| 摘要 |
<p>The present invention relates to a combustion chamber for a gas turbine. The combustion chamber comprises a pilot burner device, a fuel injector (102) and an ignitor unit (103). The pilot burner device comprises a pilot body (100) with a pilot surface (101) which is facing an inner volume of the combustion chamber. The fuel injector (102) comprises a fuel outlet for injecting a fuel into the inner volume. The ignitor unit (103) is adapted for igniting the fuel inside the inner volume, wherein the ignitor unit (103) is arranged at the pilot surface (101) such that fuel which passes the ignitor unit (103) is ignitable. The pilot body (100) comprises a recess (501), wherein the fuel outlet is arranged within the recess (501).</p> |
