A compressor (16) for pressurizing a flow of air within an aircraft includes an inlet (26) providing the flow of air to the compressor (16). An outlet (28) provides the flow of air, after pressurization by the compressor (16), to a chamber of the aircraft. A diffuser assembly (30) is disposed between the inlet (26) and the outlet (28). The diffuser assembly (30) includes one or more vanes (38) at least partially impeding the flow of air through the diffuser assembly (30). A backing plate (32) is included having a surface (44) adjacent to the one or more vanes (38). The surface (44) includes a relief feature (46) that enables air to bypass the one or more vanes (38). The relief feature (46) has an axial depth (D2) of about 0.25% to 2.5% of a width (D5) of a flow path through the diffuser assembly (30) or of about 0.5% to 5% of a thickness (D4) of a flange (52) of the backing plate (32).
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