Blade outer air seal with circumferential cooled teeth
AssigneeFlorida Turbine Technologies, Inc.
InventorGeorge Liang
Life of this patent
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Abstract
A BOAS with a blade tip shroud having a row of teeth formed by rows of grooves on an underside surface, and where rows of teeth include cooling air passages to provide cooling for the blade tip shroud and to discharge cooling air into the blade tip gap to reduce an effective hot gas leakage area to reduce the blade tip leakage flow. The cooling passages include inlet convergent channels to increase the cooling air flow velocity, followed by flow metering sections and then cooling air exit slots that open onto the bottom surface of the teeth.
Claims6
A blade outer air seal for a turbine of an industrial gas turbine engine, the blade outer air seal comprising:
- a blade tip shroud segment having an underside surface exposed to a hot gas stream passing through the turbine;
- the underside surface having rows of grooves formed by rows of teeth;
- the rows of teeth each having a convergent channel opening on a top of the blade tip shroud segment;
- the convergent channels connected to constant cross-section flow metering holes;
- and,
- the constant cross-section flow metering holes connected to continuous slot exit grooves that open onto bottom surfaces of the rows of teeth.
Dependencies are inferred from the claim text.