Method of manufacturing a rotor disc for a turbine engine
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United States of America Patent
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Aug 27, 2024
Grant Date -
Jul 1, 2021
app pub date -
Mar 15, 2021
filing date -
Nov 22, 2018
priority date (Note) -
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status (Latency Note)
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Abstract
A blade for mounting on a rotor disc of a gas turbine engine includes platform segments between a airfoil and blade root and extending laterally from the blade, the platform segment having a curved profile defining a platform recess on a root side of the platform segment, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket. A recessed region is defined in a rear surface of the blade root, and is configured to receive a complementary projection of the rotor disc upon mounting the blade on the rotor disc. The recessed region has a surface configured to abut a corresponding surface on the projection of the rotor disc to form a face seal. Methods of manufacturing such a rotor disc and of sealing a circumferential joint between such blades and the rotor disc are also disclosed.
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