Aircraft piston seal ring including anti-rotation provisions
AssigneeRtx Corporation
InventorsPedro D. Laureano, Raghib A. Chowdhury
Life of this patent
Estimating the term…
Abstract
A piston seal ring including a body shaped as an annular ring having an inner diameter and an outer diameter; an end gap formed in the body; a first interface surface formed on the body between the inner diameter and the outer diameter; a second interface surface orthogonally adjacent the first interface surface; and a receiver extending from the first interface surface substantially opposite the end gap, the receiver including a cavity configured to support a lug.
Claims20
A piston seal ring comprising:
- a single body shaped as an annular ring having an inner diameter and an outer diameter;
- an end gap formed in the body;
- a first interface surface formed on the body between the inner diameter and the outer diameter;
- a second interface surface orthogonally adjacent the first interface surface;
- and
- a receiver extending from the first interface surface opposite the end gap, the receiver including a cavity configured to support a lug;
- wherein the piston seal ring is configured to fluidly separate a gas turbine engine compartment.
A piston seal ring within a gas turbine engine compartment comprising:
- a body shaped as an annular ring having an inner diameter and an outer diameter;
- an end gap formed in the body;
- a first interface surface formed on the body between the inner diameter and the outer diameter;
- a second interface surface orthogonally adjacent the first interface surface;
- a receiver extending from the first interface surface opposite the end gap, the receiver including a cavity configured to support a lug;
- and
- at least one casing mount formed within the gas turbine engine compartment;
- and
- at least one turbine frame static structure formed within the gas turbine engine compartment proximate the at least one casing mount;
- wherein the piston seal ring is secured between the at least one casing mount and the at least one turbine frame static structure configured to fluidly separate the gas turbine engine compartment.
(canceled)
A process for preventing piston seal ring wear comprising:
- mounting the piston seal ring within a gas turbine engine compartment adjacent at least one casing mount formed within the gas turbine engine compartment and at least one turbine frame static structure formed within the gas turbine engine compartment proximate the at least one casing mount;
- the piston seal ring comprising:
- a body shaped as an annular ring having an inner diameter and an outer diameter;
- an end gap formed in the body;
- a first interface surface formed on the body between the inner diameter and the outer diameter;
- a second interface surface orthogonally adjacent the first interface surface;
- a receiver extending from the first interface surface opposite the end gap, the receiver including a cavity configured to support a lug;
- and
- abutting the lug against one of the at least one casing mount and the at least one turbine frame static structure.
(canceled)
Dependencies are inferred from the claim text.