Fan blade apparatus
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United States of America Patent
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Nov 12, 2019
Grant Date -
Jun 8, 2017
app pub date -
Nov 8, 2016
filing date -
Dec 7, 2015
priority date (Note) -
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Abstract
A gas turbine engine fan blade apparatus is disclosed comprising a reverse pitch rotatable mounting and an aerofoil part. The aerofoil part comprises radially inner and radially outer portions that are separated by an interface extending from a leading edge of the aerofoil part to a trailing edge of the aerofoil part. The reverse pitch rotatable mounting locates the radially inner and radially outer portions with respect to one another. The reverse pitch rotatable mounting and separation at the interface permit relative pitch change rotation between the radially inner and radially outer portions such that one of the radially inner and radially outer portions is rotatable to a reverse pitch configuration by comparison with the other portion.
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