| 摘要 |
<p>A gas turbine combustion system (1) which comprises - a first radial inflow swirler (7) having first radial outer intake openings (13), first radial inner outlet openings (15) and first flow passages (11) extending from the first radial outer intake openings (13) to the first radial inner outlet openings (15), each first flow passage (11) including a first angle (a) with respect to the radial direction; - a second radial inflow swirler (17) having second radial outer intake openings (23), second radial inner outlet openings (25) and second flow passages (21) extending from the second radial outer intake openings (23) to the second radial inner outlet openings (25), each second flow passage (21) including a second angle (p) with respect to the radial direction; - where the radial outer circumference of the second radial inflow swirler (17) has a diameter that is smaller than the diameter of the radial inner circumference of the first radial inflow swirler (7) and the second radial inflow swirler (17) is located coaxially with and radially inside the first radial inflow swirler (7). The first angle (a) has a different sign than the second angle (p) with respect to the radial direction.</p> |
