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1. WO2022043079 - COMBUSTOR FOR A GAS TURBINE

Publication Number WO/2022/043079
Publication Date 03.03.2022
International Application No. PCT/EP2021/072492
International Filing Date 12.08.2021
IPC
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
F23R 3/36 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
36Supply of different fuels
F23R 3/14 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
02characterised by the air-flow or gas-flow configuration
04Air inlet arrangements
10for primary air
12inducing a vortex
14by using swirl vanes
CPC
F23R 2900/03343
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
03343Pilot burners operating in premixed mode
F23R 3/14
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
02characterised by the air-flow or gas-flow configuration
04Air inlet arrangements
10for primary air
12inducing a vortex
14by using swirl vanes
F23R 3/346
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
346for staged combustion
F23R 3/36
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
36Supply of different fuels
Applicants
  • SIEMENS ENERGY GLOBAL GMBH & CO. KG [DE]/[DE]
Inventors
  • SADASIVUNI, Suresh
Agents
  • ROTH, Thomas
Priority Data
2013274.225.08.2020GB
Publication Language English (en)
Filing Language English (EN)
Designated States
Title
(EN) COMBUSTOR FOR A GAS TURBINE
(FR) DISPOSITIF DE COMBUSTION POUR TURBINE À GAZ
Abstract
(EN) A combustor (36) for a gas turbine, the combustor (36) comprising a combustor axis (44) about which is arranged in flow sequence a radial swirler (40), a pre-chamber (42) and a combustion chamber (38). The radial swirler (40) comprises a base plate (45), an annular array of swirler vanes (46), defining swirler slots (47), arranged around the base plate (45), a main fuel injector (48A, 48B) for injecting a main fuel and a pilot fuel injector (50) for injecting a pilot fuel. The combustor comprises a premixer nozzle (70) located on the combustion chamber (38). The premixer nozzle (70) comprising a housing (78), an array of tubes (80) within the housing (78) and a first fuel gallery (72) for supplying a first fuel (83). Each tube (80) of the array of tubes (80) comprising an inlet (86), an outlet (88), a first aperture (90) and a second aperture (92). The first fuel gallery (72) is arranged to supply the first fuel (83) to the first aperture (90) and / or the second aperture (92). In use, air (34) is supplied to the combustor and a first portion of the air (34A) passes through the radial swirler (40) and a second portion of the air (34B) passes through the tubes (80) of the array of tubes (80) from inlet (86) to outlet (88) and mixes with the first fuel (83) that passes through the first aperture (90) and / or the second aperture (92).
(FR) La présente invention concerne un dispositif de combustion (36) pour une turbine à gaz, le dispositif de combustion (36) comprenant un axe de dispositif de combustion (44) autour duquel sont disposés dans l'ordre d'écoulement une coupelle de turbulence radiale (40), une pré-chambre (42) et une chambre de combustion (38). La coupelle de turbulence radiale (40) comprend une plaque de base (45), un réseau annulaire d'aubes de coupelle de turbulence (46), définissant des fentes de coupelle de turbulence (47), disposées autour de la plaque de base (45), un injecteur de carburant principal (48A, 48B) pour injecter un carburant principal et un injecteur de carburant pilote (50) pour injecter un carburant pilote. La chambre de combustion comprend une buse de pré-mélangeur (70) située sur la chambre de combustion (38). La buse de pré-mélangeur (70) comprend un boîtier (78), un réseau de tubes (80) à l'intérieur du boîtier (78) et une première rampe de carburant (72) pour fournir un premier carburant (83). Chaque tube (80) du réseau de tubes (80) comprend une entrée (86), une sortie (88), une première ouverture (90) et une seconde ouverture (92). La première rampe de carburant (72) est agencée pour fournir le premier carburant (83) à la première ouverture (90) et/ou à la seconde ouverture (92). En utilisation, de l'air (34) est fourni à la chambre de combustion et une première partie de l'air (34A) passe à travers la coupelle de turbulence radiale (40) et une seconde partie de l'air (34B) passe à travers les tubes (80) du réseau de tubes (80) de l'entrée (86) à la sortie (88) et se mélange avec le premier carburant (83) qui passe à travers la première ouverture (90) et/ou la seconde ouverture (92).
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