FR3080168B1 - Ensemble pour une chambre de combustion de turbomachine - Google Patents

Ensemble pour une chambre de combustion de turbomachine Download PDF

Info

Publication number
FR3080168B1
FR3080168B1 FR1853274A FR1853274A FR3080168B1 FR 3080168 B1 FR3080168 B1 FR 3080168B1 FR 1853274 A FR1853274 A FR 1853274A FR 1853274 A FR1853274 A FR 1853274A FR 3080168 B1 FR3080168 B1 FR 3080168B1
Authority
FR
France
Prior art keywords
assembly
combustion chamber
zone
shell
ferrule
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
FR1853274A
Other languages
English (en)
Other versions
FR3080168A1 (fr
Inventor
Marcel Arthur Bunel Jacques
Eric Lefebvre Alexandre
Marc Matthieu Leparoux Julien
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 Aircraft Engines SAS
Original Assignee
Safran Aircraft Engines SAS
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 Aircraft Engines SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1853274A priority Critical patent/FR3080168B1/fr
Publication of FR3080168A1 publication Critical patent/FR3080168A1/fr
Application granted granted Critical
Publication of FR3080168B1 publication Critical patent/FR3080168B1/fr
Active legal-status Critical Current
Anticipated expiration legal-status Critical

Links

Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03041—Effusion cooled combustion chamber walls or domes
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • 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)
  • Portable Nailing Machines And Staplers (AREA)

Abstract

L'invention concerne un ensemble pour une chambre de combustion d'une turbomachine, comportant une virole annulaire (3) s'étendant selon un axe longitudinal, ladite virole (3) comportant une surface intérieure destinée à être tournée vers un foyer de la chambre de combustion et une surface extérieure (25) opposée à la surface intérieure, la virole (3) comprenant un élément perturbateur, la virole (3) comportant au moins une première zone (29) comportant des premières perforations (30), la virole (3) comportant une seconde zone (31) située directement en aval de l'élément perturbateur, la seconde zone (31) comportant plusieurs rangées (34) de secondes perforations (32) traversant ladite virole (3).
FR1853274A 2018-04-13 2018-04-13 Ensemble pour une chambre de combustion de turbomachine Active FR3080168B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1853274A FR3080168B1 (fr) 2018-04-13 2018-04-13 Ensemble pour une chambre de combustion de turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1853274A FR3080168B1 (fr) 2018-04-13 2018-04-13 Ensemble pour une chambre de combustion de turbomachine
FR1853274 2018-04-13

Publications (2)

Publication Number Publication Date
FR3080168A1 FR3080168A1 (fr) 2019-10-18
FR3080168B1 true FR3080168B1 (fr) 2020-03-20

Family

ID=62223030

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1853274A Active FR3080168B1 (fr) 2018-04-13 2018-04-13 Ensemble pour une chambre de combustion de turbomachine

Country Status (1)

Country Link
FR (1) FR3080168B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116147016B (zh) 2021-11-22 2025-09-19 通用电气公司 用于燃料-空气混合器组件的套圈

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6145319A (en) * 1998-07-16 2000-11-14 General Electric Company Transitional multihole combustion liner
US7216485B2 (en) * 2004-09-03 2007-05-15 General Electric Company Adjusting airflow in turbine component by depositing overlay metallic coating
US7509809B2 (en) * 2005-06-10 2009-03-31 Pratt & Whitney Canada Corp. Gas turbine engine combustor with improved cooling
FR2958372B1 (fr) * 2010-03-30 2013-05-17 Snecma Chambre de combustion de turbomachine.

Also Published As

Publication number Publication date
FR3080168A1 (fr) 2019-10-18

Similar Documents

Publication Publication Date Title
FR3081211B1 (fr) Ensemble pour une chambre de combustion de turbomachine
US8844491B2 (en) Laser spark plug
FR2882488B1 (fr) Element ultrasonique
FR3071296B1 (fr) Dispositif d'etancheite pour organe de dialogue homme-machine
MA30425B1 (fr) ANTICORPS D'AFFINITE ELEVEE HUMAINS ET HUMANISES A FONCTION DE BLOCAGE ANTI-INTEGRINE a5ß1 AYANT UNE IMMUNOGENICITE REDUITE
FR3103630B1 (fr) Puce fonctionnelle adaptee pour etre assemblee a des elements filaires, et procede de fabrication d’une telle puce
DE59610628D1 (de) Dichtungsanordnung
FR3079560B1 (fr) Dispositif de refroidissement pour une turbine d'une turbomachine
FR3082908B1 (fr) Dispositif de poulie pour galet tendeur ou enrouleur
FR3072749B1 (fr) Train d'engrenages epicycloidal
ATE438023T1 (de) Kombinationsschalldämpfer
FR3099801B1 (fr) Ensemble pour une turbine de turbomachine
FR3078895B1 (fr) Filtre et cartouche amovible, avec deux niveaux d'etancheite dans un puits de la base du filtre
FR3121951B1 (fr) Systeme de renforcement pour un carter de soufflante en materiau composite, carter de soufflante et turbomachine correspondants
WO2019053297A3 (fr) Ensemble destiné à générer de l'énergie électrique ou thermique à partir d'un système de freinage
FR3087510B1 (fr) Unité bague extérieure de roulement à collerette
FR3099798B1 (fr) Ensemble pour une turbine de turbomachine
FR3058458B1 (fr) Etage de turbine de turbomachine pourvu de moyens d'etancheite
FR3087509B1 (fr) Palier en élastomère ayant un embout d’extrémité de poids réduit
FR3094049B1 (fr) Rotule sphérique
FR3063231B1 (fr) Element d'injection de gaz pour unite de craquage catalytique fluide et systeme de distribution de gaz equipe de cet element d'injection.
FR3096394B1 (fr) Ensemble pour turbomachine
FR3089561B1 (fr) Dispositif ameliore d’etancheite a l’air destine a etre interpose entre un element de carter de turbomachine d’aeronef a double flux, et un element de nacelle
JP2003254020A (ja) 内燃機関用バルブステムシール
FR3087694B1 (fr) Dispositif destine a etre positionne a proximite d’une articulation et systeme general comportant un tel dispositif

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20191018

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5

PLFP Fee payment

Year of fee payment: 6

PLFP Fee payment

Year of fee payment: 7

PLFP Fee payment

Year of fee payment: 8

PLFP Fee payment

Year of fee payment: 9