Gas turbine engine with exit flow discourager
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United States of America Patent
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Sep 19, 2017
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N/A
app pub date -
Jan 10, 2014
filing date -
Jan 10, 2014
priority date (Note) -
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Abstract
A turbine stage for a gas turbine engine is disclosed. The turbine stage includes a turbine disk and a turbine diaphragm, forming a cavity there between. The turbine stage also includes an exit flow discourager comprised of at least two teeth. The teeth may be located radially apart from each other, each tooth including a length extending in the axial direction and a width extending in the radial direction. A channel is formed between the teeth and an axially adjacent surface. A recirculation region may be formed in between each pair of teeth.
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