Granted Patent B2

US 12,584,416 · App. 18/442,464 · Granted Mar 24, 2026

Inventor: Richard Ivakitch (Scarborough, CA)

Assignee: PRATT & WHITNEY CANADA CORP.

F01D11/003F05D2240/35F05D2240/55

Abstract

Claims (11)

1 . 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.

2 . The method of claim 1 , wherein the high-temperature O-ring is configured to operate at temperatures greater than 350 degrees Fahrenheit.

3 . The method of claim 1 , further comprising forming a seal groove in the first component to at least partially defining the gland volume.

4 . The method of claim 1 , further comprising defining the ring inner diameter in a range of 0.2-0.4 times the ring outer diameter.

5 . The method of claim 1 , further comprising defining the ring inner by Formula 1.

6 . The method of claim 1 , wherein the first component and the second component are disposed at a bearing assembly of the gas turbine engine.

Assignments (1)

Continuity (1)

References Cited (18)