Blade outer seal with micro axial flow cooling system
AssigneeUnited Technologies Corporation
InventorsDmitriy Romanov, Jeremy Drake
Life of this patent
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Abstract
A turbine blade outer air seal assembly includes a hot side exposed to a combustion hot gas flow, and a back side that is exposed to a supply of cooling air. The outer air seal segment includes a trailing edge cavity and a leading edge cavity separated by a divider. The cavities are feed cooling air through a plurality of inlet openings disposed transverse to the gas flow. The cooling air enters the cavities and flows toward a plurality of outlets at the leading edge and a plurality of outlets along the trailing edge. A plurality of pedestals within each of the cavities disrupts cooling air flow to increase heat absorption capacity and to increase the surface area capable of transferring heat from the hot side.
Claims20
A blade outer air seal assembly for a turbine engine comprising:
- a cavity including a top surface and a bottom surface, said top surface comprising a side opposite a back side, and said bottom surface comprising a side opposite a hot side exposed to combustion gases;
- and
- a plurality of pedestals extending between said top surface and said bottom surface for creating turbulent cooling air flow through said cavity.
A turbine blade shroud assembly for a turbine engine comprising:
- a plurality of interfitting blade outer air seal segments, each of said plurality of interfitting blade outer air seal assemblies comprising a cavity including a top surface and a bottom surface, said top surface comprising a side opposite a back side, and said bottom surface comprising a side opposite a hot side exposed to combustion gases, and a plurality of pedestals extending between said top surface and said bottom surface for creating turbulent cooling air flow through said cavity.
Dependencies are inferred from the claim text.