Sensor ice shield
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United States of America Patent
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-
May 19, 1998
Grant Date -
N/A
app pub date -
Aug 21, 1996
filing date -
Aug 21, 1996
priority date (Note) -
In Force
status (Latency Note)
Importance
Abstract
A system is provided for reducing ice mass on an aircraft engine. A compressor inlet temperature and pressure sensor measures total temperature and total pressure at the inlet to the engine compressor. An ice shield is provided, wherein a plurality of wedge portions has multiple protrusions for promoting ice formation in multiple locations. The ice shield is separable from the sensor with which it interfaces. The ice shield comprises straight angle wedge shapes and curved surfaces to separate and minimize ice accretion in desired locations. The mass of each resultant ice formation is reduced to a size that the compressor inlet blades can withstand without deformation.
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