Locating plate for use with turbine shroud assemblies
A turbine assembly includes a turbine case, a vane assembly, and a locating plate. The vane assembly includes a first vane and an outer platform arranged on a radially outer end of the first vane, the outer platform including a first anti-rotation protrusion extending radially outwardly away from a radially outwardly-facing surface of the outer platform. The locating plate is radially outside of the vane assembly and includes a main wall and two anti-rotation extensions extending radially inwardly. The first anti-rotation protrusion of the vane assembly is arranged to engage with one of the anti-rotation extensions so as to block circumferential movement of the vane assembly relative to the locating plate.
1. A turbine assembly for use with a gas turbine engine, the turbine assembly comprising
a turbine case arranged circumferentially around an axis,
a vane assembly arranged circumferentially at least partway around the axis and arranged radially inwardly of the turbine case, the vane assembly including a first vane and an outer platform arranged on a radially outer end of the first vane, the outer platform including a first anti-rotation protrusion extending radially outwardly away from a radially outwardly-facing surface of the outer platform, and
a locating plate arranged circumferentially at least partway around the axis and coupled with the turbine case radially outward of the vane assembly, the locating plate including a main wall, a first anti-rotation extension extending radially inwardly away from an aft end of the main wall, and a second anti-rotation extension extending radially inwardly away from the aft end of the main wall and circumferentially spaced apart from the first anti-rotation extension,
wherein the first anti-rotation protrusion of the vane assembly is arranged to engage with one of the first anti-rotation extension and the second anti-rotation extension of the locating plate so as to block circumferential movement of the vane assembly relative to the locating plate.
2. The turbine assembly of claim 1 , wherein the locating plate extends partway circumferentially around the axis, wherein the main wall includes a first circumferential side and second circumferential side circumferentially opposite the first circumferential side, and wherein the aft end of the main wall extends between the first circumferential side and the second circumferential side.
3. The turbine assembly of claim 2 , wherein the vane assembly further includes a second anti-rotation protrusion circumferentially spaced apart from the first anti-rotation protrusion.
4. The turbine assembly of claim 3 , wherein the first anti-rotation extension includes a first extension surface that faces a first circumferential direction and the first anti-rotation protrusion includes a first protrusion surface that faces a second circumferential direction opposite the first circumferential direction, and wherein the first extension surface is configured to contact the first protrusion surface so as to block circumferential movement of the vane assembly relative to the locating plate in response to circumferential forces acting on the vane assembly.
5. The turbine assembly of claim 4 , wherein the second anti-rotation extension includes a second extension surface that faces the second circumferential direction and the second anti-rotation protrusion includes a second protrusion surface that faces the first circumferential direction, and wherein the second extension surface is configured to contact the second protrusion surface so as to further block circumferential movement of the vane assembly relative to the locating plate in response to circumferential forces acting on the vane assembly.
6. The turbine assembly of claim 5 , wherein the first extension surface faces away from the second extension surface and the first protrusion surface faces the second protrusion surface.
7. The turbine assembly of claim 3 , wherein the outer platform of the vane assembly includes a main platform and a first flange extending radially outwardly from an aft end of the main platform, and wherein the first and second anti-rotation protrusions are arranged on the first flange.
8. The turbine assembly of claim 2 , further comprising:
a turbine shroud assembly coupled with the turbine case to define a portion of a gas path of the turbine assembly, the turbine shroud assembly including a carrier segment and a blade track segment, the carrier segment being made of metallic materials and arranged circumferentially at least partway around the axis, the carrier segment including an outer wall and a hanger extending from the outer wall and supported on the turbine case to couple the carrier segment to the turbine case,
wherein the locating plate is arranged axially forward of the carrier segment to block axially forward movement of the carrier segment and prevent separation of the hanger from the turbine case.
9. The turbine assembly of claim 8 , wherein the carrier segment further includes an anti-rotation platform extending axially away from a forward-facing surface of the outer wall, wherein the locating plate further includes an anti-rotation recess formed in the main wall of the locating plate, and wherein the anti-rotation recess is configured to receive the anti-rotation platform to block axially forward movement of the carrier segment and prevent separation of the hanger from the turbine case.
10. The turbine assembly of claim 9 , wherein the anti-rotation recess is defined by an axially forward wall, a first circumferential wall, and a second circumferential wall opposite the first circumferential wall, and wherein a first circumferential end of the anti-rotation platform of the carrier segment and a second circumferential end of the anti-rotation platform opposite the first circumferential end are configured to engage with the first and second circumferential walls, respectively, so as to block circumferential movement of the carrier segment relative to the locating plate.
11. The turbine assembly of claim 10 , wherein the anti-rotation recess further includes a first peg extending radially upwardly from a bottom surface of the anti-rotation recess, wherein the anti-rotation platform includes a first slot formed therein, and wherein the first peg is arranged within the first slot so as to secure the anti-rotation platform within the anti-rotation recess.
12. The turbine assembly of claim 11 , wherein the first slot includes a stadium shape and includes a length that is greater than a diameter of the first peg and a width that is generally equal to the diameter of the first peg so as to allow for circumferential movement of the first peg within the first slot and not allow for axial movement of the first peg within the first slot.
13. A turbine assembly for use with a gas turbine engine, the turbine assembly comprising
a turbine case arranged circumferentially around an axis,
a vane assembly arranged radially inwardly of the turbine case and including a first vane and an outer platform having a first anti-rotation protrusion extending radially outwardly away from a radially outwardly-facing surface of the outer platform, and
a locating plate coupled with the turbine case radially outward of the vane assembly, the locating plate including a main wall, a first anti-rotation extension extending radially inwardly away from an aft end of the main wall,
wherein a circumferentially facing surface of the first anti-rotation protrusion of the vane assembly is arranged to engage with and contact a circumferentially facing surface of the first anti-rotation extension of the locating plate so as to block circumferential movement of the vane assembly relative to the locating plate.
14. The turbine assembly of claim 13 , wherein the locating plate further includes a second anti-rotation extension extending radially inwardly away from the aft end of the main wall and circumferentially spaced apart from the first anti-rotation extension, wherein the vane assembly further includes a second anti-rotation protrusion circumferentially spaced apart from the first anti-rotation protrusion, and wherein the second anti-rotation protrusion of the vane assembly is arranged to engage with the second anti-rotation extension of the locating plate so as to further block circumferential movement of the vane assembly relative to the locating plate.
15. The turbine assembly of claim 14 , wherein the outer platform of the vane assembly includes a main platform and a first flange extending radially outwardly from an aft end of the main platform, and wherein the first and second anti-rotation protrusions are arranged on the first flange.
16. The turbine assembly of claim 13 , further comprising:
a turbine shroud assembly coupled with the turbine case and including a carrier segment and a blade track segment, the carrier segment including an outer wall and a hanger extending from the outer wall and supported on the turbine case to couple the carrier segment to the turbine case,
wherein the locating plate is arranged axially forward of the carrier segment to block axially forward movement of the carrier segment and prevent separation of the hanger from the turbine case.
17. The turbine assembly of claim 16 , wherein the carrier segment further includes an anti-rotation platform extending axially away from a forward-facing surface of the outer wall, wherein the locating plate further includes an anti-rotation recess formed in the main wall of the locating plate, and wherein the anti-rotation recess is configured to receive the anti-rotation platform to block axially forward movement of the carrier segment and prevent separation of the hanger from the turbine case.
18. The turbine assembly of claim 17 , wherein the anti-rotation recess is defined by an axially forward wall, a first circumferential wall, and a second circumferential wall opposite the first circumferential wall, and wherein a first circumferential end of the anti-rotation platform of the carrier segment and a second circumferential end of the anti-rotation platform opposite the first circumferential end are configured to engage with the first and second circumferential walls, respectively, so as to block circumferential movement of the carrier segment relative to the locating plate.
19. The turbine assembly of claim 18 , wherein the anti-rotation recess further includes a first peg extending radially upwardly from a bottom surface of the anti-rotation recess, wherein the anti-rotation platform includes a first slot formed therein, and wherein the first peg is arranged within the first slot so as to secure the anti-rotation platform within the anti-rotation recess.
20. A method comprising
arranging a turbine case circumferentially around an axis,
arranging a vane assembly circumferentially at least partway around the axis and radially inwardly of the turbine case, the vane assembly including a first vane and an outer platform arranged on a radially outer end of the first vane, the outer platform including a first anti-rotation protrusion extending radially outwardly away from a radially outwardly-facing surface of the outer platform,
arranging a locating plate circumferentially at least partway around the axis and coupling the locating plate with the turbine case radially outward of the vane assembly, the locating plate including a main wall, a first anti-rotation extension extending radially inwardly away from an aft end of the main wall, and a second anti-rotation extension extending radially inwardly away from the aft end of the main wall and circumferentially spaced apart from the first anti-rotation extension,
engaging the first anti-rotation protrusion of the vane assembly with one of the first anti-rotation extension and the second anti-rotation extension of the locating plate so as to block circumferential movement of the vane assembly relative to the locating plate.