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US 10,662,794 B2Granted
Strip seal axial assembly groove
AssigneeROLLS-ROYCE plc
InventorSayon Das
Life of this patent
Estimating the term…
Abstract
Systems and methods for reducing heat exposure of a turbine casing in a gas turbine engine may be provided. The system may include blade track segments. The blade track segments may include a cavity formed at a circumferential end of the blade track segment. The blade track segments may further include an assembly groove configured to provide a clearance for axial insertion of an inter-segment strip seal. An inter-segment strip seal may be axially inserted past the assembly grooves and into the cavity. The inter-segment strip seal may cover a gap between adjacent blade track segments, thus blocking hot, high pressure fluid from contacting the turbine casing.
Claims18
An apparatus comprising:
- a blade track segment for a gas turbine engine including:
- a front end;
- a rear end downstream of the front end;
- a cavity within the blade track segment having an opening at the rear end for axial insertion of an inter-segment strip seal;
- an overhanging portion at the rear end, the overhanging portion disposed radially outward from the cavity and extending along an axial direction downstream of the opening;
- and
- an assembly groove in the overhanging portion of the blade track segment, wherein the assembly groove is configured to provide a clearance for the axial insertion of the inter-segment strip seal into the cavity.
4 more elements
A system comprising:
- a first blade track segment for a gas turbine engine including:
- a first front end;
- a first rear end downstream of the first front end;
- a first cavity within the first blade track segment having a first opening at the first rear end for axial insertion of an inter-segment strip seal;
- a first overhanging portion at the first rear end, the first overhanging portion disposed radially outward from the first cavity and extending along an axial direction downstream of the first opening;
- and
- a first assembly groove in the first overhanging portion of the first blade track segment, the first assembly groove configured to provide a first clearance for the axial insertion of the inter-segment strip seal into the first cavity;
- and
- a second blade track segment for the gas turbine engine including:
- a second front end;
- a second rear end downstream of the second front end;
- a second cavity within the second blade track segment having a second opening at the second rear end for axial insertion of the inter-segment strip seal;
- a second overhanging portion at the second rear end, the second overhanging portion disposed radially outward from the second cavity and extending along the axial direction downstream of the second opening;
- and
- a second assembly groove in the second overhanging portion of the second blade track segment, the second assembly groove configured to provide a second clearance for the axial insertion of the inter-segment strip seal into the second cavity, and the first cavity being circumferentially adjacent to the second cavity.
12 more elements
A method comprising:
- assembling a first blade track segment for a gas turbine engine, the first blade track segment including:
- a first front end;
- a first rear end downstream of the first front end;
- a first cavity within the first blade track segment having a first opening at the first rear end for axial insertion of an inter-segment strip seal;
- a first overhanging portion at the first rear end, the first overhanging portion disposed radially outward from the first cavity and extending along an axial direction downstream of the first opening;
- and
- a first assembly groove in the first overhanging portion of the first blade track segment, the first assembly groove configured to provide a first clearance for the axial insertion of the inter-segment strip seal into the first cavity;
- assembling a second blade track segment for the gas turbine engine, the second blade track segment including:
- a second front end;
- a second rear end downstream of the first front end;
- a second cavity within the second blade track segment having a second opening at the second rear end for axial insertion of the inter-segment strip seal;
- a second overhanging portion at the second rear end, the second overhanging portion disposed radially outward from the second cavity and extending along the axial direction downstream of the second opening;
- and
- a second assembly groove in the second overhanging portion of the second blade track segment, the second assembly groove configured to provide a second clearance for axial insertion of the inter-segment strip seal into the second cavity;
- and
- axially inserting the inter-segment strip seal past the first assembly groove and past the second assembly groove into the first cavity and the second cavity.
13 more elements
Dependencies are inferred from the claim text.