BR112013006037A2 - capuz aerodinâmico para a traseira de uma câmara de combustão de uma turbomáquina. - Google Patents

capuz aerodinâmico para a traseira de uma câmara de combustão de uma turbomáquina.

Info

Publication number
BR112013006037A2
BR112013006037A2 BR112013006037A BR112013006037A BR112013006037A2 BR 112013006037 A2 BR112013006037 A2 BR 112013006037A2 BR 112013006037 A BR112013006037 A BR 112013006037A BR 112013006037 A BR112013006037 A BR 112013006037A BR 112013006037 A2 BR112013006037 A2 BR 112013006037A2
Authority
BR
Brazil
Prior art keywords
combustion chamber
hood
projections
turbocharger
end wall
Prior art date
Application number
BR112013006037A
Other languages
English (en)
Other versions
BR112013006037B1 (pt
Inventor
Didier Hippolyte Hernandez
Sébastien Alain Christophe Bourgois
Original Assignee
Snecma
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 filed Critical Snecma
Publication of BR112013006037A2 publication Critical patent/BR112013006037A2/pt
Publication of BR112013006037B1 publication Critical patent/BR112013006037B1/pt

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
    • F23R3/10—Air inlet arrangements for primary air
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
    • F04D—NON-POSITIVE-DISPLACEMENT PUMPS
    • F04D29/00—Details, component parts, or accessories
    • F04D29/40—Casings; Connections of working fluid
    • F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
    • F04D29/44—Fluid-guiding means, e.g. diffusers
    • F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
    • 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
    • F23R3/26—Controlling the air flow
    • 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
    • F05D2250/50—Inlet or outlet
    • F05D2250/52—Outlet

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Supercharger (AREA)

Abstract

capuz aerodinâmico para a traseira de uma câmara de combustão de uma turbomáquina. a presente invenção refere-se a um capuz anular (42) que tem uma face interna pretendida para cobrir a parede de extremidade traseira (33) de uma câmara de combustão anular (12) de uma turbomáquina (14) adapatada com um compressor centífugo, em conjunto com uma face externa oposta à referida face interna, e em que o referido capuz inclui múltiplas aberturas (54) pretendidas para se permitir que injetores de combustível (38,40) suportados pela referida parede de extremidade traseira (33) da câmara de combustão passem através dali em conjunto com múltiplas saliências (56), as quais se estendem como projeções na referida face externa radialmente em direção ao interior respectivamente a partir das respectivas bordas radialmente internas (58) das referidas aberturas (54), de modo que cada uma das referidas saliências (56) delimite uma extensão (60) da abertura correspondente (54) aberta radialmente em direção ao exterior, de modo a formar uma pá côncava de admissão de ar.
BR112013006037-9A 2010-09-14 2011-09-13 Capuz anular, camara de combustao anular e turbomaquina BR112013006037B1 (pt)

Applications Claiming Priority (3)

Application Number Priority Date Filing Date Title
FR1057319 2010-09-14
FR1057319A FR2964725B1 (fr) 2010-09-14 2010-09-14 Carenage aerodynamique pour fond de chambre de combustion
PCT/FR2011/052084 WO2012035248A1 (fr) 2010-09-14 2011-09-13 Carenage aerodynamique pour fond de chambre de combustion de turbomachine

Publications (2)

Publication Number Publication Date
BR112013006037A2 true BR112013006037A2 (pt) 2016-06-07
BR112013006037B1 BR112013006037B1 (pt) 2020-11-17

Family

ID=44063986

Family Applications (1)

Application Number Title Priority Date Filing Date
BR112013006037-9A BR112013006037B1 (pt) 2010-09-14 2011-09-13 Capuz anular, camara de combustao anular e turbomaquina

Country Status (8)

Country Link
US (1) US8661829B2 (pt)
EP (1) EP2616742B1 (pt)
CN (1) CN103080652B (pt)
BR (1) BR112013006037B1 (pt)
CA (1) CA2811163C (pt)
FR (1) FR2964725B1 (pt)
RU (1) RU2572736C2 (pt)
WO (1) WO2012035248A1 (pt)

Families Citing this family (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2943403B1 (fr) 2009-03-17 2014-11-14 Snecma Chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air
FR2945854B1 (fr) 2009-05-19 2015-08-07 Snecma Vrille melangeuse pour un injecteur de carburant dans une chambre de combustion d'une turbine a gaz et dispositif de combustion correspondant
FR3003632B1 (fr) 2013-03-19 2016-10-14 Snecma Systeme d'injection pour chambre de combustion de turbomachine comportant une paroi annulaire a profil interne convergent
US9650916B2 (en) 2014-04-09 2017-05-16 Honeywell International Inc. Turbomachine cooling systems
FR3035481B1 (fr) * 2015-04-23 2017-05-05 Snecma Chambre de combustion de turbomachine comportant un dispositif de guidage de flux d'air de forme specifique
US10619856B2 (en) * 2017-03-13 2020-04-14 Rolls-Royce Corporation Notched gas turbine combustor cowl
US10816213B2 (en) 2018-03-01 2020-10-27 General Electric Company Combustor assembly with structural cowl and decoupled chamber
US10907831B2 (en) * 2018-05-07 2021-02-02 Rolls-Royce Corporation Ram pressure recovery fuel nozzle with a scoop
US10982852B2 (en) 2018-11-05 2021-04-20 Rolls-Royce Corporation Cowl integration to combustor wall

Family Cites Families (25)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB239127A (en) * 1925-03-25 1925-09-03 Stephen Edward Beeson Improvements in or relating to sawing, cutting and similar machines
BE795867A (fr) * 1972-03-01 1973-06-18 Gen Electric Dispositif pour uniformiser l'ecoulement de l'air dans une turbine a gaz
FR2559856B1 (fr) * 1984-02-17 1987-06-19 Caillau Ets Collier de serrage et son procede de fabrication
FR2686683B1 (fr) * 1992-01-28 1994-04-01 Snecma Turbomachine a chambre de combustion demontable.
CA2089272C (en) 1992-03-23 2002-09-03 James Norman Reinhold, Jr. Impact resistant combustor
US5279126A (en) * 1992-12-18 1994-01-18 United Technologies Corporation Diffuser-combustor
DE10159668A1 (de) * 2001-12-05 2003-06-18 Rolls Royce Deutschland Brennkammerkopf
GB2391297A (en) * 2002-07-24 2004-02-04 Rolls Royce Plc Gas supply assembly
US7222488B2 (en) * 2002-09-10 2007-05-29 General Electric Company Fabricated cowl for double annular combustor of a gas turbine engine
US6952927B2 (en) * 2003-05-29 2005-10-11 General Electric Company Multiport dome baffle
FR2856467B1 (fr) * 2003-06-18 2005-09-02 Snecma Moteurs Chambre de combustion annulaire de turbomachine
RU2250415C1 (ru) * 2003-08-05 2005-04-20 Открытое акционерное общество "Научно-производственное объединение "Сатурн" (ОАО "НПО "Сатурн") Кольцевая камера сгорания газотурбинного двигателя
FR2885201B1 (fr) * 2005-04-28 2010-09-17 Snecma Moteurs Chambre de combustion aisement demontable a performance aerodynamique amelioree
FR2888631B1 (fr) * 2005-07-18 2010-12-10 Snecma Turbomachine a distribution angulaire de l'air
FR2897145B1 (fr) * 2006-02-08 2013-01-18 Snecma Chambre de combustion annulaire de turbomachine a fixations alternees.
FR2897144B1 (fr) * 2006-02-08 2008-05-02 Snecma Sa Chambre de combustion de turbomachine a fentes tangentielles
FR2897417A1 (fr) * 2006-02-10 2007-08-17 Snecma Sa Chambre de combustion annulaire d'une turbomachine
FR2910597B1 (fr) * 2006-12-22 2009-03-20 Snecma Sa Carenage pour fond de chambre de combustion
FR2911668B1 (fr) * 2007-01-18 2009-03-20 Snecma Sa Chambre de combustion d'une turbomachine
FR2914399B1 (fr) * 2007-03-27 2009-10-02 Snecma Sa Carenage pour fond de chambre de combustion.
FR2921464B1 (fr) 2007-09-24 2014-03-28 Snecma Agencement de systemes d'injection dans un fond de chambre de combustion d'un moteur d'aeronef
FR2929690B1 (fr) * 2008-04-03 2012-08-17 Snecma Propulsion Solide Chambre de combustion sectorisee en cmc pour turbine a gaz
FR2943403B1 (fr) * 2009-03-17 2014-11-14 Snecma Chambre de combustion de turbomachine comprenant des moyens ameliores d'alimentation en air
FR2945854B1 (fr) 2009-05-19 2015-08-07 Snecma Vrille melangeuse pour un injecteur de carburant dans une chambre de combustion d'une turbine a gaz et dispositif de combustion correspondant
FR2975465B1 (fr) 2011-05-19 2018-03-09 Safran Aircraft Engines Paroi pour chambre de combustion de turbomachine comprenant un agencement optimise d'orifices d'entree d'air

Also Published As

Publication number Publication date
CA2811163A1 (fr) 2012-03-22
CA2811163C (fr) 2018-10-23
US8661829B2 (en) 2014-03-04
RU2572736C2 (ru) 2016-01-20
US20130160452A1 (en) 2013-06-27
EP2616742A1 (fr) 2013-07-24
FR2964725A1 (fr) 2012-03-16
EP2616742B1 (fr) 2018-10-31
CN103080652A (zh) 2013-05-01
RU2013117008A (ru) 2014-10-20
WO2012035248A1 (fr) 2012-03-22
FR2964725B1 (fr) 2012-10-12
BR112013006037B1 (pt) 2020-11-17
CN103080652B (zh) 2015-05-06

Similar Documents

Publication Publication Date Title
BR112013006037A2 (pt) capuz aerodinâmico para a traseira de uma câmara de combustão de uma turbomáquina.
BR112015027221A2 (pt) câmara de admissão de ar e sistema de motor de turbina a gás
WO2015147929A3 (en) Cooling an aperture body of a combustor wall
BR112014000942A2 (pt) ventilador
EP2256299A3 (en) Deflector for a gas turbine strut and vane assembly
WO2014178731A3 (en) A rotor assembly for an open cycle engine, and an open cycle engine
EP2532963A3 (en) Reverse-flow annular combustor for reduced emissions
WO2015017000A3 (en) Diffuser case strut for a turbine engine
EP2236930A3 (en) Combustor for gas turbine engine
EP2354491A3 (en) Gas turbine engine steam injection manifold
WO2015065550A3 (en) Fuel igniter assembly having heat-dissipating element and methods of using same
BR112013032000A2 (pt) montagem de fluxo de ar dotada de desempenho acústico aperfeiçoado
WO2015050592A3 (en) Gas turbine engine combustor liner panel
RU2015120552A (ru) Ступица выпускного корпуса для газотурбинного двигателя
RU2013119150A (ru) Охлаждающий бандажный узел турбины для газотурбинной установки (варианты)
WO2015112227A3 (en) Multiple injector holes for gas turbine engine vane
EP2144003A3 (en) A combustion liner for a gas turbine engine
BR112012013480A2 (pt) câmara de combustão de uma turbomáquina, e, turbomáquina, como um turborreator ou um turbopropulsor.
EP2144002A3 (en) Flow sleeve with tabbed direct combustion liner cooling air
DE602008005749D1 (de) Triebwerksgondel mit mindestens einer überdruckklappe
RU2013144762A (ru) Картер турбины, содержащий средства крепления секций кольца
RU2014142817A (ru) Воздухозаборник гондолы турбореактивного двигателя ламинарного типа
BR112015024444A2 (pt) dispositivo de separação de óleo
JP2016061506A5 (pt)
RU2011141837A (ru) Камера сгорания турбомашины, содержащая улучшенные средства питания воздухом

Legal Events

Date Code Title Description
B06F Objections, documents and/or translations needed after an examination request according [chapter 6.6 patent gazette]
B06U Preliminary requirement: requests with searches performed by other patent offices: procedure suspended [chapter 6.21 patent gazette]
B09A Decision: intention to grant [chapter 9.1 patent gazette]
B16A Patent or certificate of addition of invention granted [chapter 16.1 patent gazette]

Free format text: PRAZO DE VALIDADE: 20 (VINTE) ANOS CONTADOS A PARTIR DE 13/09/2011, OBSERVADAS AS CONDICOES LEGAIS.