| 摘要 |
An airblast fuel injector for the combustor of a gas turbine engine has, in order from radially inner to outer, a coaxial arrangement of an inner swirler passage (7), an annular fuel passage (3), an annular mid swirler passage (9), and an annular outer swirler passage (15). The fuel passage extends to a prefilming lip (5), and the inner and mid swirler passages swirl air past the prefilming lip so that fuel fed from the fuel passage to the prefilming lip is entrained by the swirling air into a fuel spray stream which emanates from the prefilming lip. The outer swirler passage, which swirls further air past the mid swirler passage to modify the fuel spray stream, has a convergent portion (23) which converges in the direction of air flow. The radially inward wall of said convergent portion is defined by a frustoconical separator element (19) which separates the outer swirler passage from the mid swirler passage, the separator element converging in the direction of air flow to terminate in a lip at the mouths of the mid swirler passage and the outer swirler passage. The radially outward wall of said convergent portion is defined by a shroud which converges in the direction of air flow to a shroud lip (25) at the position of maximum convergence of the shroud, the shroud lip having a diameter D* and being downstream of the separator element lip by an axial distance L, and the ratio L/D* being in the range from 0.02 to 0.11. The shroud depth d is the radial distance between the radially outward wall of the outer swirler passage at the entrance to said convergent portion and the shroud lip, and the outer swirler diameter D is the distance between diametrically opposing midspan positions of the outer swirler passage at the entrance to said convergent portion, the ratio D/d being in the range from 4.5 to 6.5.
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