Seals and methods of making seals
A tribological and creep resistant system configured to operate at temperatures in excess of 700° C. A seal body extends between a leading edge and a trailing edge. A first component contact surface is adjacent the leading edge and a second component contact surface is adjacent the trailing edge. The seal body is formed from a high entropy alloy.
1. A tribological and creep resistant system configured to operate at temperatures in excess of 700° C., comprising:
a seal body extending between a leading edge and a trailing edge including a first component contact surface adjacent the leading edge and a second component contact surface adjacent the trailing edge,
wherein the seal body is formed from a high entropy alloy that includes MoNbTaW.
2. The system of claim 1 , wherein the seal body forms a complete ring.
3. The system of claim 1 , wherein the system is configured to operate at temperatures up to 900° C.
4. The system of claim 1 , further comprising a gas turbine engine with the seal body located radially outward of a core airflow path through the gas turbine engine in a turbine section of the gas turbine engine.
5. The system of claim 1 , further comprising a gas turbine engine with the seal body located radially outward of a core airflow path through the gas turbine engine in a high pressure compressor of the gas turbine engine.
6. The system of claim 2 , wherein the seal body includes at least one bend.
7. The system of claim 6 , wherein the at least one bend includes multiple bends on one of a radially inner side or a radially outer side of the seal body and only a single bend on the other of the radially inner side or the radially outer side.
8. The system of claim 7 , further comprising:
a first component engaging the first component contact surface on the leading edge of the body seal and a second component engaging the second component contact surface on the trailing edge of the body seal.
9. The system of claim 8 , wherein the first component is a vane and the second component is a blade outer air seal.
10. The system of claim 2 , further comprising:
a first component defining a groove that seats a radially inner portion of the seal body, wherein the seal body defines a piston seal.
11. The system of claim 10 , wherein the first component is a mid-turbine frame vane and the groove is located on a radially outer portion of the mid-turbine frame vane.
12. A tribological and creep resistant system configured to operate at temperatures in excess of 700° C., comprising:
a seal body extending between a leading edge and a trailing edge including a first component contact surface adjacent the leading edge and a second component contact surface adjacent the trailing edge,
wherein the seal body is formed from a high entropy alloy that includes CoCrFeMnNi.
13. The system as recited in claim 12 , wherein the CoCrFeMnNi is formed from 17.04% Co, 15.43% Cr, 16.97% Fe, 15.68% Mn, 17.82% Ni, 15% Ti, 0.9% Al, 1.02% C, and 0.13 O.
14. The system of claim 12 , wherein the seal body forms a complete ring.
15. The system of claim 14 , wherein the seal body includes multiple bends on one of a radially inner side or a radially outer side of the seal body and only a single bend on the other of the radially inner side or the radially outer side.
16. The system of claim 15 , further comprising:
a first component engaging the first component contact surface on the leading edge of the body seal and a second component engaging the second component contact surface on the trailing edge of the body seal.
17. The system of claim 16 , wherein the first component is a vane and the second component is a blade outer air seal.
18. The system of claim 14 , further comprising:
a first component defining a groove that seats a radially inner portion of the seal body, wherein the seal body defines a piston seal and the first component is a mid-turbine frame vane and the groove is located on a radially outer portion of the mid-turbine frame vane.
19. The system of claim 12 , wherein the system is configured to operate at temperatures up to 900° C.
20. The system of claim 12 , further comprising a gas turbine engine with the seal body located radially outward of a core airflow path through the gas turbine engine in a turbine section of the gas turbine engine.
21. The system of claim 12 , further comprising a gas turbine engine with the seal body located radially outward of a core airflow path through the gas turbine engine in a high pressure compressor of the gas turbine engine.