Compressor inlet manifold for a gas turbine engine

摘要

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.

主权项

1. 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, comprising:
a compressor inlet manifold body having at least one annular opening extending axially downstream from an upstream wall; a compressor inlet outer wall at least partially extending around the at least one annular opening; a compressor airflow inlet in fluid communication with the radial airflow inlet and the at least one annular opening, wherein the compressor airflow inlet is positioned on an opposite side of the at least one annular opening from the compressor inlet outer wall; wherein the compressor inlet outer wall includes a flow improvement projection extending radially inward relative to other aspects of the compressor inlet outer wall; and wherein the at least one annular opening is formed from an downstream inner sidewall and a upstream inward recess radially inward and downstream from the downstream inner sidewall.