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US 9,759,079 B2Granted
Split line flow path seals
AssigneesROLLS-ROYCE plc, Rolls-Royce North American Technologies Inc., Rolls-Royce High Temperature Composites 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.
Claims16
A gas turbine engine assembly, the assembly comprising
- a first component comprising ceramic matrix materials, the first component including a panel arranged to separate a high pressure zone from a low pressure zone and formed to include a first chamfer surface that extends from a high pressure surface of the first component facing the high pressure zone to a first side surface of the first component,
- a second component comprising ceramic matrix materials, the second component including a panel arranged to separate the high pressure zone from the low pressure zone and formed to include a second chamfer surface that extends from a high pressure surface of the second component facing the high pressure zone to a second side surface of the first component,
- a seal assembly arranged in a channel formed by the first chamfer and the second chamfer when the first side surface of the first component is arranged in confronting relation to the second side surface of the second component, the seal assembly including a rod configured to block gasses from passing through the interface of the first side surface included in the first component with the second side surface included in the second component and a rod locator configured to engage the rod to hold the rod in place relative to the first component and the second component,
- wherein the seal assembly includes a bias member configured to push the rod into contact with the first chamfered surface of the first component and the second chamfered surface of the second component, and
- wherein the rod locator and the bias member are included in a singular component.
2 more elements
A gas turbine engine assembly, the assembly comprising
- a first component including a panel 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 arranged to separate the high pressure zone from the low pressure zone when used in a gas turbine engine,
- a rod arranged in a channel formed between the first component and the second component that opens toward the high pressure zone when used in a gas turbine engine,
- further comprising a bias member that engages the rod, and
- further comprising a rod locator that engages the rod to hold the rod in place relative to the first component and the second component, and the rod locator and the bias member are included in a singular component.
2 more elements
Dependencies are inferred from the claim text.