FR3040439B1 - DOUBLE-FLOW TURBOREACTOR WITH CONFLUENCE WALL - Google Patents

DOUBLE-FLOW TURBOREACTOR WITH CONFLUENCE WALL Download PDF

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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
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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
French (fr)
Other versions
FR3040439A1 (en
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/en
Publication of FR3040439A1 publication Critical patent/FR3040439A1/en
Application granted granted Critical
Publication of FR3040439B1 publication Critical patent/FR3040439B1/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
    • F02K1/38—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).A turbofan (1) comprising a low pressure compressor (3) capable of taking off an air flow intended to be divided into a separate primary air flow (F1) and a secondary air flow (F2), a primary channel (10) capable of conveying the primary air flow (F1) from the low pressure compressor (3) to a zone of confluence (12) of the primary and secondary air flows (F1 and F2) allowing dilution of the secondary air flow (F2) in the primary air flow (Fi), a secondary channel (11) capable of conveying the secondary air flow from the low pressure compressor (3) to the area confluence (12). The turbojet engine (1) comprises an annular confluence wall (13) pierced with a plurality of through orifices (14).

FR1558068A 2015-08-31 2015-08-31 DOUBLE-FLOW TURBOREACTOR WITH CONFLUENCE WALL Active FR3040439B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1558068A FR3040439B1 (en) 2015-08-31 2015-08-31 DOUBLE-FLOW TURBOREACTOR WITH CONFLUENCE WALL

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1558068A FR3040439B1 (en) 2015-08-31 2015-08-31 DOUBLE-FLOW TURBOREACTOR WITH CONFLUENCE WALL
FR1558068 2015-08-31

Publications (2)

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

Family

ID=54783769

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1558068A Active FR3040439B1 (en) 2015-08-31 2015-08-31 DOUBLE-FLOW TURBOREACTOR WITH CONFLUENCE WALL

Country Status (1)

Country Link
FR (1) FR3040439B1 (en)

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
EP2959146B1 (en) * 2013-02-19 2018-04-04 United Technologies Corporation Turbofan engine including third flowpath exhaust nozzle

Also Published As

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

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