Swept fan blade
Number of patents in Portfolio can not be more than 2000
United States of America Patent
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-
Jun 6, 2000
Issued Date -
N/A
app pub date -
Oct 9, 1998
filing date -
Apr 9, 1996
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A swept fan blade design for the low pressure compressor rotor or fan rotor stage of a ducted fan gas turbine engine has a leading edge swept forward near the hub up to a first radial height, then rearward up to second radial height and finally is swept forward again up to the blade tip. The aerodynamic effect is to produce a mid-height bias to the airflow enabling the tip region to be given increased twist and to possess increased resistance to foreign object damage. The design also provides a rear radial blade stacking axis to help reduce internal stresses due to centrifugal forces.
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