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US 2024/0344607 A1Published application
Piston ring with integrated anti-rotation feature
AssigneePratt & Whitney Canada Corp.
InventorRabih Kassab
Life of this patent
Estimating the term…
Abstract
A piston ring for use with a gas turbine engine, including: a circular body having a rectangular cross section with overlapping open free ends; and an anti-rotating feature extending from an axial surface of the circular body, the anti-rotating feature being integrally formed with the circular body such that the circular body and the anti-rotating feature are formed from a single unitary member.
Claims20
A piston ring for use with a gas turbine engine, comprising:
- a circular body having a rectangular cross section with overlapping open free ends;
- and
- an anti-rotating feature extending from an axial surface of the circular body, the anti-rotating feature being integrally formed with the circular body such that the circular body and the anti-rotating feature are formed from a single unitary member.
A seal assembly for use in a gas turbine engine, comprising:
- a first inner cylindrical component;
- a second outer cylindrical component;
- a groove located in the first inner cylindrical component or the second outer cylindrical component, the groove defined by a seal side rail that extends radially away from a surface of the first inner cylindrical component or a surface of the second outer cylindrical component and a non-seal side rail that extends radially away from the surface of the first inner cylindrical component or the surface of the second outer cylindrical component, the seal side rail and the non-seal rail being in a facing spaced relationship;
- and
- a piston ring located in the groove between the first inner cylindrical component and the second outer cylindrical component, the piston ring being located between the seal side rail and the non-seal side rail, the piston ring having a circular body with a rectangular cross section with overlapping open free ends, and an anti-rotating feature extending from an axial surface of the circular body, the anti-rotating feature being integrally formed with the circular body such that the circular body and the anti-rotating feature are formed from a single unitary member, wherein the anti-rotating feature is received within a slot formed in the non-seal side rail and contact between the anti-rotating feature and the slot prevents circumferential movement of the piston ring in the groove.
2 more elements
A method for providing a seal in a gas turbine engine, comprising:
- inserting a piston ring between a first inner cylindrical component and a second outer cylindrical component, the piston ring having a circular body with a rectangular cross section with overlapping open free ends, and an anti-rotating feature extending from an axial surface of the circular body, the anti-rotating feature being integrally formed with the circular body such that the circular body and the anti-rotating feature are formed from a single unitary member, wherein a groove is located in the first inner cylindrical component or the second outer cylindrical component, the groove defined by a seal side rail that extends radially away from a surface of the first inner cylindrical component or a surface of the second outer cylindrical component and a non-seal side rail that extends radially away from the surface of the first inner cylindrical component or the surface of the second outer cylindrical component, the seal side rail and the non-seal rail being in a facing spaced relationship;
- and
- preventing circumferential movement of the piston ring within the groove by locating the anti-rotating feature within a slot formed in the non-seal side rail such that contact between the anti-rotating feature and the slot prevents circumferential movement of the piston ring in the groove.
Dependencies are inferred from the claim text.