| 摘要 |
A gas turbine engine pilot assembly includes a swirler (28) having high and low pressure sides (12, 14). A hood (32) at least partially encloses the swirler (28) on the high pressure side (12). The hood (32) is secured over the swirler (28), in one example. The hood (32) includes an aperture creating a tortuous path from the high pressure side (12) to the low pressure side (14) through the swirler (28). The hood (32) reduces the differential pressure across the swirler (28) by reducing the velocity and pressure of the air before entering the swirler (28). In one example, the hood (32) includes first and second spaced apart walls (38, 40) interconnected by a perimeter wall (36). The walls (38, 40, 36) form a generally annular structure, in one example. At least one of the walls (38, 40, 36) includes an array of apertures (42, 44) communicating with a cavity interiorly arranged within the walls (38, 40, 36) upstream from the swirler (28). Air from the high pressure side (12) flows through the apertures (42, 44) and is slowed before passing through the swirler (28) and into a combustion chamber (20). |
