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US 2021/0348523 A1Published application
Reduced radial clearance seal system
AssigneeRaytheon Technologies Corporation
InventorsJonathan Logan Miller, Daniel B. Denis, Shadd A. Bradshaw
Life of this patent
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Abstract
A seal system for a gas turbine engine includes a seal runner manufactured of a Molybdenum alloy material that provides a first coefficient of thermal expansion and a seal ring manufactured of a graphitic material that provides a second coefficient of thermal expansion greater than the first coefficient of thermal expansion.
Claims19
A seal system for a gas turbine engine comprising:
- a seal runner manufactured of a Molybdenum alloy material that provides a first coefficient of thermal expansion;
- and
- a seal ring manufactured of a graphitic material that provides a second coefficient of thermal expansion greater than the first coefficient of thermal expansion.
A seal system for a gas turbine engine comprising:
- a seal runner manufactured of a Titanium-Zirconium-Molybdenum (TZM) alloy material that provides a first coefficient of thermal expansion;
- and
- a seal ring manufactured of an electrographitic carbon material that provides a second coefficient of thermal expansion greater than the first coefficient of thermal expansion, wherein the seal ring is assembled to the seal runner to form a sealing interface that provides a clearance in both a hot operating condition and a cold operating condition.
Dependencies are inferred from the claim text.