FR2979005B1 - Systemes d'injection de carburant pour turbomachine d'aeronef a permeabilites differenciees - Google Patents

Systemes d'injection de carburant pour turbomachine d'aeronef a permeabilites differenciees

Info

Publication number
FR2979005B1
FR2979005B1 FR1157259A FR1157259A FR2979005B1 FR 2979005 B1 FR2979005 B1 FR 2979005B1 FR 1157259 A FR1157259 A FR 1157259A FR 1157259 A FR1157259 A FR 1157259A FR 2979005 B1 FR2979005 B1 FR 2979005B1
Authority
FR
France
Prior art keywords
permeabilities
differentiated
fuel injection
injection systems
aircraft turbomachine
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
FR1157259A
Other languages
English (en)
Other versions
FR2979005A1 (fr
Inventor
Sebastien Alain Christophe Bourgois
Patrice Andre Commaret
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
Priority to FR1157259A priority Critical patent/FR2979005B1/fr
Publication of FR2979005A1 publication Critical patent/FR2979005A1/fr
Application granted granted Critical
Publication of FR2979005B1 publication Critical patent/FR2979005B1/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
    • F23R3/02—Continuous combustion chambers using liquid or gaseous fuel characterised by the air-flow or gas-flow configuration
    • F23R3/04—Air inlet arrangements
    • F23R3/06—Arrangement of apertures along the flame tube
    • 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
    • F23R3/12—Air inlet arrangements for primary air inducing a vortex
    • F23R3/14—Air inlet arrangements for primary air inducing a vortex by using swirl vanes
    • 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
    • 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
    • F23R3/50—Combustion chambers comprising an annular flame tube within an annular casing
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft
FR1157259A 2011-08-09 2011-08-09 Systemes d'injection de carburant pour turbomachine d'aeronef a permeabilites differenciees Active FR2979005B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1157259A FR2979005B1 (fr) 2011-08-09 2011-08-09 Systemes d'injection de carburant pour turbomachine d'aeronef a permeabilites differenciees

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1157259A FR2979005B1 (fr) 2011-08-09 2011-08-09 Systemes d'injection de carburant pour turbomachine d'aeronef a permeabilites differenciees

Publications (2)

Publication Number Publication Date
FR2979005A1 FR2979005A1 (fr) 2013-02-15
FR2979005B1 true FR2979005B1 (fr) 2015-04-03

Family

ID=44588112

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1157259A Active FR2979005B1 (fr) 2011-08-09 2011-08-09 Systemes d'injection de carburant pour turbomachine d'aeronef a permeabilites differenciees

Country Status (1)

Country Link
FR (1) FR2979005B1 (fr)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2829228B1 (fr) * 2001-08-28 2005-07-15 Snecma Moteurs Chambre de combustion annulaire a double tete etagee
JP3990678B2 (ja) * 2004-03-17 2007-10-17 川崎重工業株式会社 ガスタービン燃焼器
JP3958767B2 (ja) * 2005-03-18 2007-08-15 川崎重工業株式会社 ガスタービン燃焼器およびその着火方法
JP5057363B2 (ja) * 2007-01-30 2012-10-24 独立行政法人 宇宙航空研究開発機構 ガスタービン燃焼器
FR2943119B1 (fr) * 2009-03-12 2011-03-25 Snecma Systemes d'injection de carburant dans une chambre de combustion de turbomachine
FR2950415B1 (fr) * 2009-09-21 2011-10-14 Snecma Chambre de combustion de turbomachine aeronautique avec trous de combustion decales ou de debits differents

Also Published As

Publication number Publication date
FR2979005A1 (fr) 2013-02-15

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