Systems and methods with distributed bleed for gas turbine engine compressor stabilization
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United States of America
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Jan 14, 2025
Grant Date -
Oct 24, 2024
app pub date -
Apr 19, 2023
filing date -
Apr 19, 2023
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Abstract
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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