Tip turbine engine with aspirated compressor
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United States of America Patent
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Mar 6, 2018
Grant Date -
Jan 22, 2009
app pub date -
Feb 15, 2006
filing date -
Feb 15, 2006
priority date (Note) -
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Abstract
A tip turbine engine includes an axial compressor having a plurality of airfoils compressing core airflow. The airfoils include bleed air openings on their suction side surfaces. The bleed air openings prevent separation of the compressed airflow, which permits each airfoil stage to perform increased compression without separation of the airflow. As a result, the number of stages can be reduced, thereby shortening the overall length of the turbine engine.
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