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1. WO2016024007 - GAS TURBINE SYSTEM

Publication Number WO/2016/024007
Publication Date 18.02.2016
International Application No. PCT/EP2015/068720
International Filing Date 14.08.2015
Chapter 2 Demand Filed 09.12.2015
IPC
F23R 3/00 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
F01D 9/02 2006.01
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
9Stators
02Nozzles; Nozzle boxes; Stator blades; Guide conduits
CPC
F01D 25/12
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
08Cooling
12Cooling
F01D 9/023
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
9Stators
02Nozzles; Nozzle boxes; Stator blades; Guide conduits ; , e.g. individual nozzles
023Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings
F02C 7/18
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
12Cooling of plants
16characterised by cooling medium
18the medium being gaseous, e.g. air
F05D 2260/202
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
2260Function
20Heat transfer, e.g. cooling
202by film cooling
F05D 2260/204
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
2260Function
20Heat transfer, e.g. cooling
204by the use of microcircuits
F23R 2900/00017
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
00017Assembling combustion chamber liners or subparts
Applicants
  • SIEMENS AKTIENGESELLSCHAFT [DE]/[DE]
Inventors
  • HASE, Matthias
  • KRISHNAN, Vaidyanathan
  • SANDERS, Paul A.
Priority Data
14/460,87815.08.2014US
Publication Language English (EN)
Filing Language English (EN)
Designated States
Title
(EN) GAS TURBINE SYSTEM
(FR) SYSTÈME DE TURBINE À GAZ
Abstract
(EN)
The present invention relates to a gas turbine system comprising a burner arrangement having a tubular combustion chamber, a turbine and a transition duct (7) connecting the combustion chamber and the turbine, wherein the transition duct (7) is provided with an axially extending cooling air channel (11), wherein the transition duct (7) is provided with a plurality of axially extending cooling air channels (11), and wherein largely each cooling air channel (11) is provided with one single inlet opened to the outside of the transition duct (7) and with one single outlet opened to the inside of the transition duct (7).
(FR)
L'invention concerne un système de turbine à gaz comprenant un agencement de brûleur pourvu d'une chambre de combustion tubulaire, une turbine et un conduit de transition (7) reliant la chambre de combustion et la turbine, le conduit de transition (7) s'étendant axialement comprenant une pluralité de canaux d'air de refroidissement (11) s'étendant axialement, chaque canal d'air de refroidissement (11) étant pourvu d'un orifice d'entrée unique débouchant sur l'extérieur du conduit de transition (7) et d'un orifice de sortie unique débouchant sur l'intérieur du conduit de transition (7).
Also published as
IR139550140003008870
SA517380856
Latest bibliographic data on file with the International Bureau