FR3105985B1 - IMPROVED INJECTOR MULTIPOINT CIRCUIT - Google Patents

IMPROVED INJECTOR MULTIPOINT CIRCUIT Download PDF

Info

Publication number
FR3105985B1
FR3105985B1 FR2000034A FR2000034A FR3105985B1 FR 3105985 B1 FR3105985 B1 FR 3105985B1 FR 2000034 A FR2000034 A FR 2000034A FR 2000034 A FR2000034 A FR 2000034A FR 3105985 B1 FR3105985 B1 FR 3105985B1
Authority
FR
France
Prior art keywords
fuel
gas
multipoint
combustion chamber
injection orifice
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
FR2000034A
Other languages
French (fr)
Other versions
FR3105985A1 (en
Inventor
Normand Kevin Didier Pierre Le
Hugo Charles Deneuville
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 FR2000034A priority Critical patent/FR3105985B1/en
Publication of FR3105985A1 publication Critical patent/FR3105985A1/en
Application granted granted Critical
Publication of FR3105985B1 publication Critical patent/FR3105985B1/en
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
    • F23R3/28—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
    • F23D—BURNERS
    • F23D11/00—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space
    • F23D11/10—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour
    • F23D11/101—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet
    • F23D11/102—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space the spraying being induced by a gaseous medium, e.g. water vapour medium and fuel meeting before the burner outlet in an internal mixing chamber
    • 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
    • F23D11/24—Burners using a direct spraying action of liquid droplets or vaporised liquid into the combustion space by pressurisation of the fuel before a nozzle through which it is sprayed by a substantial pressure reduction into a space
    • 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
    • F23D—BURNERS
    • F23D2900/00—Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
    • F23D2900/11002—Liquid fuel burners with more than one nozzle

Abstract

L’invention concerne un circuit multipoint (M) d’injecteur de carburant, en particulier pour une turbomachine d’aéronef comportant une chambre de combustion (10), ledit circuit multipoint (M) comportant au moins un orifice d’injection (20) destiné à injecter du carburant dans la chambre de combustion (10), l’au moins un orifice d’injection (20) étant alimenté en carburant par des moyens (22) d’alimentation en carburant, caractérisé en ce que l’au moins un orifice d’injection (20) est alimenté en gaz par des moyens (24) d’alimentation en gaz de manière à réaliser un mélange gaz/carburant en amont de la chambre de combustion (10) et à injecter le mélange gaz/carburant dans la chambre (10). Figure pour l'abrégé : Figure 2The invention relates to a multipoint fuel injector circuit (M), in particular for an aircraft turbomachine comprising a combustion chamber (10), said multipoint circuit (M) comprising at least one injection orifice (20) intended to inject fuel into the combustion chamber (10), the at least one injection orifice (20) being supplied with fuel by fuel supply means (22), characterized in that the at least an injection orifice (20) is supplied with gas by gas supply means (24) so as to produce a gas/fuel mixture upstream of the combustion chamber (10) and to inject the gas/fuel mixture in the room (10). Figure for abstract: Figure 2

FR2000034A 2020-01-03 2020-01-03 IMPROVED INJECTOR MULTIPOINT CIRCUIT Active FR3105985B1 (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
FR2000034A FR3105985B1 (en) 2020-01-03 2020-01-03 IMPROVED INJECTOR MULTIPOINT CIRCUIT

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
FR2000034A FR3105985B1 (en) 2020-01-03 2020-01-03 IMPROVED INJECTOR MULTIPOINT CIRCUIT
FR2000034 2020-01-03

Publications (2)

Publication Number Publication Date
FR3105985A1 FR3105985A1 (en) 2021-07-09
FR3105985B1 true FR3105985B1 (en) 2023-11-24

Family

ID=69903614

Family Applications (1)

Application Number Title Priority Date Filing Date
FR2000034A Active FR3105985B1 (en) 2020-01-03 2020-01-03 IMPROVED INJECTOR MULTIPOINT CIRCUIT

Country Status (1)

Country Link
FR (1) FR3105985B1 (en)

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE19653059A1 (en) * 1996-12-19 1998-06-25 Asea Brown Boveri Process for operating a burner
FR2875585B1 (en) * 2004-09-23 2006-12-08 Snecma Moteurs Sa AERODYNAMIC SYSTEM WITH AIR / FUEL INJECTION EFFERVESCENCE IN A TURBOMACHINE COMBUSTION CHAMBER
FR2919672B1 (en) 2007-07-30 2014-02-14 Snecma FUEL INJECTOR IN A TURBOMACHINE COMBUSTION CHAMBER
EP2434221A1 (en) * 2010-09-22 2012-03-28 Siemens Aktiengesellschaft Method and arrangement for injecting an emulsion into a flame
FR2996287B1 (en) 2012-09-28 2018-03-02 Safran Aircraft Engines INJECTION DEVICE FOR A TURBOMACHINE COMBUSTION CHAMBER
EP3133343A1 (en) * 2015-08-18 2017-02-22 General Electric Technology GmbH Gas turbine with diluted liquid fuel

Also Published As

Publication number Publication date
FR3105985A1 (en) 2021-07-09

Similar Documents

Publication Publication Date Title
US8099940B2 (en) Low cross-talk gas turbine fuel injector
US10598079B2 (en) Charge-fed pre-chamber assembly
JP2017530298A (en) Ducted fuel injection
DK1981644T3 (en) injector
WO2008097320A3 (en) Premixing injector for gas turbine engines
KR830006575A (en) Gas Turbine Combustion Method and Gas Turbine Combustor
RU2014138247A (en) GAS TURBINE WITH COMPOSITION FOR SEQUENTIAL COMBUSTION
GB2429516A (en) An apparatus/method for modifying a gaseous fuel
US9212609B2 (en) Combination air assist and pilot gaseous fuel circuit
JP2013530371A5 (en) Second water injection system for a diffusion combustion system
US10400705B2 (en) Injector assembly and method of using same
FR3105985B1 (en) IMPROVED INJECTOR MULTIPOINT CIRCUIT
CN109555626A (en) Injection nozzle and dual fuel engine for dual fuel engine
RU2008138545A (en) GAS TURBINE BURNER AND METHOD FOR OPERATING A GAS TURBINE BURNER
US10012388B2 (en) Fuel supply system for turbine engines and methods of assembling same
ES413299A1 (en) Combustion chambers for internal combustion engines equipped with a turbo-compressor unit with reheating upstream of the turbine
EP4019839A3 (en) Torch ignitors with gas assist start
JP2019505721A (en) Duct type fuel injection system and method
US20200340429A1 (en) Efficiency and emissions improvements for natural gas conversions of emd 2-cycle medium speed engines
FR3095006B1 (en) FUEL INJECTOR WITH INTEGRATED HEATER ELEMENT FOR A GAS TURBINE AND METHOD OF MANUFACTURING THEREOF
FR3101396B1 (en) Improved combustion system
DK181318B1 (en) A fuel valve for a large turbocharged two-stroke uniflow crosshead internal combustion engine
GB1126163A (en) Gas turbine by-pass engine
Burguburu et al. Enrichment 3.8 Flame Effects Stability of H and 2 on Pollutant Emissions for a Kerosene/Air Swirled Flame with an Aeronautical Injector
JP2743675B2 (en) Gas turbine combustor

Legal Events

Date Code Title Description
PLFP Fee payment

Year of fee payment: 2

PLSC Publication of the preliminary search report

Effective date: 20210709

PLFP Fee payment

Year of fee payment: 3

PLFP Fee payment

Year of fee payment: 4

PLFP Fee payment

Year of fee payment: 5