Patent ID: 7284954
Filing Date: 2007-10-23
Classification: F01D,F05D

Abstract:
1. A shroud surrounding a portion of a turbine flow path in a gas turbine engine, said shroud comprising: A first surface having a first contour; A second surface having a second contour, said second surface located radially outward of said first surface thereby establishing a thickness therebetween, said second surface having a plurality of openings located therein; A forward face and an aft face extending radially between said first and second surfaces, said forward face and said aft face in axial spaced relation; A first sidewall and a second sidewall in circumferential spaced relation and extending generally axially from said forward face to said aft face; A first row of hooks extending radially outward from said second surface proximate said forward face; A plurality of generally axial cooling holes extending from proximate said first row of hooks to said aft face; A plurality of generally circumferential cooling holes oriented generally perpendicular to said generally axial cooling holes; and, Wherein said generally circumferential cooling holes are spaced a non-uniform distance apart so as to provide additional cooling to selected portions of said sidewalls.