# US 2014/0150442 A1 · Gas turbine centripetal annular combustion chamber and method for flow guidance > Agents: this data is available as JSON from the patentgrep API and MCP server — see https://patentgrep.com/llms.txt - Number: US 2014/0150442 A1 - Document ID: US20140150442A1 - Status: Published application - Kind: A1 - Application number: 14/232,814 - Filed: 2012-06-14 - Published: 2014-06-05 - Earliest claimed: 2011-07-28 - Assignees: Rolls-Royce Deutschland Ltd & Co KG - Inventors: Dimitrie Negulescu - Web page: https://patentgrep.com/patent/US20140150442A1 ## CPC - F23R 3/10: for primary air (F23R3/06, F23R3/045 take precedence) - F02C 3/08: the compressor comprising at least one radial stage (F02C3/10 takes precedence) - F02C 3/14: characterised by the arrangement of the combustion chamber in the plant (combustion chambers per se F23R; F02C3/205 takes precedence) - F23R 3/52: Toroidal combustion chambers - F05D 2240/36: Fuel vaporizer - F05D 2250/314: the axes being inclined in relation to each other - Y02T 50/60: Efficient propulsion technologies, e.g. for aircraft - F23R: GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS (fluidised bed combustion apparatus specially adapted for operation at superatmospheric pressures F23C10/16) - F02C: GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines F01D; jet-propulsion plants F02K; construction of compressors or fans F04; generating combustion products of high pressure or high velocity F23R; using gas turbines in compression refrigeration plants F25B11/00) - F05D: INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS - Y02T: CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION ## Abstract A gas-turbine combustion chamber arrangement includes at least one centrifugal compressor as well as one centripetal annular combustion chamber, with a stator vane arrangement being provided between the centrifugal compressor and the annular combustion chamber. The stator vane arrangement for diverting the air flowing out of the centrifugal compressor is designed at an angle α of 20° to 30°, preferably 25°, relative to the engine axis, so the airflow is passed at essentially this angle α to the combustion chamber. The inflow area into the combustion chamber for supplying air is designed at an angle of 20° to 30°, preferably 25°, relative to the meridional plane, and the center axes of the burners or of the injection nozzles of the combustion chamber are arranged inclined at an angle β of 30° to 40°, preferably 35°, relative to a meridional plane passing through the engine axis. ## Claims ### Claim 1 Gas-turbine combustion chamber arrangement with at least one centrifugal compressor as well as one centripetal annular combustion chamber, with a stator vane arrangement being provided between the centrifugal compressor and the annular combustion chamber, characterized in that the stator vane arrangement for diverting the air flowing out of the centrifugal compressor is designed at an angle (α) of 20° to 30°, preferably 25°, relative to the engine axis, that the airflow is passed at essentially this angle (α) to the combustion chamber, that the inflow area into the combustion chamber for supplying air is designed at an angle of 20° to 30°, preferably 25°, relative to the meridional plane, and that the center axes of the burners or of the injection nozzles of the combustion chamber are arranged inclined at an angle (β) of 30° to 40°, preferably 35°, relative to a meridional plane passing through the engine axis. ### Claim 2 (depends on 1) Gas-turbine combustion chamber arrangement in accordance with claim 1, characterized in that the heat shields of the burners and/or the injection nozzles are arranged inclined at an angle (β) of 30° to 40°, preferably 35°, relative to a meridional plane passing through the engine axis. ### Claim 3 (depends on 1) Gas-turbine combustion chamber arrangement in accordance with claim 1, characterized in that the burners are designed for applying an initial swirl onto the flames of the burner, which is between 30° and 40°, preferably 35°, relative to the meridional plane. ### Claim 4 (depends on 3) Gas-turbine combustion chamber arrangement in accordance with claim 3, characterized in that the burners are designed for generating a swirl flow onto the flames of the burner in the axial outlet of the centripetal flame tube at the inlet area to a turbine stator vane ring of 50° to 60°, preferably 55°, relative to the meridional plane. ### Claim 5 (depends on 1) Gas-turbine combustion chamber arrangement in accordance with claim 1, characterized in that the annular combustion chamber is designed to form a helical flame in the centripetal flame tube. ### Claim 6 (depends on 1) Gas-turbine combustion chamber arrangement in accordance with claim 1, characterized in that an array of recesses for introducing air from the centrifugal compressor is designed to form a helical flame in the centripetal flame tube. ### Claim 7 Method for flow guidance in a centrifugal compressor and a centripetal annular combustion chamber of a gas-turbine, where a flow exiting the centrifugal compressor is aligned at an angle (α) of 20° to 30°, preferably to 25°, relative to the engine axis, where the flow is supplied to the annular combustion chamber at an angle (α), where the flow in the inflow area into the annular combustion chamber is aligned at an angle of 30° to 40°, preferably 35°, relative to the meridional plane, and where the flow exiting the annular combustion chamber is aligned at an angle of 50° to 60°, preferably 55°, relative to a meridional plane including the engine axis. ### Claim 8 (depends on 7) Method in accordance with claim 7, characterized in that the flow diversion in the combustion chamber is approx. 175°.