Gas turbine engine compressors having optimized stall enhancement feature configurations and methods for the production thereof

A multistage Gas Turbine Engine (GTE) compressor included in a gas turbine engine, the multistage GTE compressor comprising:

• an engine casing;
• a shaft mounted in the engine casing for rotation about a rotational axis;
• a series of axial compressor stages each containing a rotor mounted to the shaft and surrounded by the engine casing;
• and
• a plurality of stall enhancing features (SEFs) integrated into the series of axial compressor stages at locations corresponding to a selected subset of rotors included in the series of axial compressor stages;
• wherein the total number of rotors contained within the series of axial compressor stages is equal to ntotal, wherein the number of rotors included within the selected subset of rotors is equal to nenhanced, and wherein 2<nenhanced <ntotal;
• and
• wherein the series of axial compressor stages comprises:
• a first forward axial compressor stage to which a first SEF in the plurality of SEFs is applied and the first SEF comprises a first casing treatment feature;
• and
• a first aft compressor stage to which a second SEF in the plurality of SEFs is applied, and the second SEF comprises an upstream injection feature that is configured to direct pressurized airflow into a main flow path through the first aft compressor stage at a location proximate a hub of a stator immediately upstream from the rotor contained in the first aft compressor stage.