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US 10,519,807 B2Granted
Seal segment retention ring with chordal seal feature
AssigneesROLLS-ROYCE plc, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites Inc.
InventorsBrian J. Shoemaker, Joseph P. Lamusga, Ted J. Freeman
Life of this patent
Estimating the term…
Abstract
Turbine assemblies for a turbine of a gas turbine engine are disclosed herein. The turbine assemblies include a carrier and a blade track. The blade track extends around blades of a turbine wheel assembly to block gasses passed along a gas path from moving over the blades without causing the blades to rotate during operation of the turbine assembly. The blade track includes a plurality of blade track segments arranged circumferentially adjacent to one another about a central axis to form a ring. A retention ring engages both the carrier and the blade track segments to facilitate coupling and sealing.
Claims18
A turbine assembly comprising
- a carrier coupled to a case,
- a blade track cooperating with the carrier to define a cavity configured to receive pressurized gasses, the blade track extending around blades of a turbine wheel assembly to block gasses passed along a gas path from moving over the blades without causing the blades to rotate during operation of the turbine assembly, the blade track including a plurality of blade track segments arranged circumferentially adjacent to one another about a central axis to form a ring, each blade track segment having a runner and an attachment feature coupled to the carrier, and
- a retention ring coupled to the carrier and the blade track to retain the blade track segments at predetermined locations along the central axis during operation of the turbine assembly, the retention ring including a radially-inner surface having a plurality of generally planar surface segments that cooperate to define a polygonal shape of the inner surface, wherein each one of the surface segments interfaces with the attachment feature of one of the blade track segments such that the radially-inner surface provides a seal to resist leakage of the pressurized gasses provided to the cavity into the gas path during operation of the turbine assembly, wherein a first point at which two circumferentially adjacent surface segments of the radially-inner surface intersect is spaced from the central axis by a first radial distance, a second point located on one of the two circumferentially adjacent surface segments is spaced from the central axis by a second radial distance less than the first radial distance, and a third point located on the other of the two circumferentially adjacent surface segments is spaced from the central axis by a third radial distance less than the first radial distance.
A turbine shroud comprising
- a carrier formed from metallic materials,
- a blade track coupled to the carrier and formed from ceramic matrix composite materials, the blade track including a plurality of blade track segments, and
- a retention ring coupled to the carrier and the blade track to retain the blade track segments at predetermined locations along a central axis, the retention ring including a plurality of surface segments that interface with the blade track segments to provide a seal, wherein the surface segments cooperate to define a polygonal shape of at least part of the retention ring, wherein a first point at which two circumferentially adjacent surface segments of the retention ring intersect is spaced from the central axis by a first radial distance, a second point located on one of the two circumferentially adjacent surface segments is spaced from the central axis by a second radial distance less than the first radial distance, and a third point located on the other of the two circumferentially adjacent surface segments is spaced from the central axis by a third radial distance less than the first radial distance.
A turbine shroud comprising
- a carrier formed from metallic materials,
- a blade track coupled to the carrier and formed from ceramic matrix composite materials, the blade track including a plurality of blade track segments, and
- a retention ring coupled to the carrier and the blade track to retain the blade track segments at predetermined locations along a central axis, the retention ring including a plurality of surface segments that interface with the blade track segments to provide a seal, wherein the surface segments cooperate to define a polygonal shape of at least part of the retention ring, wherein each blade track segment includes a forward hanger and an aft hanger located aft of the forward hanger along the central axis, and each one of the surface segments interfaces directly with the aft hanger of one of the blade track segments during operation of the turbine assembly to establish the seal.
A turbine shroud comprising
- a carrier formed from metallic materials,
- a blade track coupled to the carrier and formed from ceramic matrix composite materials, the blade track including a plurality of blade track segments, and
- a retention ring coupled to the carrier and the blade track to retain the blade track segments at predetermined locations along a central axis, the retention ring including a plurality of surface segments that interface with the blade track segments to provide a seal, wherein the surface segments cooperate to define a polygonal shape of at least part of the retention ring, wherein the retention ring includes a plurality of tabs extending outwardly from an outer surface thereof, and the tabs are received by corresponding slots formed in a case such that the retention ring is installed in a predetermined orientation relative to the carrier and the blade track during operation of the turbine assembly.
Dependencies are inferred from the claim text.