Multi-piece turbine airfoil
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United States of America Patent
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Oct 13, 2020
Grant Date -
Apr 28, 2016
app pub date -
Oct 20, 2015
filing date -
Oct 24, 2014
priority date (Note) -
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status (Latency Note)
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Abstract
A gas turbine engine includes a compressor, a combustor fluidly connected to the compressor via a flow path, and a turbine fluidly connected to the combustor via the flow path. At least one multi-piece structure is disposed within the flow path such that the multi-piece structure at least partially radially spans the flow path. The at least one multi-piece structure includes a fore portion defining a leading edge, a consumable aft portion defining a trailing edge, a pressure surface at least partially defined by a first surface of the fore portion and a first surface of the consumable aft portion, and a suction surface at least partially defined by a second surface of the fore portion and a second surface of the consumable aft portion.
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