Honeywell International Inc.

Greyson Boyll

Nick A Nolcheff

Bruce David Reynolds

Ryan Bernaud

Systems and methods for stable operation of a compressor of a gas turbine engine include axial stages, each including a series of rotor blades. A centrifugal stage has a centrifugal impeller disposed downstream from the axial stages. Air flows through the compressor first through the axial stages and then through the centrifugal stage. Each respective axial stage includes mechanisms for the avoidance of certain operating conditions of the compressor such as surge. The mechanisms include variable vane sets disposed upstream from a series of the rotor blades or a bleed port or ports around the respective axial stage downstream from the series of rotor blades to selectively extract air from the respective axial stage.

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Phoenix, AZ, United States of America

Greyson Boyll