FR3009747B1 - Chambre de combustion de turbomachine pourvue d'un passage d'entree d'air ameliore en aval d'un orifice de passage de bougie - Google Patents

Chambre de combustion de turbomachine pourvue d'un passage d'entree d'air ameliore en aval d'un orifice de passage de bougie

Info

Publication number
FR3009747B1
FR3009747B1 FR1358050A FR1358050A FR3009747B1 FR 3009747 B1 FR3009747 B1 FR 3009747B1 FR 1358050 A FR1358050 A FR 1358050A FR 1358050 A FR1358050 A FR 1358050A FR 3009747 B1 FR3009747 B1 FR 3009747B1
Authority
FR
France
Prior art keywords
candle
combustion chamber
air input
improved air
passing down
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
FR1358050A
Other languages
English (en)
Other versions
FR3009747A1 (fr
Inventor
Jean-Francois Cabre
Emeric D'herbigny
Sylvain Oblaza
Christophe Pieussergue
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 FR1358050A priority Critical patent/FR3009747B1/fr
Publication of FR3009747A1 publication Critical patent/FR3009747A1/fr
Application granted granted Critical
Publication of FR3009747B1 publication Critical patent/FR3009747B1/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
    • 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
    • F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
    • F02C7/26—Starting; Ignition
    • F02C7/264—Ignition
    • F02C7/266—Electric
    • 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
    • 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
    • F23R2900/03042—Film cooled combustion chamber walls or domes
    • 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

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
FR1358050A 2013-08-19 2013-08-19 Chambre de combustion de turbomachine pourvue d'un passage d'entree d'air ameliore en aval d'un orifice de passage de bougie Active FR3009747B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1358050A FR3009747B1 (fr) 2013-08-19 2013-08-19 Chambre de combustion de turbomachine pourvue d'un passage d'entree d'air ameliore en aval d'un orifice de passage de bougie

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
FR1358050A FR3009747B1 (fr) 2013-08-19 2013-08-19 Chambre de combustion de turbomachine pourvue d'un passage d'entree d'air ameliore en aval d'un orifice de passage de bougie

Publications (2)

Publication Number Publication Date
FR3009747A1 FR3009747A1 (fr) 2015-02-20
FR3009747B1 true FR3009747B1 (fr) 2018-06-15

Family

ID=49484306

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1358050A Active FR3009747B1 (fr) 2013-08-19 2013-08-19 Chambre de combustion de turbomachine pourvue d'un passage d'entree d'air ameliore en aval d'un orifice de passage de bougie

Country Status (1)

Country Link
FR (1) FR3009747B1 (fr)

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR3033028B1 (fr) * 2015-02-25 2019-12-27 Safran Helicopter Engines Chambre de combustion de turbomachine comportant une piece penetrante avec ouverture
FR3055950B1 (fr) * 2016-09-14 2019-09-27 Safran Helicopter Engines Chambre de combustion pour turbomachine comprenant des moyens pour ameliorer le refroidissement d'une paroi annulaire dans le sillage d'un obstacle
FR3081211B1 (fr) 2018-05-16 2021-02-26 Safran Aircraft Engines Ensemble pour une chambre de combustion de turbomachine

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3581492A (en) * 1969-07-08 1971-06-01 Nasa Gas turbine combustor
FR2899315B1 (fr) * 2006-03-30 2012-09-28 Snecma Configuration d'ouvertures de dilution dans une paroi de chambre de combustion de turbomachine
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
FR2981733B1 (fr) * 2011-10-25 2013-12-27 Snecma Module de chambre de combustion de turbomachine d'aeronef et procede de conception de celui-ci

Also Published As

Publication number Publication date
FR3009747A1 (fr) 2015-02-20

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