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FR3059047B1 - COMBUSTION CHAMBER INJECTOR FOR A TURBOMACHINE AND ITS MANUFACTURING PROCESS - Google Patents

COMBUSTION CHAMBER INJECTOR FOR A TURBOMACHINE AND ITS MANUFACTURING PROCESS Download PDF

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Publication number
FR3059047B1
FR3059047B1 FR1661318A FR1661318A FR3059047B1 FR 3059047 B1 FR3059047 B1 FR 3059047B1 FR 1661318 A FR1661318 A FR 1661318A FR 1661318 A FR1661318 A FR 1661318A FR 3059047 B1 FR3059047 B1 FR 3059047B1
Authority
FR
France
Prior art keywords
turbomachine
combustion chamber
manufacturing process
chamber injector
nozzle
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
FR1661318A
Other languages
French (fr)
Other versions
FR3059047A1 (en
Inventor
Denis Luc Alain Chanteloup
Stephane Ramond
Christophe Lailhacar
Jean-Paul Autret
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 Helicopter Engines SAS
Original Assignee
Safran Helicopter 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 Helicopter Engines SAS filed Critical Safran Helicopter Engines SAS
Priority to FR1661318A priority Critical patent/FR3059047B1/en
Publication of FR3059047A1 publication Critical patent/FR3059047A1/en
Application granted granted Critical
Publication of FR3059047B1 publication Critical patent/FR3059047B1/en
Active legal-status Critical Current
Anticipated expiration legal-status Critical

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/36—Details, e.g. burner cooling means, noise reduction means
    • F23D11/38—Nozzles; Cleaning devices therefor
    • 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
    • F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • 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
    • F23R2900/00018—Manufacturing combustion chamber liners or subparts

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Fuel-Injection Apparatus (AREA)

Abstract

Injecteur (1') de chambre de combustion pour une turbomachine, en particulier d'aéronef, comportant un corps (11') comprenant au moins un circuit (C1') d'injection de carburant qui comporte un conduit interne (12a') dont une extrémité aval débouche (12aa') à une première extrémité du corps et est reliée à au moins un orifice (50') d'éjection de carburant, et une extrémité amont (12ab') débouche à une seconde extrémité du corps et est reliée à un gicleur (8'), ledit gicleur définissant une restriction calibrante de section de passage dans ledit conduit, caractérisé en ce que ledit gicleur est formé d'une seule pièce avec ledit corps.Combustion chamber injector (1 ') for a turbomachine, in particular an aircraft, comprising a body (11') comprising at least one fuel injection circuit (C1 ') which comprises an internal duct (12a') of which a downstream end opens (12aa ') at a first end of the body and is connected to at least one fuel ejection orifice (50'), and an upstream end (12ab ') opens to a second end of the body and is connected to a nozzle (8 '), said nozzle defining a calibrating restriction of passage section in said duct, characterized in that said nozzle is formed integrally with said body.

FR1661318A 2016-11-21 2016-11-21 COMBUSTION CHAMBER INJECTOR FOR A TURBOMACHINE AND ITS MANUFACTURING PROCESS Active FR3059047B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1661318A FR3059047B1 (en) 2016-11-21 2016-11-21 COMBUSTION CHAMBER INJECTOR FOR A TURBOMACHINE AND ITS MANUFACTURING PROCESS

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1661318 2016-11-21
FR1661318A FR3059047B1 (en) 2016-11-21 2016-11-21 COMBUSTION CHAMBER INJECTOR FOR A TURBOMACHINE AND ITS MANUFACTURING PROCESS

Publications (2)

Publication Number Publication Date
FR3059047A1 FR3059047A1 (en) 2018-05-25
FR3059047B1 true FR3059047B1 (en) 2020-08-28

Family

ID=58314385

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1661318A Active FR3059047B1 (en) 2016-11-21 2016-11-21 COMBUSTION CHAMBER INJECTOR FOR A TURBOMACHINE AND ITS MANUFACTURING PROCESS

Country Status (1)

Country Link
FR (1) FR3059047B1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3099231B1 (en) * 2019-07-24 2022-08-12 Safran Helicopter Engines PURGE CIRCUIT FUEL INJECTOR FOR AN AIRCRAFT TURBOMACHINE
FR3107564B1 (en) * 2020-02-24 2022-12-02 Safran Helicopter Engines Turbomachine Combustion Assembly

Family Cites Families (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE175129C (en) *
US2453378A (en) * 1941-11-07 1948-11-09 Asiatic Petroleum Co Ltd Liquid-cooled nozzle arrangement for combustion chambers of jet propulsion apparatus
US3904119A (en) * 1973-12-05 1975-09-09 Avco Corp Air-fuel spray nozzle
US20120047902A1 (en) * 2008-10-15 2012-03-01 Tuthill Richard S Fuel delivery system for a turbine engine
US8375548B2 (en) * 2009-10-07 2013-02-19 Pratt & Whitney Canada Corp. Fuel nozzle and method of repair
FR2971039B1 (en) * 2011-02-02 2013-01-11 Turbomeca GAS TURBINE FUEL COMBUSTION CHAMBER INJECTOR WITH DOUBLE FUEL CIRCUIT AND COMBUSTION CHAMBER EQUIPPED WITH AT LEAST ONE SUCH INJECTOR
US9383097B2 (en) * 2011-03-10 2016-07-05 Rolls-Royce Plc Systems and method for cooling a staged airblast fuel injector
FR2998497B1 (en) * 2012-11-29 2021-01-29 Association Pour La Rech Et Le Developpement De Methodes Et Processus Industriels Armines PROCESS FOR SELECTIVE MERGING OF BEDS OF POWDER BY HIGH ENERGY BEAM UNDER A GAS DEPRESSION
GB2516445A (en) * 2013-07-22 2015-01-28 Rolls Royce Plc A fuel spray nozzle
US20150285502A1 (en) * 2014-04-08 2015-10-08 General Electric Company Fuel nozzle shroud and method of manufacturing the shroud
JP6301774B2 (en) * 2014-08-01 2018-03-28 三菱日立パワーシステムズ株式会社 Gas turbine combustor

Also Published As

Publication number Publication date
FR3059047A1 (en) 2018-05-25

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