Shroud for splitter and rotor airfoils of a fan for a gas turbine engine
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United States of America Patent
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Oct 19, 2021
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N/A
app pub date -
Dec 13, 2019
filing date -
Dec 13, 2019
priority date (Note) -
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Abstract
A fan for a gas turbine engine is provided. The fan includes a rotor including at least one rotor stage having a rotatable disk defining a flowpath surface and an array of rotor airfoils extending outward from the flowpath surface; an array of splitter airfoils extending outward from the flowpath surface, wherein the splitter airfoils and the rotor airfoils are disposed in a sequential arrangement; and a shroud extending between the rotor airfoils and the splitter airfoils.
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