embodiment a majority of the total length of the splitter vane 30 is disposed within the redirection zone defined at the curved portion 28 the presence of the splitter vane 30 may at least reduce some of the drawbacks associated with the tight bend of the curved portion 28 as noted below the curvature of the curved portion 28 may tend to detach the flow f from the walls 28 a 28 b which can result in pressure losses and non uniform flow at the outlet o mixing loss may contribute to overall diffuser performance flow separation in the diffuser pipe 20 starting at the curved portion 28 may not only be potentially detrimental to the compressor section 17 performance and operability but also to its structural integrity as flow separation can be destructive in nature and can lead to premature pipe breakage fatigue cracking noise flame instability etc the diffuser pipe 20 of the present disclosure may relieve the pressure gradient at the curved portion 28 by the presence of the splitter vane 30 while the splitter vane 30 may provide additional aerodynamic friction loss the reduction in overall mixing loss may more than offset this increase as seen in fig4 the splitter vane 30 is in this embodiment airfoil shaped and includes a leading edge 32 and a trailing edge 34 the airfoil of the splitter vane 30 therefore defines a pressure side 36 and a suction side 38 as conventionally known for airfoils the splitter vane 30 is oriented in the diffuser pipe 20 so that the leading edge 32 receives the incoming flow f and a curvature of the airfoil shaped splitter vane 30 is in a same direction as the curved portion 28 of the diffuser pipe 20.