| 摘要 |
PROBLEM TO BE SOLVED: To provide a combustor for a micro gas turbine for achieving stable ignition performance, high combustion efficiency and low CO concentration and NOx, in a small combustion chamber using liquid fuel (e.g. kerosene) as fuel.SOLUTION: The combustor for the micro gas turbine includes: concentric and cylindrical inner liner 12 and outer liner 14 surrounding a central axis; and a burner 16 for performing fuel injection and ignition. The hollow cylindrical combustion chamber 18 is formed within the combustor for the micro gas turbine. The combustion chamber 18 includes a primary combustion chamber 18a provided on an end liner side and having a relatively small outer diameter and a secondary combustion chamber 18b positioned downstream of the primary combustion chamber 18a and having a relatively large outer diameter. The primary combustion chamber includes an ignition chamber 19a on the end liner side and a rapid dilution chamber 19b on the secondary combustion chamber side. An annular intermediate reduction part 20 narrowing the outer diameter of the primary combustion chamber is provided between the ignition chamber 19a and the rapid dilution chamber 19b. A premixing turning flow having high fuel concentration is formed within the ignition chamber and ignited, and a turning flame is rapidly diluted within the rapid dilution chamber. |
