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1. WO2020198577 - SECOND STAGE COMBUSTION FOR IGNITER

Publication Number WO/2020/198577
Publication Date 01.10.2020
International Application No. PCT/US2020/025191
International Filing Date 27.03.2020
IPC
F23R 3/34 2006.01
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
F02C 7/264 2006.01
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
7Features, component parts, details or accessories, not provided for in, or of interest apart from, groups F02C1/-F02C6/158; Air intakes for jet-propulsion plants
26Starting; Ignition
264Ignition
CPC
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 3/286
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
286having fuel-air premixing devices
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
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
Applicants
  • DAM, Bidhan [US]/[US]
  • OONK, Logan [US]/[US]
  • HUBER, Dan [US]/[US]
  • PRASAD, Vinay [US]/[US]
  • SARKER, Sudipa [US]/[US]
Inventors
  • DAM, Bidhan
  • OONK, Logan
  • HUBER, Dan
  • PRASAD, Vinay
  • SARKER, Sudipa
Agents
  • MUSSELMAN, JR., P. Weston
  • GERHART, Robert A.
Priority Data
62/825,59128.03.2019US
62/943,66204.12.2019US
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) SECOND STAGE COMBUSTION FOR IGNITER
(FR) COMBUSTION DE SECOND ÉTAGE POUR ALLUMEUR
Abstract
(EN)
A turbine combustor (100) assembly includes a primary combustion chamber in fluid communication with a primary fuel injector (104) and a primary air inlet, and an igniter (1000) carried by the primary combustion chamber and including a first igniter stage having an auxiliary combustion chamber housing (1001) comprising a mixing chamber (1070) and a tubular throat (1008) converging downstream of the mixing chamber, an ignition source (1014) projecting into the mixing chamber of the auxiliary combustion chamber, and a second igniter stage that includes an auxiliary fuel outlet (1060) manifold proximal to an outlet of the tubular throat.
(FR)
L'invention concerne un ensemble chambre de combustion de turbine (100) comprenant une chambre de combustion primaire en communication fluidique avec un injecteur de carburant primaire (104) et une entrée d'air primaire, et un allumeur (1000) supporté par la chambre de combustion primaire et comprenant un premier étage d'allumeur ayant un boîtier de chambre de combustion auxiliaire (1001) comprenant une chambre de mélange (1070) et une gorge tubulaire (1008) convergeant en aval de la chambre de mélange, une source d'allumage (1014) faisant saillie dans la chambre de mélange de la chambre de combustion auxiliaire, et un second étage d'allumeur qui comprend un collecteur de sortie de carburant auxiliaire (1060) à proximité d'une sortie de la gorge tubulaire.
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