Importance

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Abstract

A compressor inlet manifold for directing air from a radial airflow inlet into an axial compressor inlet of a compressor of a gas turbine engine is disclosed. The compressor inlet manifold provides air flow to the compressor with reduced distortion to the compressor which enables the required design surge margin to be reduced, thereby increasing gas turbine engine efficiency. The improved air flow has reduced distortion, turbulence and unsteadiness. The compressor inlet manifold body may have at least one annular opening extending axially downstream from an upstream wall. Air flow into the compressor inlet manifold may be conditioned with one or more of a flow improvement projection extending radially inward relative to other aspects of a compressor inlet outer wall, a conically shaped inner sidewall, and a baffle positioned at an acute angle relative to an axis aligned with a radially inward air flow.

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First Claim