Gas turbine blade having a cooled shroud

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

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416191, 415115, F01D 518, F01D 522

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active

054824354

ABSTRACT:
A gas turbine blade having a shroud extending outwardly from the tip of the airfoil portion of the blade. The shroud is cooled by cooling air passages formed within it. A radial cooling air supply hole directs cooling air directly from the blade root through the airfoil and to the shroud. A plurality of cooling air passages extend from the supply hole and are disposed adjacent bearing surfaces along which the shroud contacts the shroud of an adjacent blade. One of these cooling air holes is formed in the portion of the shroud that projects from the convex surface of the airfoil and another one of the cooling air holes is formed in the portion of the shroud that projects from the concave surface of the airfoil. The cooling air holes extend to the edge of the shroud and discharge the cooling through an opening in the edge.

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patent: 4456428 (1984-06-01), Cuvillier
patent: 4474532 (1984-10-01), Pazder
patent: 4648799 (1987-03-01), Brown et al.
patent: 5117626 (1992-06-01), North et al.
patent: 5382135 (1995-01-01), Green

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