FR3040439B1 - Turboreacteur double flux dote d'une paroi de confluence - Google Patents

Turboreacteur double flux dote d'une paroi de confluence Download PDF

Info

Publication number
FR3040439B1
FR3040439B1 FR1558068A FR1558068A FR3040439B1 FR 3040439 B1 FR3040439 B1 FR 3040439B1 FR 1558068 A FR1558068 A FR 1558068A FR 1558068 A FR1558068 A FR 1558068A FR 3040439 B1 FR3040439 B1 FR 3040439B1
Authority
FR
France
Prior art keywords
air flow
primary
confluence
low pressure
double
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
FR1558068A
Other languages
English (en)
Other versions
FR3040439A1 (fr
Inventor
Alain Christophe Bourgois Sebastien
Marie Yves Emile Le Pannerer Brice
Christophe Pieussergues
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
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 Safran Aircraft Engines SAS, SNECMA SAS filed Critical Safran Aircraft Engines SAS
Priority to FR1558068A priority Critical patent/FR3040439B1/fr
Publication of FR3040439A1 publication Critical patent/FR3040439A1/fr
Application granted granted Critical
Publication of FR3040439B1 publication Critical patent/FR3040439B1/fr
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
    • F02K1/38—Introducing air inside the jet
    • F02K1/386—Introducing air inside the jet mixing devices in the jet pipe, e.g. for mixing primary and secondary flow
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
    • F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
    • F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
    • F02C3/10—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor with another turbine driving an output shaft but not driving the compressor
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02K—JET-PROPULSION PLANTS
    • F02K3/00—Plants including a gas turbine driving a compressor or a ducted fan
    • F02K3/02—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber
    • F02K3/04—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type
    • F02K3/065—Plants including a gas turbine driving a compressor or a ducted fan in which part of the working fluid by-passes the turbine and combustion chamber the plant including ducted fans, i.e. fans with high volume, low pressure outputs, for augmenting the jet thrust, e.g. of double-flow type with front and aft fans
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/324—Application in turbines in gas turbines to drive unshrouded, low solidity propeller
    • 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
    • F05D2220/00—Application
    • F05D2220/30—Application in turbines
    • F05D2220/32—Application in turbines in gas turbines
    • F05D2220/325—Application in turbines in gas turbines to drive unshrouded, high solidity propeller

Landscapes

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

Abstract

Un turboréacteur (1) à double flux comprenant un compresseur basse pression (3) apte à prélever un flux d'air destiné à être divisé en un flux d'air primaire (F1) et un flux d'air secondaire (F2) distincts, un canal primaire (10) apte à acheminer le flux d'air primaire (F1) depuis le compresseur basse pression (3) jusqu'à une zone de confluence (12) des flux d'air primaire et secondaire (F1 et F2) permettant la dilution du flux d'air secondaire (F2) dans le flux d'air primaire (Fi), un canal secondaire (11) apte à acheminer le flux d'air secondaire depuis le compresseur basse pression (3) jusqu'à la zone de confluence (12). Le turboréacteur (1) comprend une paroi annulaire de confluence (13) percée d'une pluralité d'orifices traversant (14).
FR1558068A 2015-08-31 2015-08-31 Turboreacteur double flux dote d'une paroi de confluence Active FR3040439B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1558068A FR3040439B1 (fr) 2015-08-31 2015-08-31 Turboreacteur double flux dote d'une paroi de confluence

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1558068 2015-08-31
FR1558068A FR3040439B1 (fr) 2015-08-31 2015-08-31 Turboreacteur double flux dote d'une paroi de confluence

Publications (2)

Publication Number Publication Date
FR3040439A1 FR3040439A1 (fr) 2017-03-03
FR3040439B1 true FR3040439B1 (fr) 2020-06-05

Family

ID=54783769

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1558068A Active FR3040439B1 (fr) 2015-08-31 2015-08-31 Turboreacteur double flux dote d'une paroi de confluence

Country Status (1)

Country Link
FR (1) FR3040439B1 (fr)

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US6981841B2 (en) * 2003-11-20 2006-01-03 General Electric Company Triple circuit turbine cooling
US9212623B2 (en) * 2007-12-26 2015-12-15 United Technologies Corporation Heat exchanger arrangement for turbine engine
US8683814B2 (en) * 2012-02-15 2014-04-01 United Technologies Corporation Gas turbine engine component with impingement and lobed cooling hole
US10197008B2 (en) * 2013-02-19 2019-02-05 United Technologies Corporation Gas turbine engine including a third flowpath exhaust nozzle

Also Published As

Publication number Publication date
FR3040439A1 (fr) 2017-03-03

Similar Documents

Publication Publication Date Title
EP3106621A3 (fr) Couvercle d'orientation de flux pour composant de moteur
CH709500A8 (de) Brennstoffdüse mit einem Kühlkanal in einem Hauptkörper eines Aussenmantels.
GB2557475A (en) Breathing assistance apparatus
PL395668A1 (pl) Zespól zaworowy
MX2016016427A (es) Artículo protector para la cabeza con flujo de aire.
EP2228602A3 (fr) Système de refroidissement de chemise de chambre de combustion
PL415184A1 (pl) Dysza wylotowa dla silnika z turbiną gazową
EP2778375A3 (fr) Turbine à débit axial et centrale électrique l'incluant
WO2015138031A3 (fr) Gestion thermique de bord de compresseur
EP2660518A3 (fr) Résonateur acoustique situé au niveau du manchon d'écoulement d'une chambre de combustion de turbine à gaz
MX2018004804A (es) Triturador de medios de chorro.
FR3039199B1 (fr) Aubage de distributeur haute pression avec un insert a geometrie variable
EP3040522A8 (fr) Composant de trajet de gaz chaud et procédés de fabrication
SG10201808755YA (en) Filter
BR112018000986A2 (pt) dispositivos para produção de vácuo utilizando o efeito venturi, tendo uma pluralidade de subpassagem e saídas motrizes na seção motriz
BR112015025846A2 (pt) dispositivo de descongelamento de um bico de separação de turbomáquina aeronáutica
EP3106755A3 (fr) Ensemble de conduit de combustion pour turbine à gaz
JOP20180032A1 (ar) جهاز لإنتاج روابط مغزولة من فتائل متواصلة
MX2017001095A (es) Impactor en cascada.
FR3055655B1 (fr) Carter intermediaire de turbine de turbomachine
EP4060231A3 (fr) Système d'injection de vapeur étagé
FR3040439B1 (fr) Turboreacteur double flux dote d'une paroi de confluence
EA201691652A1 (ru) Система форсунки для гасительной текучей среды для стационарных систем огнетушения, имеющая диафрагменное кольцо, а также форсунка для гасительной текучей среды и диафрагменное кольцо для нее
PL421253A1 (pl) System wylotowy sprężarki
FR3049652B1 (fr) Turbomachine d'aeronef a dispositif de decharge

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20170303

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

CD Change of name or company name

Owner name: SAFRAN AIRCRAFT ENGINES, FR

Effective date: 20180809

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