| 摘要 |
<p>Compressor 14 of a gas turbine engine has a final centrifugal stage 18 discharging air into annulus 20. Diffuser 20 are straight and of frustoconical shape receiving air from the annulus. A side cut produces opening 38 in the side of each diffuser. Much of the flow exits through, and is directed by these openings.</p> |
