FR3111949B1 - Acoustic box for an ejection cone - Google Patents

Acoustic box for an ejection cone Download PDF

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Publication number
FR3111949B1
FR3111949B1 FR2006704A FR2006704A FR3111949B1 FR 3111949 B1 FR3111949 B1 FR 3111949B1 FR 2006704 A FR2006704 A FR 2006704A FR 2006704 A FR2006704 A FR 2006704A FR 3111949 B1 FR3111949 B1 FR 3111949B1
Authority
FR
France
Prior art keywords
annular wall
partitions
longitudinal
outer annular
circumferential
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
FR2006704A
Other languages
French (fr)
Other versions
FR3111949A1 (en
Inventor
Eric Conete
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 FR2006704A priority Critical patent/FR3111949B1/en
Publication of FR3111949A1 publication Critical patent/FR3111949A1/en
Application granted granted Critical
Publication of FR3111949B1 publication Critical patent/FR3111949B1/en
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
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENTS OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/04—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of exhaust outlets or jet pipes
    • B64D33/06—Silencing exhaust or propulsion jets
    • 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
    • F02K1/82—Jet pipe walls, e.g. liners
    • F02K1/827—Sound absorbing structures or liners
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/23—Three-dimensional prismatic
    • F05D2250/232—Three-dimensional prismatic conical
    • 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
    • F05D2250/20—Three-dimensional
    • F05D2250/28—Three-dimensional patterned
    • 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
    • F05D2260/36—Retaining components in desired mutual position by a form fit connection, e.g. by interlocking
    • 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
    • F05D2260/963—Preventing, counteracting or reducing vibration or noise by Helmholtz resonators
    • 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]
    • 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

Abstract

Le présent exposé concerne un ensemble pour turbine de turbomachine d’axe longitudinal (X) comprenant un cône d’éjection comprenant une paroi annulaire radialement externe (102) d’écoulement d’un flux de gaz chauds et un caisson acoustique (103) agencé radialement à l’intérieur de ladite paroi annulaire externe (102), ledit caisson acoustique (103) comprenant une paroi annulaire radialement interne (104), une pluralité de cloisons circonférentielles (120) et une pluralité de cloisons longitudinales (118) agencées entre la paroi annulaire externe (102) et la paroi annulaire interne (104), lesdites cloisons circonférentielles (120) et longitudinales (118) étant emboitées les unes dans les autres de façon à former une structure alvéolaire, etdans lequel les cloisons circonférentielles (120) sont fixées à l’une de la paroi annulaire interne (104) et de la paroi annulaire externe (102), et les cloisons longitudinales (118) sont fixées à l’autre de la paroi annulaire interne (104) et de la paroi annulaire externe (102), les cloisons circonférentielles (120) et les cloisons longitudinales (118) étant libres en déplacement l’une par rapport à l’autre. Figure à publier avec l’abrégé : figure n°3This presentation relates to an assembly for a turbomachine turbine with a longitudinal axis (X) comprising an ejection cone comprising a radially outer annular wall (102) for the flow of a stream of hot gases and an acoustic box (103) arranged radially inside said outer annular wall (102), said acoustic box (103) comprising a radially inner annular wall (104), a plurality of circumferential partitions (120) and a plurality of longitudinal partitions (118) arranged between the outer annular wall (102) and the inner annular wall (104), said circumferential (120) and longitudinal (118) partitions being nested one inside the other so as to form a honeycomb structure, andin which the circumferential partitions (120) are attached to one of the inner annular wall (104) and the outer annular wall (102), and the longitudinal partitions (118) are attached to the other of the inner annular wall (104) and the p outer annular wall (102), the circumferential partitions (120) and the longitudinal partitions (118) being free to move relative to each other. Figure to be published with abstract: Figure 3

FR2006704A 2020-06-26 2020-06-26 Acoustic box for an ejection cone Active FR3111949B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2006704A FR3111949B1 (en) 2020-06-26 2020-06-26 Acoustic box for an ejection cone

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2006704 2020-06-26
FR2006704A FR3111949B1 (en) 2020-06-26 2020-06-26 Acoustic box for an ejection cone

Publications (2)

Publication Number Publication Date
FR3111949A1 FR3111949A1 (en) 2021-12-31
FR3111949B1 true FR3111949B1 (en) 2022-06-10

Family

ID=72644431

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2006704A Active FR3111949B1 (en) 2020-06-26 2020-06-26 Acoustic box for an ejection cone

Country Status (1)

Country Link
FR (1) FR3111949B1 (en)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2933224B1 (en) * 2008-06-25 2010-10-29 Aircelle Sa ACCOUSTIC PANEL FOR EJECTION TUBE
US9551239B2 (en) * 2015-04-22 2017-01-24 Rohr, Inc. Exhaust assembly center body
FR3081510B1 (en) * 2018-05-24 2020-05-29 Safran Nacelles ACOUSTIC MITIGATION PANEL FOR AIRCRAFT TURBOREACTOR NACELLE
FR3084011B1 (en) * 2018-07-17 2021-02-26 Safran Ceram METHOD OF MANUFACTURING AN ACCOUSTIC PANEL

Also Published As

Publication number Publication date
FR3111949A1 (en) 2021-12-31

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Effective date: 20211231

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