EP1734305A3 - Assemblage d'une chambre de combustion annulaire de turbomachine - Google Patents

Assemblage d'une chambre de combustion annulaire de turbomachine Download PDF

Info

Publication number
EP1734305A3
EP1734305A3 EP06114424.2A EP06114424A EP1734305A3 EP 1734305 A3 EP1734305 A3 EP 1734305A3 EP 06114424 A EP06114424 A EP 06114424A EP 1734305 A3 EP1734305 A3 EP 1734305A3
Authority
EP
European Patent Office
Prior art keywords
nut
screw
axial
combustion chamber
chamber bottom
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.)
Granted
Application number
EP06114424.2A
Other languages
German (de)
English (en)
Other versions
EP1734305B1 (fr
EP1734305A2 (fr
Inventor
Mario De Sousa
Didier Hernandez
Laurent Marnas
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
SNECMA 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 SNECMA SAS filed Critical SNECMA SAS
Publication of EP1734305A2 publication Critical patent/EP1734305A2/fr
Publication of EP1734305A3 publication Critical patent/EP1734305A3/fr
Application granted granted Critical
Publication of EP1734305B1 publication Critical patent/EP1734305B1/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
    • F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
    • F23R3/60—Support structures; Attaching or mounting means
    • 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
    • F23R3/007—Continuous combustion chambers using liquid or gaseous fuel constructed mainly of ceramic components

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Ceramic Engineering (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Connection Of Plates (AREA)
  • Portable Nailing Machines And Staplers (AREA)

Abstract

Chambre de combustion annulaire (10) comportant des parois axiales (28) reliées par un fond de chambre (30) ayant un coefficient de dilatation thermique différent de celui des parois axiales, le fond de chambre étant muni d'une pluralité de brides d'accrochage (34) internes et externes fixées par des systèmes de fixation (36) sur des parties d'extrémité des parois axiales. Chaque système de fixation se compose d'une vis (40), d'un écrou (46) serré à l'une des extrémités de la vis, et d'une douille de coulissement (48) disposée autour de la vis entre l'écrou et la partie d'extrémité de la paroi axiale correspondante, un jeu radial (J) déterminé étant prévu entre l'écrou et la partie d'extrémité de la paroi axiale de façon à permettre en fonctionnement une libre dilatation radiale du fond de chambre (30) par rapport aux parois axiales.
EP06114424.2A 2005-06-14 2006-05-23 Assemblage d'une chambre de combustion annulaire de turbomachine Active EP1734305B1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR0505999A FR2887015B1 (fr) 2005-06-14 2005-06-14 Assemblage d'une chambre de combustion annulaire de turbomachine

Publications (3)

Publication Number Publication Date
EP1734305A2 EP1734305A2 (fr) 2006-12-20
EP1734305A3 true EP1734305A3 (fr) 2013-05-01
EP1734305B1 EP1734305B1 (fr) 2014-07-02

Family

ID=34955491

Family Applications (1)

Application Number Title Priority Date Filing Date
EP06114424.2A Active EP1734305B1 (fr) 2005-06-14 2006-05-23 Assemblage d'une chambre de combustion annulaire de turbomachine

Country Status (6)

Country Link
US (1) US7849696B2 (fr)
EP (1) EP1734305B1 (fr)
JP (1) JP2006349336A (fr)
CA (1) CA2548905C (fr)
FR (1) FR2887015B1 (fr)
RU (1) RU2400674C2 (fr)

Families Citing this family (33)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US7874059B2 (en) * 2006-01-12 2011-01-25 Siemens Energy, Inc. Attachment for ceramic matrix composite component
FR2911668B1 (fr) 2007-01-18 2009-03-20 Snecma Sa Chambre de combustion d'une turbomachine
GB2453946B (en) * 2007-10-23 2010-07-14 Rolls Royce Plc A Wall Element for use in Combustion Apparatus
GB0800294D0 (en) * 2008-01-09 2008-02-20 Rolls Royce Plc Gas heater
GB0801839D0 (en) * 2008-02-01 2008-03-05 Rolls Royce Plc combustion apparatus
GB2457281B (en) * 2008-02-11 2010-09-08 Rolls Royce Plc A Combustor Wall Arrangement with Parts Joined by Mechanical Fasteners
GB2460634B (en) * 2008-06-02 2010-07-07 Rolls Royce Plc Combustion apparatus
FR2935753B1 (fr) * 2008-09-08 2011-07-01 Snecma Propulsion Solide Liaisons souples a butee pour fixation de piece en cmc
GB0920371D0 (en) * 2009-11-23 2010-01-06 Rolls Royce Plc Combustor system
US8607577B2 (en) * 2009-11-24 2013-12-17 United Technologies Corporation Attaching ceramic matrix composite to high temperature gas turbine structure
US9322334B2 (en) * 2012-10-23 2016-04-26 General Electric Company Deformable mounting assembly
FR2998038B1 (fr) 2012-11-09 2017-12-08 Snecma Chambre de combustion pour une turbomachine
US10422532B2 (en) * 2013-08-01 2019-09-24 United Technologies Corporation Attachment scheme for a ceramic bulkhead panel
US10012104B2 (en) 2014-10-14 2018-07-03 United Technologies Corporation Gas turbine engine convergent/divergent nozzle with unitary synchronization ring for roller track nozzle
US10480321B2 (en) 2014-12-05 2019-11-19 Rolls-Royce Corporation Attachment of piloting feature
US9976746B2 (en) 2015-09-02 2018-05-22 General Electric Company Combustor assembly for a turbine engine
US10197278B2 (en) 2015-09-02 2019-02-05 General Electric Company Combustor assembly for a turbine engine
US11149646B2 (en) 2015-09-02 2021-10-19 General Electric Company Piston ring assembly for a turbine engine
US10168051B2 (en) * 2015-09-02 2019-01-01 General Electric Company Combustor assembly for a turbine engine
US10281153B2 (en) * 2016-02-25 2019-05-07 General Electric Company Combustor assembly
US9951649B2 (en) 2016-04-26 2018-04-24 Pratt & Whitney Canada Corp. Fuel flow divider valve mounting arrangement for a gas turbine engine
US10935242B2 (en) 2016-07-07 2021-03-02 General Electric Company Combustor assembly for a turbine engine
US10280959B2 (en) 2016-07-13 2019-05-07 Rohr, Inc. Sliding fastener systems to accommodate differential thermal growth
GB201613110D0 (en) 2016-07-29 2016-09-14 Rolls Royce Plc A combustion chamber
US20180051880A1 (en) * 2016-08-18 2018-02-22 General Electric Company Combustor assembly for a turbine engine
US10385709B2 (en) * 2017-02-23 2019-08-20 General Electric Company Methods and features for positioning a flow path assembly within a gas turbine engine
US11402097B2 (en) 2018-01-03 2022-08-02 General Electric Company Combustor assembly for a turbine engine
US11054136B2 (en) * 2018-11-30 2021-07-06 Pratt & Whitney Canada Corp. Interface for double-skin combustor liner
US11378012B2 (en) * 2019-12-12 2022-07-05 Rolls-Royce Plc Insert-mounted turbine assembly for a gas turbine engine
US11525577B2 (en) 2020-04-27 2022-12-13 Raytheon Technologies Corporation Extended bulkhead panel
EP3929487A1 (fr) * 2020-06-25 2021-12-29 General Electric Company Ensemble chambre de combustion pour moteur de turbine à gaz
CN113931872B (zh) * 2021-12-15 2022-03-18 成都中科翼能科技有限公司 一种燃气轮机压气机的双层鼓筒加强型转子结构
CN116697399A (zh) * 2022-02-28 2023-09-05 通用电气公司 具有柔性连接的燃烧器圆顶-导流板和衬里

Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1265033A1 (fr) * 2001-06-06 2002-12-11 Snecma Moteurs Chambre de combustion munie d'un système de fixation de fond de chambre
EP1265031A1 (fr) * 2001-06-06 2002-12-11 Snecma Moteurs Fixation de casquettes métalliques sur des parois de chambre de combustion CMC de turbomachine
EP1431665A2 (fr) * 2002-12-20 2004-06-23 General Electric Company Assemblage pour le montage de l'extrémité avant d'une chemise en composite à matrice céramique à l'intérieur d'une chambre de combustion de turbine à gaz
EP1479975A1 (fr) * 2003-05-20 2004-11-24 Snecma Moteurs Chambre de combustion ayant une liason souple entre un fond de chambre et une paroi de chambre

Patent Citations (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1265033A1 (fr) * 2001-06-06 2002-12-11 Snecma Moteurs Chambre de combustion munie d'un système de fixation de fond de chambre
EP1265031A1 (fr) * 2001-06-06 2002-12-11 Snecma Moteurs Fixation de casquettes métalliques sur des parois de chambre de combustion CMC de turbomachine
EP1431665A2 (fr) * 2002-12-20 2004-06-23 General Electric Company Assemblage pour le montage de l'extrémité avant d'une chemise en composite à matrice céramique à l'intérieur d'une chambre de combustion de turbine à gaz
EP1479975A1 (fr) * 2003-05-20 2004-11-24 Snecma Moteurs Chambre de combustion ayant une liason souple entre un fond de chambre et une paroi de chambre

Also Published As

Publication number Publication date
US20070107710A1 (en) 2007-05-17
RU2006120529A (ru) 2007-12-20
FR2887015A1 (fr) 2006-12-15
FR2887015B1 (fr) 2010-09-24
US7849696B2 (en) 2010-12-14
JP2006349336A (ja) 2006-12-28
EP1734305B1 (fr) 2014-07-02
EP1734305A2 (fr) 2006-12-20
RU2400674C2 (ru) 2010-09-27
CA2548905A1 (fr) 2006-12-14
CA2548905C (fr) 2013-09-17

Similar Documents

Publication Publication Date Title
EP1734305A3 (fr) Assemblage d'une chambre de combustion annulaire de turbomachine
RU2005108415A (ru) Уплотнительная прокладка между наружным и внутренним картерами отсека турбореактивного двигателя
DE502006006351D1 (de) Hochtemperaturfeste dichtungsanordnung, insbesondere für gasturbinen
EP1564494A3 (fr) Système de fixation pour tube de flamme ou garniture de chambre de combustion
DK1106892T3 (da) Tætningsring til rörformet element
EA032194B1 (ru) Раструбное соединение труб и способ установки раструбного соединения труб
EP1746348A3 (fr) Turbomachine à distribution angulaire de l'air
JP2004239438A (ja) 冷却媒体配管用連結装置
EP1657406A3 (fr) Joint statorique
WO2009043672A3 (fr) Tuyau ondulé flexible
BRPI0604266A (pt) sistema de instalação de motor
CA2398589A1 (fr) Plongeur a tampon avec sous-ensemble concave
FR3099801B1 (fr) Ensemble pour une turbine de turbomachine
US10167736B2 (en) Joint assembly
US20180347441A1 (en) Exhaust gas outlet system for a motor vehicle, motor vehicle having such an exhaust gas outlet system, and method for producing an exhaust gas outlet system
BRPI0407111A (pt) Luva para entradas de cabo e penetrações de tubos
CN103062508A (zh) 一种用于穿过机匣的异形螺母式浮动密封结构
SE0202367L (sv) Rörförbindningsdel med invändigt liggande dämpnigsselement
JP6372213B2 (ja) アクチュエータのガイドユニット
FR3072749B1 (fr) Train d'engrenages epicycloidal
EP1862735A3 (fr) Conduite annulaire à double flux et brûleur comportant une telle conduite
ATE410658T1 (de) Rohrwaffe
WO2007122631A3 (fr) Système d'étanchéité pour plaque tubulaire interne pour échangeurs de chaleur tubulaires
FR3119868B1 (fr) Système de combustion avec une chambre de combustion tubulaire et un échangeur de chaleur annulaire
DE50307002D1 (de) Pressverbindungsanordnung und Halteelement für eine Pressverbindung

Legal Events

Date Code Title Description
PUAI Public reference made under article 153(3) epc to a published international application that has entered the european phase

Free format text: ORIGINAL CODE: 0009012

17P Request for examination filed

Effective date: 20060523

AK Designated contracting states

Kind code of ref document: A2

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

PUAL Search report despatched

Free format text: ORIGINAL CODE: 0009013

AK Designated contracting states

Kind code of ref document: A3

Designated state(s): AT BE BG CH CY CZ DE DK EE ES FI FR GB GR HU IE IS IT LI LT LU LV MC NL PL PT RO SE SI SK TR

AX Request for extension of the european patent

Extension state: AL BA HR MK YU

RIC1 Information provided on ipc code assigned before grant

Ipc: F23R 3/60 20060101ALI20130326BHEP

Ipc: F23R 3/00 20060101AFI20130326BHEP

AKX Designation fees paid

Designated state(s): DE FR GB IT SE

GRAP Despatch of communication of intention to grant a patent

Free format text: ORIGINAL CODE: EPIDOSNIGR1

INTG Intention to grant announced

Effective date: 20140120

GRAS Grant fee paid

Free format text: ORIGINAL CODE: EPIDOSNIGR3

GRAA (expected) grant

Free format text: ORIGINAL CODE: 0009210

AK Designated contracting states

Kind code of ref document: B1

Designated state(s): DE FR GB IT SE

REG Reference to a national code

Ref country code: GB

Ref legal event code: FG4D

Free format text: NOT ENGLISH

REG Reference to a national code

Ref country code: DE

Ref legal event code: R096

Ref document number: 602006042111

Country of ref document: DE

Effective date: 20140814

REG Reference to a national code

Ref country code: SE

Ref legal event code: TRGR

REG Reference to a national code

Ref country code: DE

Ref legal event code: R097

Ref document number: 602006042111

Country of ref document: DE

PLBE No opposition filed within time limit

Free format text: ORIGINAL CODE: 0009261

STAA Information on the status of an ep patent application or granted ep patent

Free format text: STATUS: NO OPPOSITION FILED WITHIN TIME LIMIT

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 10

26N No opposition filed

Effective date: 20150407

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 11

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 12

REG Reference to a national code

Ref country code: FR

Ref legal event code: CD

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20170719

REG Reference to a national code

Ref country code: FR

Ref legal event code: PLFP

Year of fee payment: 13

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: IT

Payment date: 20230420

Year of fee payment: 18

Ref country code: FR

Payment date: 20230420

Year of fee payment: 18

Ref country code: DE

Payment date: 20230419

Year of fee payment: 18

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: SE

Payment date: 20230419

Year of fee payment: 18

PGFP Annual fee paid to national office [announced via postgrant information from national office to epo]

Ref country code: GB

Payment date: 20230420

Year of fee payment: 18