (2)

Application Number Priority Date Filing Date Title
FR2012917A FR3117151B1 (en) 2020-12-09 2020-12-09 TURBOMACHINE SET
PCT/FR2021/052133 WO2022123142A1 (en) 2020-12-09 2021-11-30 Turbomachine assembly

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2012917A FR3117151B1 (en) 2020-12-09 2020-12-09 TURBOMACHINE SET
FR2012917 2020-12-09

Publications (2)

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

Family

ID=75108453

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2012917A Active FR3117151B1 (en) 2020-12-09 2020-12-09 TURBOMACHINE SET

Country Status (2)

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

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 (en) * 2011-01-19 2012-07-19 Rolls-Royce Deutschland Ltd & Co Kg Sound absorber, in particular for a gas turbine exhaust cone and method for its production
FR2987079B1 (en) * 2012-02-17 2017-02-10 Snecma Propulsion Solide EXHAUST CONE WITH ACOUSTICAL ATTENUATION SYSTEM
FR3061933B1 (en) * 2017-01-18 2019-08-16 Airbus Operations INTERNAL STRUCTURE OF A PRIMARY EJECTION DUCT
FR3084917B1 (en) * 2018-08-09 2021-04-16 Safran Ceram SET FOR A TURBOMACHINE EJECTION TUBE

Also Published As

Publication number Publication date
FR3117151A1 (en) 2022-06-10
WO2022123142A1 (en) 2022-06-16

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