| 摘要 |
A compressor (122) includes a deswirl assembly (206) to improve aerodynamic coupling with the combustor (124). The assembly (206) includes a n annular housing and a plurality of vanes (224). The annular housing includes an inner and an outer annular wall (220, 222) disposed concentric to each other, and a flowpath (228) defined therebetween. The plurality of vanes (2240) s disposed in the flowpath (228) in a substantially annular pattern. Each vane has a leading edge (302) , a trailing edge (304), a convex surface (308), and concave surface (306), and each of the convex and concave surfaces (308, 306) extends between the leading and trailing edges (302, 304). Additionally, each vane (224) extends between and is angle d relative to the inner and the outer annular walls (220, 222) such that the concave surface (306) faces the outer annular wall (222) and the convex surface (308 ) faces the inner annular wall (220). The vanes (224) preferably have a uniform axia l cross section for ease of manufacturing.
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