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1. WO2017005694 - BURNER FOR A GAS TURBINE AND METHOD FOR OPERATING THE BURNER

Publication Number WO/2017/005694
Publication Date 12.01.2017
International Application No. PCT/EP2016/065712
International Filing Date 04.07.2016
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 3/36 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
F02C 3/20 2006.1
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
3Gas-turbine plants characterised by the use of combustion products as the working fluid
20using a special fuel, oxidant, or dilution fluid to generate the combustion products
CPC
F02C 3/22
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
CGAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
3Gas-turbine plants characterised by the use of combustion products as the working fluid
20using a special fuel, oxidant, or dilution fluid to generate the combustion products
22the fuel or oxidant being gaseous at standard temperature and pressure
F05D 2220/32
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2220Application
30in turbines
32in gas turbines
F05D 2240/35
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
05INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
DINDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
2240Components
35Combustors or associated equipment
F23C 2900/9901
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  ; A CARRIER GAS OR; AIR 
2900Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
9901Combustion process using hydrogen, hydrogen peroxide water or brown gas as fuel
F23C 2900/99011
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
23COMBUSTION APPARATUS; COMBUSTION PROCESSES
CMETHODS OR APPARATUS FOR COMBUSTION USING FLUID FUEL OR SOLID FUEL SUSPENDED IN  ; A CARRIER GAS OR; AIR 
2900Special features of, or arrangements for combustion apparatus using fluid fuels or solid fuels suspended in air; Combustion processes therefor
99011Combustion process using synthetic gas as a fuel, i.e. a mixture of CO and H2
F23R 2900/00002
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
00002Gas turbine combustors adapted for fuels having low heating value [LHV]
Applicants
  • SIEMENS AKTIENGESELLSCHAFT [DE]/[DE]
Inventors
  • BULAT, Ghenadie
  • MAY, Jonathan
Agents
  • MAIER, Daniel
Priority Data
15175472.806.07.2015EP
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) BURNER FOR A GAS TURBINE AND METHOD FOR OPERATING THE BURNER
(FR) BRÛLEUR POUR TURBINE À GAZ ET PROCÉDÉ DE FONCTIONNEMENT DU BRÛLEUR
Abstract
(EN)
The invention relates to a burner for a gas turbine (10), wherein the burner (30) comprises a combustion chamber (28), a first injector (103) adapted to inject a first fuel into the combustion chamber (28) and a second injector (104) adapted to inject a second fuel being less reactive than the first fuel into the combustion chamber (28), wherein the burner (30) is adapted to premix the fuels with an air flow before the fuel enter the reaction zone (109) of the combustion chamber (28) such that a first fuel flow of the first fuel has a first premixing stream line (112) and a second fuel flow of the second fuel has a second premixing stream line (113), wherein each of the premixing stream lines begins with the beginning of the premixing with the air flow and ends at the location where the fuel enters the reaction zone (109) and the length (L2) of the second premixing stream line (113) is longer than the length (L1) of the first premixing stream line (112).
(FR)
L'invention concerne un brûleur pour turbine à gaz (10), le brûleur (30) comprenant une chambre de combustion (28), un premier injecteur (103) conçu pour injecter un premier carburant dans la chambre de combustion (28), et un second injecteur (104) conçu pour injecter un second carburant, moins réactif que le premier carburant, dans la chambre de combustion (28). Le brûleur (30) est conçu pour prémélanger les carburants avec un écoulement d'air avant que le carburant n'entre dans la zone de réaction (109) de la chambre de combustion (28), de sorte qu'un premier écoulement de carburant du premier carburant présente une première trajectoire (112) de flux de prémélange et une seconde trajectoire (113) de flux de prémélange, chacune des trajectoires de flux de prémélange commençant avec le début du prémélange avec l'écoulement d'air et se terminant au point où le carburant entre dans la zone de réaction (109) ; et la longueur (L2) de la seconde trajectoire (113) de flux de prémélange est plus longue que celle (L1) de la première trajectoire (112) de flux de prémélange.
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