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US 12,584,416 B2Granted
O-ring for gas turbine engine
AssigneePratt & Whitney Canada Corp.
InventorRichard Ivakitch
Life of this patent
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Abstract
A seal arrangement of a gas turbine engine includes a first component and a second component abutting the first component. An O-ring is positioned in a gland volume defined between the first component and the second component. The O-ring has a hollow circular cross-sectional shape including a ring inner diameter and a ring outer diameter, with a hollow portion defined by the ring inner diameter. The ring inner diameter of the cross-sectional shape is defined as a function of a gland outer diameter, a gland inner diameter and a gland width.
Claims6
A method of assembling a seal arrangement of a gas turbine engine, comprising:
- at least partially defining a gland volume at a first component the gas turbine engine;
- installing a high-temperature O-ring into the gland volume, the high-temperature O-ring having a hollow circular cross-sectional shape including a ring inner diameter and a ring outer diameter, with a hollow portion defined by the ring inner diameter;
- wherein the ring inner diameter of the cross-sectional shape is defined as a function of a gland outer diameter, a gland inner diameter and a gland width;
- and
- installing a second component of the gas turbine engine over the high-temperature O-ring and the first component, to at least partially compress the high-temperature O-ring;
- further comprising removing a fluorocarbon O-ring from the first component before installing the high-temperature O-ring to the first component.
3 more elements
Dependencies are inferred from the claim text.