Tip turbine engine and operating method with reverse core airflow
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United States of America Patent
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Jan 17, 2012
Grant Date -
Jun 11, 2009
app pub date -
Dec 1, 2004
filing date -
Dec 1, 2004
priority date (Note) -
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Abstract
A tip turbine engine (10) and a method of operating the engine provides increased efficiency while eliminating or educing the number of axial compressor (122) stages by moving the core airflow inlet (27) aft of the fan (24). As a result, the core airflow entering the core airflow inlet is the fan exhaust, which is already at an increased pressure. A portion of the fan exhaust is guided radially inward, then axially forward and then radially outward through compressor chambers (72) in the hollow fan blades (28) for further, centrifugal compression.
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