TURBOMACHINE COMPONENT HAVING A PLATFORM CAVITY WITH A STRESS REDUCTION FEATURE
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United States of America Patent
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Issued Date -
Jan 18, 2018
app pub date -
Jul 12, 2017
filing date -
Jul 18, 2016
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Abstract
A turbomachine component having an aerofoil, such as a blade or a vane for a gas turbine engine, includes a suction side wall and a pressure side wall bordering an aerofoil cavity, and meeting at a leading edge and a trailing edge. The turbomachine component also includes a circumferentially extending first platform wherefrom the aerofoil extends radially. The first platform includes a first-platform cavity corresponding to a shape of the aerofoil and continuous with the aerofoil cavity. The first-platform cavity has a leading-edge end and a trailing-edge end corresponding to the leading edge and the trailing edge, respectively, of the aerofoil. The first-platform cavity at the trailing-edge end forms a protuberance within the first platform. The turbomachine component may optionally include a second-platform cavity in a circumferentially extending second platform. The second-platform cavity at its trailing-edge end forms an additional protuberance within the second platform.
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