Turbine shroud segment sealing
AssigneePratt & Whitney Canada Corp.
InventorsJOHN PIETROBON, REMY SYNNOTT
Life of this patent
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Abstract
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.
Claims20
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.
A shroud assembly surrounding a row of blades of a gas turbine engine rotor, the shroud assembly comprising:
- a plurality of blade shroud segments disposed circumferentially one adjacent to another to form a circumferentially segmented shroud ring, an inter-segment gap being defined between each pair of adjacent blade shroud segments, each of the blade shroud segments having a body axially defined from a forward end to an aft end in a direction from an upstream position to a downstream position of a gas flow passing through the shroud assembly, and being circumferentially defined between opposite first and second lateral sides, said body including a platform having a radially inner gas path surface and an opposed radially outer back surface, and forward and aft arms extending from the back surface of the platform, said forward and aft arms being axially spaced-apart from each other, and a sealing band mounted between the forward and aft arms on the back surface of the shroud segments, the sealing band encircling the segmented blade shroud ring and circumferentially spanning all the inter-segment gaps around the circumference of the segmented shroud ring.
A method for sealing and cooling a circumferentially segmented shroud ring in a gas turbine engine, the method comprising:
- surrounding the segmented shroud ring with a sealing band configured to fully encircle the segmented shroud ring, forming a pressurized air plenum around the sealing band for urging the sealing band in sealing engagement against a radially outer surface of the segmented shroud ring, and providing impingement jet holes in said sealing band to allow some of the pressurized air in the plenum to impinge upon a radially outer surface of the segmented shroud ring.
Dependencies are inferred from the claim text.