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US 2017/0370240 A1Published application
Split line flow path seals
AssigneesROLLS-ROYCE plc, Rolls-Royce North American Technologies Inc.
InventorsAaron D. Sippel, Ted J. Freeman, David J. Thomas, Joseph P. Lamusga, Brian J. Shoemaker, Steven Hillier
Life of this patent
Estimating the term…
Abstract
A gas turbine engine assembly adapted to separate a high pressure zone from a low pressure zone includes a seal assembly configured to block gasses from passing through the interface of two adjacent components. The seal assembly includes a rod.
Claims19
A gas turbine engine assembly, the assembly comprising
- a first component comprising ceramic matrix materials, the first component including a panel that extends partway around a central axis, that is arranged to separate a high pressure zone located radially outward of the panel from a low pressure zone located radially inward of the panel, and that is formed to include a first chamfer surface that extends radially outward and circumferentially away from a first side of the first component,
- a second component comprising ceramic matrix materials, the second component including a panel that extends partway around the central axis, that is arranged to separate the high pressure zone from the low pressure zone, and that is formed to include a second chamfer surface that extends radially outward and circumferentially away from a second side of the second component, and
- a seal assembly arranged between the first chamfer and the second chamfer when the first side of the first component is arranged in confronting relation to the second side of the second component, the seal assembly including a rod engaged with the first chamfer and the second chamfer that is configured to block gasses from passing through the interface of the first side included in the first component with the second side included in the second component and a rod locator that is configured to engage the rod to hold the rod in place relative to the first component and the second component.
A gas turbine engine assembly, the assembly comprising
- a first component including a panel that extends partway around a central axis and that is arranged to separate a high pressure zone from a low pressure zone when used in a gas turbine engine,
- a second component including a panel that extends partway around the central axis and that is arranged to separate the high pressure zone from the low pressure zone when used in a gas turbine engine, and
- a rod arranged in a radially-outwardly opening channel bounded by the first component and the second component that opens toward the high pressure zone when used in a gas turbine engine.
A gas turbine engine assembly, the assembly comprising
- a first blade track segment comprising ceramic matrix materials, the first blade track segment including a panel, the panel being shaped to extend partway around a central axis and partway around an associated turbine wheel, and the panel being formed to include a first chamfer surface,
- a second blade track segment comprising ceramic matrix materials, the second blade track segment including a panel, the panel being shaped to extend partway around the central axis and partway around an associated turbine wheel, and the panel being formed to include a second chamfer surface, and
- a rod engaged with the first chamfer surface and the second chamfer surface to seal an interface between the first blade track segment and the second blade track segment.
Dependencies are inferred from the claim text.