Processing

Please wait...

Settings

Settings

Goto Application

1. WO2013165868 - GAS TURBINE ENGINE COMBUSTOR SURGE RETENTION

Publication Number WO/2013/165868
Publication Date 07.11.2013
International Application No. PCT/US2013/038572
International Filing Date 29.04.2013
IPC
F02C 3/14 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
14characterised by the arrangement of the combustion chamber in the plant
F02C 7/00 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
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
F23R 3/42 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
42characterised by the arrangement or form of the flame tubes or combustion chambers
F02K 3/00 2006.1
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
KJET-PROPULSION PLANTS
3Plants including a gas turbine driving a compressor or a ducted fan
CPC
F01D 25/24
FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
01MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
DNON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
25Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
24Casings
F02C 7/20
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
20Mounting or supporting of plant; Accommodating heat expansion or creep
F23R 2900/00005
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
00005Preventing fatigue failures or reducing mechanical stress in gas turbine components
F23R 3/002
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
002Wall structures
F23R 3/50
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
42characterised by the arrangement or form of the flame tubes or combustion chambers
50Combustion chambers comprising an annular flame tube within an annular casing
F23R 3/60
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
42characterised by the arrangement or form of the flame tubes or combustion chambers
60Support structures; Attaching or mounting means
Applicants
  • UNITED TECHNOLOGIES CORPORATION [US]/[US]
Inventors
  • EASTWOOD, Jonathan Jeffery
  • LOW, Kevin Joseph
Agents
  • KOZIARZ, Matthew L.
Priority Data
13/460,99801.05.2012US
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) GAS TURBINE ENGINE COMBUSTOR SURGE RETENTION
(FR) PRÉVENTION DE POMPAGE DE CHAMBRE DE COMBUSTION DE MOTEUR À TURBINE À GAZ
Abstract
(EN)
A combustor assembly for a gas turbine engine includes a static structure and an annular combustor extending around a central axis and located radially inwards of the static structure. The annular combustor includes an annular outer shell and an annular inner shell that define an annular combustion chamber there between. The annular combustor is free of any rigid attachments directly between the static structure and the annular outer shell. The annular outer shell includes a radially-outwardly extending flange. A stop member is rigidly connected with the static structure and is located adjacent the radially-outwardly extending flange such that axial-forward movement of the annular combustor is limited.
(FR)
L'invention porte sur un ensemble chambre de combustion pour un moteur à turbine à gaz qui comprend une structure fixe et une chambre de combustion annulaire s'étendant autour d'un axe central et placé radialement vers l'intérieur de la structure fixe. La chambre de combustion annulaire comprend une coque extérieure annulaire et une coque intérieure annulaire qui définissent entre celles-ci une chambre de combustion annulaire. La chambre de combustion annulaire ne comporte pas de fixations rigides directement entre la structure fixe et la coque extérieure annulaire. La coque extérieure annulaire comprend une bride s'étendant radialement vers l'extérieur. Un élément de butée est relié rigidement à la structure fixe et est placé adjacent à la bride s'étendant radialement vers l'extérieur, de sorte que le mouvement d'avancée axiale de la chambre de combustion annulaire est limité.
Related patent documents
Latest bibliographic data on file with the International Bureau