FR3084917B1 - SET FOR A TURBOMACHINE EJECTION TUBE - Google Patents

SET FOR A TURBOMACHINE EJECTION TUBE Download PDF

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Publication number
FR3084917B1
FR3084917B1 FR1857407A FR1857407A FR3084917B1 FR 3084917 B1 FR3084917 B1 FR 3084917B1 FR 1857407 A FR1857407 A FR 1857407A FR 1857407 A FR1857407 A FR 1857407A FR 3084917 B1 FR3084917 B1 FR 3084917B1
Authority
FR
France
Prior art keywords
radially
core
turbomachine
shell
ejection tube
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
FR1857407A
Other languages
French (fr)
Other versions
FR3084917A1 (en
Inventor
Eric Conete
Eric Bouillon
Eric Philippe
Yann Richard
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 FR1857407A priority Critical patent/FR3084917B1/en
Publication of FR3084917A1 publication Critical patent/FR3084917A1/en
Application granted granted Critical
Publication of FR3084917B1 publication Critical patent/FR3084917B1/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
    • F02K1/44—Nozzles having means, e.g. a shield, reducing sound radiation in a specified direction
    • 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
    • F02K1/52—Nozzles specially constructed for positioning adjacent to another nozzle or to a fixed member, e.g. fairing
    • 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
    • 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

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)

Abstract

L'invention concerne un ensemble (4) pour une tuyère d'éjection (1) de turbomachine, comportant une virole annulaire radialement externe (5), destinée à délimiter une veine d'écoulement des gaz, une âme (6) comportant des alvéoles et montée radialement à l'intérieur de la virole (5), et une peau radialement interne (7) située radialement à l'intérieur de l'âme (6), caractérisé en ce que la peau radialement interne (7) est fixée par collage sur une surface radialement interne de l'âme (6), ladite peau (7) et/ou une surface radialement externe de l'âme (6) étant fixées par collage à la virole radialement externe (5).The invention relates to an assembly (4) for a turbomachine ejection nozzle (1), comprising a radially outer annular shell (5), intended to delimit a gas flow stream, a core (6) comprising cells and mounted radially inside the shell (5), and a radially internal skin (7) located radially inside the core (6), characterized in that the radially internal skin (7) is fixed by bonding to a radially inner surface of the core (6), said skin (7) and / or a radially outer surface of the core (6) being fixed by bonding to the radially outer shell (5).

FR1857407A 2018-08-09 2018-08-09 SET FOR A TURBOMACHINE EJECTION TUBE Active FR3084917B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1857407A FR3084917B1 (en) 2018-08-09 2018-08-09 SET FOR A TURBOMACHINE EJECTION TUBE

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1857407A FR3084917B1 (en) 2018-08-09 2018-08-09 SET FOR A TURBOMACHINE EJECTION TUBE

Publications (2)

Publication Number Publication Date
FR3084917A1 FR3084917A1 (en) 2020-02-14
FR3084917B1 true FR3084917B1 (en) 2021-04-16

Family

ID=63896390

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1857407A Active FR3084917B1 (en) 2018-08-09 2018-08-09 SET FOR A TURBOMACHINE EJECTION TUBE

Country Status (1)

Country Link
FR (1) FR3084917B1 (en)

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3115568B1 (en) * 2020-10-27 2023-06-30 Safran Ceram TURBOMACHINE TURBINE ASSEMBLY
FR3115829B1 (en) * 2020-11-05 2022-10-14 Safran Nacelles Fixing an exhaust cone in a turbomachine nozzle
FR3115832B1 (en) * 2020-11-05 2023-04-21 Safran Nacelles Set for a turbomachine
FR3117151B1 (en) * 2020-12-09 2023-01-13 Safran Ceram TURBOMACHINE SET
FR3129181B1 (en) * 2021-11-18 2024-04-19 Safran Ceram Nozzle element for a turbomachine

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4340951A1 (en) * 1992-12-04 1994-06-09 Grumman Aerospace Corp One-piece engine inlet sound tube
FR2933224B1 (en) * 2008-06-25 2010-10-29 Aircelle Sa ACCOUSTIC PANEL FOR EJECTION TUBE
FR2934641B1 (en) * 2008-07-30 2011-03-04 Aircelle Sa ACOUSTICAL ATTENUATION PANEL FOR AN AIRCRAFT ENGINE NACELLE
FR2949820B1 (en) * 2009-09-04 2011-10-14 Aircelle Sa STRUCTURING ASSEMBLY FOR AN EJECTION TUBE.
FR2978989B1 (en) * 2011-08-12 2013-07-26 Aircelle Sa EJECTION CONE FOR AIRCRAFT TURBOJET ENGINE

Also Published As

Publication number Publication date
FR3084917A1 (en) 2020-02-14

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