Annular combustion chamber of a gas turbine
AssigneeRolls-Royce Deutschland Ltd & Co KG
InventorCarsten Clemen
Life of this patent
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Abstract
The present invention relates to an annular combustion chamber of a gas turbine with—relative to the engine axis—a radially outer combustion chamber wall and a radially inner combustion chamber wall, with the combustion chamber walls forming an annular combustion space, with a combustion chamber head having a plurality of fuel nozzles and air inlet openings, with the respective central axes of the fuel nozzles forming an envelope rotationally symmetrical to the engine axis, the envelope dividing the combustion chamber into an annular and radially outer area and an annular and radially inner area, with the radially outer area and the radially inner area having the same volumes.
Claims3
An annular combustion chamber of a gas turbine, comprising:
- a radially outer combustion chamber wall relative to an engine axis;
- a radially inner combustion chamber wall;
- an annular combustion space formed between the radially inner and outer combustion chamber walls;
- a combustion chamber head including a plurality of fuel nozzles and air inlet openings, with respective central axes of the fuel nozzles forming an envelope rotationally symmetrical to the engine axis, the envelope dividing the combustion chamber into an annular radially outer region and an annular radially inner region, with the annular radially outer region and the annular radially inner region being equal in volume;
- wherein, at each position along envelop in an axial direction of the gas turbine, a respective conical section around the combustion chamber is defined, with the respective conical section being centered on the engine axis and perpendicular to each of the central axes of the fuel nozzles, with the annular radially outer region and the annular radially inner region being equal in area in each respective conical section.
Dependencies are inferred from the claim text.