초록

A blade outer air seal (BOAS) assembly for an engine case of a gas turbine engine includes a multiple of supported air seal segments and a multiple of floating air seal segments circumferentially alternate with the multiple of supported air seal segments.

대표청구항 ▼

1. A blade outer air seal (BOAS) assembly for an engine case of a gas turbine engine, comprising: a multiple of supported air seal segments; anda multiple of floating air seal segments that circumferentially alternated with the multiple of supported air seal segments. 2. The assembly as recited in c

1. A blade outer air seal (BOAS) assembly for an engine case of a gas turbine engine, comprising: a multiple of supported air seal segments; anda multiple of floating air seal segments that circumferentially alternated with the multiple of supported air seal segments. 2. The assembly as recited in claim 1, wherein each of the multiple of floating air seal segments includes a first stepped surface with a first contact surface, and a second stepped surface with a second contact surface. 3. The assembly as recited in claim 2, wherein the first contact surface and the second contact surface each include a semi-cylindrical member. 4. The assembly as recited in claim 2, wherein the first contact surface and the second contact surface each are axially arranged with respect to an engine central longitudinal axis. 5. The assembly as recited in claim 2, wherein the first contact surface is axially arranged along a length of a first axial edge, and the second contact surface is axially arranged along a length of a second axial edge. 6. The assembly as recited in claim 2, wherein the first stepped surface and the second stepped surface are stepped with respect to a back surface of the multiple of supported air seal segments such that the gas path surface is circumferentially aligned with a gas path surface of the multiple supported air seal segments. 7. The assembly as recited in claim 1, wherein each of the multiple of supported air seal segments includes a support that extends therefrom. 8. The assembly as recited in claim 1, wherein each of the multiple of supported air seal segments includes a support that extends therefrom, and wherein the support interfaces with a shroud assembly. 9. The assembly as recited in claim 1, wherein each of the multiple of supported air seal segments include a support that extends therefrom, and wherein the support movable in response to an actuator. 10. The assembly as recited in claim 1, wherein each of the multiple of floating air seal segments includes a support that extends therefrom, and wherein the support interfaces with a shroud assembly. 11. A gas turbine engine, comprising: an engine case structure extending around an engine central longitudinal axis;a shroud assembly attached to the engine case structure;a multiple of supported air seal segments attached to the shroud assembly; anda multiple of floating air seal segments circumferentially alternated with the multiple of supported air seal segments. 12. The gas turbine engine as recited in claim 11, wherein the multiple of supported air seal segments are actively actuated. 13. The gas turbine engine as recited in claim 11, wherein each of the multiple of floating air seal segments includes a first stepped surface with a first contact surface, and a second stepped surface with a second contact surface. 14. The gas turbine engine as recited in claim 13, wherein the first contact surface and the second contact surface each include a semi-cylindrical member. 15. The gas turbine engine as recited in claim 14, wherein the first contact surface and the second contact surface are axially arranged with respect to the engine central longitudinal axis. 16. A method for blade tip clearance control of a gas turbine engine, comprising: circumferentially alternating a multiple of floating air seal segments with a multiple of supported air seal segments. 17. The method as recited in claim 16, further comprising: supporting the multiple of supported air seal segments with respect to a shroud assembly. 18. The method as recited in claim 17, further comprising: constraining the multiple of floating air seal segments with respect to the shroud assembly.