| 摘要 |
<p>The specification discloses a gas turbine engine for use with a gaseous fuel, the engine having combustion chambers of the can or can-annular type and each combustion chamber being provided with a plurality of means for the injection of fuel thereinto. A primary injection means 5 is located axially in the upstream end of the combustion chamber, and a secondary fuel injection means 8, which may comprise a single injector, is located in the sidewall of the combustion chamber. The secondary fuel injector is preferably aligned so that the fuel injected therethrough will follow a spiral path within the combustion chamber. The engine is preferably operated in such a way that the ratio of the fuel flow rates in the primary and secondary fuel injection means is in the range from 1.5:1 to 0.85:1. <IMAGE></p> |
