| 摘要 |
A gas turbine combustion apparatus includes a cylindrical combustion liner with a dome through which primary combustion air is admitted in part. Film cooling air is admitted between the dome and the side wall to flow along the side wall and additional primary combustion air is admitted through mixing devices which mix the air with some combustion products, the resulting mixing being cooled in part by the combustion liner film cooling air. The result is to dilute oxygen at the flame and lower combustion temperatures, and therefore minimize formation of oxides of nitrogen.
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