Blade anchored securely in radial translation, propeller, turbine engine and aircraft
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United States of America Patent
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-
Dec 12, 2017
Grant Date -
Nov 19, 2015
app pub date -
May 14, 2015
filing date -
May 14, 2014
priority date (Note) -
In Force
status (Latency Note)
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Abstract
A blade includes an aerodynamic portion (21) and an assembly of the aerodynamic portion to a blade shank retaining the aerodynamic portion in a radial direction (23). The blade shank includes at least one passage restriction in at least one retention direction orthogonal to the radial direction, having a restricted width allowing the aerodynamic portion (21) to pass through. The base of the aerodynamic portion (21) has an overall dimension which is strictly greater than the restricted width so that, in the event of rupture of the assembly, the base is able to come into abutment against the passage restriction so as to retain the aerodynamic portion (21) in the blade shank (20).
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