Back to results
US 11,466,591 B2Granted
Reduced radial clearance seal system
AssigneeRaytheon Technologies Corporation
InventorsJonathan Logan Miller, Daniel B. Denis, Shadd A. Bradshaw
Life of this patent
Estimating the term…
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 Titanium-Zirconium-Molybdenum (TZM) alloy 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 Molybdenum alloy material that provides a first coefficient of thermal expansion,
- a seal ring manufactured of a graphitic material that provides a second coefficient of thermal expansion greater than the first coefficient of thermal expansion,
- wherein the seal ring is manufactured of electrographitic carbon materials.
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.