Air deflector for a cooling circuit for a gas turbine blade

Fluid reaction surfaces (i.e. – impellers) – With heating – cooling or thermal insulation means – Changing state mass within or fluid flow through working...

Reexamination Certificate

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Reexamination Certificate

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11466660

ABSTRACT:
A gas turbine blade comprising an internal cooling circuit consisting of at least one cavity extending radially between the base and tip of the blade, at least one air inlet aperture at one radial end of the cavity and at least one air outlet orifice opening into the cavity and emerging onto one of the faces of the blade. At least one of the walls of the cavity of the cooling circuit comprises at least one air deflector whereof the shape and dimensions are adapted to project the air flowing along the wall of the cavity towards an opposite wall of the cavity whilst avoiding re-attachment of the boundary layer immediately downstream of the air deflector.

REFERENCES:
patent: 3171631 (1965-03-01), Aspinwall
patent: 4180373 (1979-12-01), Moore et al.
patent: 4775296 (1988-10-01), Schwarzmann et al.
patent: 5738493 (1998-04-01), Lee et al.
patent: 5779438 (1998-07-01), Wilfert
patent: 2003/0044278 (2003-03-01), Eneau et al.
patent: 2005/0025623 (2005-02-01), Botrel et al.
patent: 2005/0058546 (2005-03-01), Cooper
patent: 195 26 917 (1997-01-01), None

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