Aircraft piston seal ring including anti-rotation provisions
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.
1. 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.
2. The piston seal ring according to claim 1 , wherein the cavity is formed between a pair of opposing side walls coupled with an upper shelf and a lower shelf opposite the upper shelf.
3. The piston seal ring according to claim 1 , wherein the receiver is formed as a section of material integral with the body along a circumference of the piston seal ring.
4. The piston seal ring according to claim 1 , wherein the receiver comprises an upper shelf along with opposing side walls to form a C-channel shape cavity.
5. The piston seal ring according to claim 1 , wherein the receiver includes opposing side walls extending from the first interface surface.
6. The piston seal ring according to claim 1 , wherein the lug is configured for mistake proofing and as an anti-rotation device preventing the piston seal ring from rotation against a mating part.
7. The piston seal ring according to claim 1 , wherein the cavity is selected from the group consisting of a C-channel, and D-channel.
8. 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.
9. The piston seal ring within a gas turbine engine compartment according to claim 8 , wherein the receiver is formed between 160 degrees to 200 degrees apart from the end gap.
10. The piston seal ring within a gas turbine engine compartment according to claim 8 , further comprising:
multiple receivers formed in the body at spaced apart intervals around a circumference of the body.
11. The piston seal ring within a gas turbine engine compartment according to claim 10 , wherein the multiple receivers are spaced opposite to each other around the circumference.
12. The piston seal ring within a gas turbine engine compartment according to claim 8 , wherein the lug is configured as an anti-rotation device preventing the piston seal ring from rotation relative to the at least one casing mount.
13. 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.
14. The process of claim 13 , further comprising:
securing the piston seal ring between the at least one casing mount and the at least one turbine frame static structure; and
fluidly separating the gas turbine engine compartment.
15. The process of claim 13 , further comprising:
forming receiver as a section of material integral with the body along a circumference of the piston seal ring.
16. The process of claim 13 , further comprising:
forming multiple receivers in the body at spaced apart intervals around a circumference of the body.
17. The process of claim 13 , wherein the cavity is selected from the group consisting of a C-channel, and D-channel.
18. The process of claim 13 , wherein the receiver is formed between 160 degrees to 200 degrees apart from the end gap.