Processing

Please wait...

Settings

Settings

Goto Application

1. WO2020071399 - ANNULAR GAS TURBINE COMBUSTOR FOR AIRPLANES

Publication Number WO/2020/071399
Publication Date 09.04.2020
International Application No. PCT/JP2019/038850
International Filing Date 02.10.2019
IPC
F23R 3/16 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
02characterised by the air-flow or gas-flow configuration
16with devices inside the flame tube or the combustion chamber to influence the air or gas flow
F02C 7/24 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
24Heat or noise insulation
F23R 3/14 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
02characterised by the air-flow or gas-flow configuration
04Air inlet arrangements
10for primary air
12inducing a vortex
14by using swirl vanes
F23R 3/28 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
CPC
F02C 7/24
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, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
24Heat or noise insulation
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 3/16
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
16with devices inside the flame tube or the combustion chamber to influence the air or gas flow
F23R 3/28
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
Applicants
  • 川崎重工業株式会社 KAWASAKI JUKOGYO KABUSHIKI KAISHA [JP]/[JP]
  • 国立研究開発法人宇宙航空研究開発機構 JAPAN AEROSPACE EXPLORATION AGENCY [JP]/[JP]
Inventors
  • 松山 竜佐 MATSUYAMA, Ryusuke
  • 吉田 征二 YOSHIDA, Seiji
  • 藤原 仁志 FUJIWARA, Hitoshi
Agents
  • 特許業務法人 有古特許事務所 PATENT CORPORATE BODY ARCO PATENT OFFICE
Priority Data
2018-18751402.10.2018JP
Publication Language Japanese (JA)
Filing Language Japanese (JA)
Designated States
Title
(EN) ANNULAR GAS TURBINE COMBUSTOR FOR AIRPLANES
(FR) CHAMBRE DE COMBUSTION DE TURBINE À GAZ ANNULAIRE POUR AVIONS
(JA) 航空機用のアニュラ型ガスタービン燃焼器
Abstract
(EN)
An annular gas turbine combustor for airplanes comprising a plurality of resonators that have resonance chambers and that are disposed in a fuel injection device installation space side-by-side with a fuel injection device in the radial direction of the fuel injection device. A bulkhead that separates a combustion chamber and the fuel injection device installation space has a plurality of openings disposed between the combustion chamber and the resonance chambers of the plurality of resonators. The resonance chambers communicate with the combustion chamber by way of the openings. At least some of the resonance chambers are disposed more radially inward, as seen from the axial direction of the fuel injection device, than the maximum outer diameter section of an outer liner.
(FR)
L'invention concerne une chambre de combustion de turbine à gaz annulaire pour avions, comprenant plusieurs résonateurs qui ont des chambres de résonance et qui sont disposés dans un espace d'installation de dispositif d'injection de carburant côte à côte avec un dispositif d'injection de carburant dans la direction radiale du dispositif d'injection de carburant. Une cloison qui sépare une chambre de combustion et l'espace d'installation de dispositif d'injection de carburant comporte plusieurs ouvertures disposées entre la chambre de combustion et les chambres de résonance des multiples résonateurs. Les chambres de résonance communiquent avec la chambre de combustion par l'intermédiaire des ouvertures. Au moins certaines des chambres de résonance sont disposées plus radialement vers l'intérieur, comme cela est vu depuis la direction axiale du dispositif d'injection de carburant, par rapport à la section de diamètre externe maximum d'une chemise externe.
(JA)
航空機用のアニュラ型ガスタービン燃焼器は、燃料噴射装置配置空間において燃料噴射装置の径方向に前記燃料噴射装置と並んで配置され、共振室を有する複数のレゾネータを備える。前記燃焼室と前記燃料噴射装置配置空間とを区分けするバルクヘッドは、前記複数のレゾネータの前記共振室と前記燃焼室との間に配置された複数の開口を有する。前記共振室は、前記開口により前記燃焼室に連通している。前記共振室の少なくとも一部は、前記燃料噴射装置の軸線方向から見て前記アウターライナの最大外径部よりも径方向内側に配置されている。
Also published as
Latest bibliographic data on file with the International Bureau