METHOD OF DIFFUSING A GAS TURBINE COMPRESSION STAGE, AND DIFFUSION STAGE FOR IMPLEMENTING SAME
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United States of America Patent
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app pub date -
Jun 19, 2012
filing date -
Jun 20, 2011
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Abandoned
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Abstract
A diffusion stage of a radial or mixed gas turbine engine compressor includes an impeller formed by two plates, between which fluid flows in a centrifugal or inclined manner from a center towards a periphery. Blades of a cascade are distributed between the plates to channel the flow of the fluid between leading edges of the blades at the center and trailing edges at the periphery. At least one of the plates has an internal face including at least one zone with alternating hollow and bump curvatures between two adjacent blades, in at least one of two substantially perpendicular directions, in the direction of flow along the blades and in an inter-blade tangential direction.
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