FR3080672B1 - PRECHAMBER FOR ROTARY-FLOW RING COMBUSTION CHAMBER FOR GAS TURBINE ENGINE - Google Patents

PRECHAMBER FOR ROTARY-FLOW RING COMBUSTION CHAMBER FOR GAS TURBINE ENGINE Download PDF

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Publication number
FR3080672B1
FR3080672B1 FR1853643A FR1853643A FR3080672B1 FR 3080672 B1 FR3080672 B1 FR 3080672B1 FR 1853643 A FR1853643 A FR 1853643A FR 1853643 A FR1853643 A FR 1853643A FR 3080672 B1 FR3080672 B1 FR 3080672B1
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FR
France
Prior art keywords
chamber
combustion
gas turbine
turbine engine
combustion chamber
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
FR1853643A
Other languages
French (fr)
Other versions
FR3080672A1 (en
Inventor
Pascal Verdier Hubert
Claude Berat
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 FR1853643A priority Critical patent/FR3080672B1/en
Publication of FR3080672A1 publication Critical patent/FR3080672A1/en
Application granted granted Critical
Publication of FR3080672B1 publication Critical patent/FR3080672B1/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
    • 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
    • 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
    • F23R3/34—Feeding into different combustion zones
    • 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
    • F23R3/34—Feeding into different combustion zones
    • F23R3/343—Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
    • 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
    • F23R3/54—Reverse-flow combustion chambers
    • 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
    • F23R3/58—Cyclone or vortex type combustion chambers

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Combustion Methods Of Internal-Combustion Engines (AREA)

Abstract

L'invention concerne une chambre de combustion annulaire à écoulement giratoire pour moteur à turbine à gaz, comprenant une virole annulaire interne (4) centrée sur un axe longitudinal de chambre (X-X), une virole annulaire externe (6) disposée autour de la virole interne en lui étant coaxiale pour délimiter avec celle-ci un foyer annulaire principal de combustion (8), une pluralité de systèmes d'injection de carburant (12) espacés tangentiellement autour de l'axe longitudinal de chambre et positionnés de sorte à injecter du carburant dans le foyer principal de combustion selon une même direction tangentielle de giration (F), et au moins une préchambre de combustion (14) comprenant un foyer de combustion (16) indépendant du foyer principal de combustion qui s'ouvre à l'intérieur de celui-ci selon la direction tangentielle de giration et qui est alimenté en carburant par un injecteur de carburant (18).The invention relates to an annular combustion chamber with gyratory flow for a gas turbine engine, comprising an internal annular ferrule (4) centered on a longitudinal axis of the chamber (XX), an external annular ferrule (6) disposed around the ferrule. internal by being coaxial with it to delimit therewith a main annular combustion focus (8), a plurality of fuel injection systems (12) spaced tangentially around the longitudinal axis of the chamber and positioned so as to inject fuel in the main combustion hearth in the same tangential direction of gyration (F), and at least one combustion pre-chamber (14) comprising a combustion hearth (16) independent of the main combustion hearth which opens inside of the latter in the tangential direction of gyration and which is supplied with fuel by a fuel injector (18).

FR1853643A 2018-04-26 2018-04-26 PRECHAMBER FOR ROTARY-FLOW RING COMBUSTION CHAMBER FOR GAS TURBINE ENGINE Active FR3080672B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR1853643A FR3080672B1 (en) 2018-04-26 2018-04-26 PRECHAMBER FOR ROTARY-FLOW RING COMBUSTION CHAMBER FOR GAS TURBINE ENGINE

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR1853643 2018-04-26
FR1853643A FR3080672B1 (en) 2018-04-26 2018-04-26 PRECHAMBER FOR ROTARY-FLOW RING COMBUSTION CHAMBER FOR GAS TURBINE ENGINE

Publications (2)

Publication Number Publication Date
FR3080672A1 FR3080672A1 (en) 2019-11-01
FR3080672B1 true FR3080672B1 (en) 2020-05-08

Family

ID=62684943

Family Applications (1)

Application Number Title Priority Date Filing Date
FR1853643A Active FR3080672B1 (en) 2018-04-26 2018-04-26 PRECHAMBER FOR ROTARY-FLOW RING COMBUSTION CHAMBER FOR GAS TURBINE ENGINE

Country Status (1)

Country Link
FR (1) FR3080672B1 (en)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US11415059B2 (en) * 2020-12-23 2022-08-16 Collins Engine Nozzles, Inc. Tangentially mounted torch ignitors
US12078350B2 (en) 2022-11-10 2024-09-03 General Electric Company Gas turbine combustion section having an integrated fuel cell assembly

Family Cites Families (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5613357A (en) * 1993-07-07 1997-03-25 Mowill; R. Jan Star-shaped single stage low emission combustor system
US6955053B1 (en) * 2002-07-01 2005-10-18 Hamilton Sundstrand Corporation Pyrospin combuster
US6931862B2 (en) * 2003-04-30 2005-08-23 Hamilton Sundstrand Corporation Combustor system for an expendable gas turbine engine
US7716931B2 (en) * 2006-03-01 2010-05-18 General Electric Company Method and apparatus for assembling gas turbine engine

Also Published As

Publication number Publication date
FR3080672A1 (en) 2019-11-01

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