Turbine shroud segment sealing

摘要

A segmented shroud ring surrounds a circumferential array of blades of a gas turbine engine rotor. The shroud ring has a plurality of shroud segments disposed circumferentially one adjacent to another. The circumferentially adjacent shroud segments have confronting sides defining an inter-segment gap therebetween. The inter-segment gaps are sealed by a sealing band mounted to the radially outer surface of the segmented shroud ring so as to extend across the inter-segment gaps around the full circumference of the shroud ring. Impingement jet holes may be defined in the sealing band for cooling the shroud segments.

主权项

1. A shroud assembly for surrounding a circumferential array of blades of a gas turbine engine rotor, the shroud assembly comprising: a plurality of shroud segments disposed circumferentially one adjacent to another, each shroud segment having a radially inner gas path surface and an opposed radially outer surface, wherein each pair of circumferentially adjacent shroud segments defines an inter-segment gap, and a sealing band mounted around the radially outer surface of the blade shroud segments and extending across the inter-segment gaps around the full circumference of the shroud assembly, the sealing band including a split ring having opposed overlapping end portions adapted to circumferentially slide one over the other and forming a radially outer end portion and a radially inner end portion, wherein the radially outer end portion has a window opening defined therein in registry with a plurality of impingement holes defined in the radially inner end portion of the split ring.