FR3116592B1 - Vrille pour dispositif d’injection étagé de turbomachine - Google Patents

Vrille pour dispositif d’injection étagé de turbomachine Download PDF

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Publication number
FR3116592B1
FR3116592B1 FR2012223A FR2012223A FR3116592B1 FR 3116592 B1 FR3116592 B1 FR 3116592B1 FR 2012223 A FR2012223 A FR 2012223A FR 2012223 A FR2012223 A FR 2012223A FR 3116592 B1 FR3116592 B1 FR 3116592B1
Authority
FR
France
Prior art keywords
channel
blade
inter
injection device
auger
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
FR2012223A
Other languages
English (en)
Other versions
FR3116592A1 (fr
Inventor
Haris Musaefendic
Sébastien Alain Christophe Bourgois
Romain Nicolas Lunel
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
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 filed Critical Safran Aircraft Engines SAS
Priority to FR2012223A priority Critical patent/FR3116592B1/fr
Publication of FR3116592A1 publication Critical patent/FR3116592A1/fr
Application granted granted Critical
Publication of FR3116592B1 publication Critical patent/FR3116592B1/fr
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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
    • F23R3/02—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
    • F23R3/286—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices
    • 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
    • F23R2900/00—Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
    • F23R2900/00014—Reducing thermo-acoustic vibrations by passive means, e.g. by Helmholtz resonators
    • 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
    • F23R2900/00016—Retrofitting in general, e.g. to respect new regulations on pollution
    • 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)
  • Nozzles (AREA)

Abstract

La présente invention concerne une vrille (10) pour un dispositif d’injection de chambre de combustion multipoint de turbomachine, la vrille s’étendant autour d’un axe longitudinal et comprenant une surface de vrille et une pluralité d’aubages (12) montés sur la surface de vrille et répartis radialement autour de l’axe longitudinal,chaque aubage (12) de la pluralité d’aubages délimitant avec la surface de vrille et avec l’aubage consécutif respectif un canal inter-aubage (14a, 14b), ledit canal inter-aubage (14a, 14b) s’étendant radialement vers l’intérieur depuis une extrémité d’entrée (15a, 15b) dudit canal jusqu’à une extrémité de sortie (16a, 16b) dudit canal,une première section de passage de l’extrémité de sortie (16b) d’un premier canal inter-aubage (14b) présentant une surface plus réduite qu’une deuxième section de passage de l’extrémité de sortie (16a) d’un deuxième canal inter-aubage (14a). Figure pour l’abrégé : Figure 2
FR2012223A 2020-11-26 2020-11-26 Vrille pour dispositif d’injection étagé de turbomachine Active FR3116592B1 (fr)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2012223A FR3116592B1 (fr) 2020-11-26 2020-11-26 Vrille pour dispositif d’injection étagé de turbomachine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2012223 2020-11-26
FR2012223A FR3116592B1 (fr) 2020-11-26 2020-11-26 Vrille pour dispositif d’injection étagé de turbomachine

Publications (2)

Publication Number Publication Date
FR3116592A1 FR3116592A1 (fr) 2022-05-27
FR3116592B1 true FR3116592B1 (fr) 2023-06-16

Family

ID=74860053

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2012223A Active FR3116592B1 (fr) 2020-11-26 2020-11-26 Vrille pour dispositif d’injection étagé de turbomachine

Country Status (1)

Country Link
FR (1) FR3116592B1 (fr)

Families Citing this family (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN116202105B (zh) * 2023-02-27 2024-05-03 中国航发四川燃气涡轮研究院 一种优化燃烧性能的旋流燃烧室头部结构

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE4228817C2 (de) * 1992-08-29 1998-07-30 Mtu Muenchen Gmbh Brennkammer für Gasturbinentriebwerke
US7581396B2 (en) * 2005-07-25 2009-09-01 General Electric Company Mixer assembly for combustor of a gas turbine engine having a plurality of counter-rotating swirlers
US7716931B2 (en) * 2006-03-01 2010-05-18 General Electric Company Method and apparatus for assembling gas turbine engine
FR2957659B1 (fr) * 2010-03-22 2012-07-20 Snecma Systeme d'injection pour chambre de combustion de turbomachine, comprenant des moyens d'injection de carburant en sortie d'une double vrille d'admission d'air
FR2996287B1 (fr) 2012-09-28 2018-03-02 Safran Aircraft Engines Dispositif d'injection pour une chambre de combustion de turbomachine

Also Published As

Publication number Publication date
FR3116592A1 (fr) 2022-05-27

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