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1. WO2020136359 - INJECTOR NOZZLE FOR TURBOMACHINE COMPRISING A PRIMARY FUEL CIRCUIT ARRANGED AROUND A SECONDARY FUEL CIRCUIT

Publication Number WO/2020/136359
Publication Date 02.07.2020
International Application No. PCT/FR2019/053302
International Filing Date 26.12.2019
IPC
F23R 3/28 2006.1
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3Continuous combustion chambers using liquid or gaseous fuel
28characterised by the fuel supply
F23R 3/34 2006.1
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3Continuous combustion chambers using liquid or gaseous fuel
28characterised by the fuel supply
34Feeding into different combustion zones
CPC
F23D 2900/00016
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
DBURNERS
2900Special features of, or arrangements for burners using fluid fuels or solid fuels suspended in a carrier gas
00016Preventing or reducing deposit build-up on burner parts, e.g. from carbon
F23R 2900/00004
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
2900Special features of, or arrangements for continuous combustion chambers; Combustion processes therefor
00004Preventing formation of deposits on surfaces of gas turbine components, e.g. coke deposits
F23R 3/283
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3Continuous combustion chambers using liquid or gaseous fuel
28characterised by the fuel supply
283Attaching or cooling of fuel injecting means including supports for fuel injectors, stems, or lances
F23R 3/343
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
3Continuous combustion chambers using liquid or gaseous fuel
28characterised by the fuel supply
34Feeding into different combustion zones
343Pilot flames, i.e. fuel nozzles or injectors using only a very small proportion of the total fuel to insure continuous combustion
Applicants
  • SAFRAN AIRCRAFT ENGINES [FR]/[FR]
Inventors
  • CHABAILLE, Christophe
  • BERNARD, Clément, Yves, Emile
  • LOVAL, Sébastien, Christophe
Agents
  • AHNER, Philippe
Priority Data
187426127.12.2018FR
Publication Language French (FR)
Filing Language French (FR)
Designated States
Title
(EN) INJECTOR NOZZLE FOR TURBOMACHINE COMPRISING A PRIMARY FUEL CIRCUIT ARRANGED AROUND A SECONDARY FUEL CIRCUIT
(FR) NEZ D'INJECTEUR POUR TURBOMACHINE COMPRENANT UN CIRCUIT PRIMAIRE DE CARBURANT AGENCÉ AUTOUR D'UN CIRCUIT SECONDAIRE DE CARBURANT
Abstract
(EN)
An injector nozzle (43) for a turbomachine comprises a primary fuel circuit ending in a fuel ejection pipe (66), and a secondary fuel circuit comprising an annular end portion for ejecting fuel (68) arranged around the fuel ejection pipe. A portion upstream from the primary fuel circuit comprises an annular channel (70), which extends around the secondary fuel circuit and is defined by an external wall (72) of the injector nozzle. The injector nozzle comprises air intake channels (126) extending through the annular channel (70) and having inlets opening into the external wall (72) and outlets (130) opening into an annular air injection channel (124) arranged radially in the interior in relation to the end portion for ejecting fuel, around the fuel ejection pipe, and cooperating with the end portion for ejecting fuel in order to form an aerodynamic secondary injector.
(FR)
Un nez d'injecteur (43) pour turbomachine comprend un circuit primaire de carburant terminé par une buse d'éjection de carburant (66), et un circuit secondaire de carburant comportant une partie terminale d'éjection de carburant (68) annulaire agencée autour de la buse d'éjection de carburant. Une partie amont du circuit primaire de carburant comporte un canal annulaire (70) s'étendant autour du circuit secondaire de carburant et délimité par une paroi externe (72) du nez d'injecteur.Le nez d'injecteur comporte des canaux d'entrée d'air (126) s'étendant au travers du canal annulaire (70) et présentant des entrées s'ouvrant dans la paroi externe (72) et des sorties (130) débouchant dans un canal annulaire d'injection d'air (124) agencé radialement à l'intérieur par rapport à la partie terminale d'éjection de carburant, autour de la buse d'éjection de carburant, et coopérant avec la partie terminale d'éjection de carburant pour former un injecteur secondaire aérodynamique.
Also published as
EP2019848993
Latest bibliographic data on file with the International Bureau