| 摘要 |
<p>The invention concerns an aerodynamic system for injecting an air-fuel mixture into the combustion furnace (2) of a gas turbine engine. The fuel injector (43) is a two flow rate injector and delivers a secondary fuel cone (53) beyond a predetermined capacity. A primary twist (32) and a secondary twist (33) are associated with a venturi (30) upstream of an aerodynamic bowl (20) mounted in the chamber base (3). The primary fuel cone (51) does not strike the venturi (30).</p> |
