Gas turbine engine blade and disk
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United States of America Patent
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Feb 20, 2018
Issued Date -
N/A
app pub date -
Dec 18, 2013
filing date -
Feb 25, 2013
priority date (Note) -
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Abstract
In some examples, an apparatus may include a gas turbine engine component comprising a blade, a platform forming an airflow surface from which the blade extends on one side, and a motion weld receiving surface disposed on a non-airflow side of the platform, and a disk having a motion weld disk portion to receive the motion weld receiving surface of the gas turbine engine component and form a motion weld coupling when the disk and gas turbine engine component are coupled, wherein, prior to coupling, the gas turbine engine component further includes a blade stalk disposed on the non-airflow side of the platform and in which is formed the motion weld receiving surface.
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