| 摘要 |
<p>A method for modifying a gas turbine burner assembly (1), which extends along an axis (A) and comprises a premix main burner (3) and a pilot burner (5), about which the main burner (3) is arranged; the pilot burner (5) comprises a swirler (20), a first body (17) and a second body (18), arranged about the first body (17) so as to define an annular channel (19) having a first passage section; the swirler (20) is arranged along the annular passage channel (19) and comprises a plurality of blades (21) radially extending between the first body (17) and the second body (18); the method includes the step of reducing the passage section of the annular channel (19).</p> |
