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US 10,100,660 B2Granted
Seals for gas turbine engines
AssigneeROLLS-ROYCE plc
InventorsAaron D. Sippel, Jun Shi, Emil R. DeJulio
Life of this patent
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Abstract
A turbine shroud for use in a gas turbine engine that includes a metallic carrier, a blade track, and a seal is disclosed. The seal is engaged with surfaces of the metallic carrier and the blade track to block ingress of hot gasses at the interface of the blade track and the metallic carrier.
Claims19
A turbine shroud for use in a gas turbine engine that extends around a central axis, the turbine shroud comprising
- an annular metallic carrier adapted to be coupled to a gas turbine engine case and formed to include a cooling channel that opens inwardly in a radial direction,
- an annular blade track nested in the annular metallic carrier and arranged radially inward of the cooling channel, and
- a metallic seal engaged with surfaces of the annular metallic carrier and a radially-outer surface of the annular blade track to block ingress of hot gases into the cooling channel at the interface of the annular blade track and the annular metallic carrier,
- wherein the seal includes a first split ring having a W-shaped cross section that opens outwardly in the radial direction so that pressurized cooling air provided to the cooling channel encourages the first split ring to change size axially such that the first split ring engages the surfaces of the annular metallic carrier during use of the turbine shroud.
1 more element
A turbine shroud for use in a gas turbine engine that extends around a central axis, the turbine shroud comprising
- a carrier adapted to be coupled to a gas turbine engine case and formed to include a cooling channel that opens inwardly in a radial direction,
- a blade track nested in the carrier and arranged radially inward of the cooling channel, and
- a seal engaged with surfaces of the carrier defining the cooling channel and a radially-outer surface of the blade track, the seal including a first split ring having a W-shaped cross section that opens outwardly in the radial direction.
A method of assembling a turbine shroud comprising
- creating a seal by nesting a first split ring having a W-shaped cross section and a second split ring having a W-shaped cross section so that circumferential breaks in the first and the second split rings are offset from one another by about 180 degrees, and
- positioning the seal radially between a carrier and a blade track so that the seal engages surfaces defining a radially-inwardly opening cooling channel formed by the carrier and a radially-outer surface of the blade track.
Dependencies are inferred from the claim text.