Turbine vane assembly with ceramic matrix composite components mounted to case
A vane assembly for a gas turbine engine is provided having an outer casing and an inner casing radially spaced apart from the outer casing. An airfoil extends radially between the outer casing and the inner casing. The airfoil includes a spar having an outer endwall positioned adjacent the outer casing and an inner endwall positioned adjacent the inner casing. A pressure side and a suction side extend between the inner endwall and the outer endwall. A ceramic matrix composite cover has a pressure side extending along the pressure side of the spar and a suction side extending along the suction side of the spar.
1. A turbine vane assembly for a gas turbine engine, the assembly comprising:
a turbine vane support made from metallic materials, the turbine vane support including an outer mount panel that extends at least partway around a central axis and a load transfer flange that extends radially-inwardly from the outer mount panel, and
a gas path heat shield made from ceramic matrix composite materials, the gas path heat shield including (i) an airfoil having a pressure side wall and a suction side wall and (ii) an end wall having a pressure side portion that extends circumferentially from the pressure side wall of the airfoil and a suction side portion that extends circumferentially from the suction side wall of the airfoil, the suction side portion of the end wall being a thickened suction side portion with a radially-measured thickness greater than the pressure side portion of the end wall, wherein the thickened suction side portion of the endwall included in the gas path heat shield engages the load transfer flange of the turbine vane support to provide an aero-load transfer interface configured to carry circumferentially directed aerodynamic loads applied to the pressure side wall of the airfoil from the gas path heat shield to the turbine vane support,
wherein the load transfer flange includes a load transfer pad extending circumferentially towards the thickened suction side portion of the end wall to form a load transfer interface, and wherein the thickened suction side portion of the end wall engages the load transfer pad.
2. The turbine vane assembly of claim 1 , wherein the suction side wall included in the airfoil has a circumferential thickness greater than a circumferential thickness of the pressure side wall included in the airfoil.
3. The turbine vane assembly of claim 2 , wherein the airfoil and the outer end wall of the gas path heat shield are co-infiltrated with ceramic matrix material such that the gas path heat shield is a one piece, integral component.
4. The turbine vane assembly of claim 1 , wherein the turbine vane support includes a spar that extends radially-inwardly from the mount panel through the gas path heat shield.
5. The turbine vane assembly of claim 1 , further comprising:
a pressure side fillet extending between the pressure side wall of the airfoil and the pressure portion of the endwall, and
a suction side fillet extending between the suction side wall of the airfoil and the suction portion of the endwall, wherein the suction side fillet is a thickened fillet with a angularly-measured thickness greater than the pressure side fillet, wherein the angularly-measured thickness is measured at an angle between a circumferential direction and a radial direction.
6. The turbine vane assembly of claim 1 , further comprising a locating pad extending radially-inwardly from the outer mount panel and engaging a radially-outward surface of the suction side portion of the end wall.
7. The turbine vane assembly of claim 1 , further comprising a flange protector wall extending circumferentially from the gas path heat shield.
8. The turbine vane assembly of claim 7 , wherein the flange protector wall extends circumferentially from the pressure side portion of the endwall and is configured to engage the load transfer flange of an adjacent turbine vane assembly.
9. The turbine vane assembly of claim 8 , wherein the flange protector wall has a circumferential thickness less than a circumferential thickness of the pressure side portion of the endwall.
10. The turbine vane assembly of claim 7 , wherein the flange protector wall extends circumferentially from the pressure side wall of the airfoil and is configured to engage the load transfer flange of an adjacent turbine vane assembly.
11. The turbine vane assembly of claim 1 , wherein a circumferentially facing wall of the thickened suction side portion of the endwall engages a circumferentially facing wall of the load transfer flange.
12. A turbine vane assembly for a gas turbine engine, the assembly comprising:
a turbine vane support made from metallic materials, the turbine vane support including an outer mount panel that extends at least partway around a central axis and a load transfer flange that extends radially-inwardly from the outer mount panel,
a gas path heat shield made from ceramic matrix composite materials, the gas path heat shield including (i) an airfoil having a pressure side wall and a suction side wall, the suction side wall having a circumferential thickness greater than a circumferential thickness of the pressure side wall and (ii) an end wall having a pressure side portion that extends circumferentially from the pressure side wall of the airfoil and a suction side portion that extends circumferentially from the suction side wall of the airfoil, the suction side portion of the end wall being a thickened suction side portion with a radially-measured thickness greater than the pressure side portion of the end wall, wherein the thickened suction side portion of the endwall included in the gas path heat shield engages the load transfer flange of the turbine vane support,
a flange protector wall extending circumferentially from a circumferential face of the pressure side portion of the endwall and configured to engage the load transfer flange of an adjacent turbine vane assembly, and
a spar that extends radially-inwardly from the mount panel through the gas path heat shield
wherein the load transfer flange includes a load transfer pad extending circumferentially towards the thickened suction side portion of the end wall to form a load transfer interface, and wherein the thickened suction side portion of the end wall engages the load transfer pad.
13. The turbine vane assembly of claim 12 , wherein the airfoil and the outer end wall of the gas path heat shield are co-infiltrated with ceramic matrix material such that the gas path heat shield is a one piece, integral component.
14. The turbine vane assembly of claim 12 , further comprising:
a pressure side fillet extending between the pressure side wall of the airfoil and the pressure portion of the endwall, and
a suction side fillet extending between the suction side wall of the airfoil and the suction portion of the endwall, wherein the suction side fillet is a thickened fillet with a angularly-measured thickness greater than the pressure side fillet, wherein the angularly-measured thickness is measured at an angle between a circumferential direction and a radial direction.
15. The turbine vane assembly of claim 12 , further comprising a locating pad extending radially-inwardly from the outer mount panel and engaging a radially-outward surface of the suction side portion of the end wall.
16. The turbine vane assembly of claim 12 , wherein the flange protector wall has a circumferential thickness less than a circumferential thickness of the pressure side portion of the endwall.
17. A turbine vane assembly for a gas turbine engine, the assembly comprising:
a turbine vane support made from metallic materials, the turbine vane support including an outer mount panel that extends at least partway around a central axis and a load transfer flange that extends radially-inwardly from the outer mount panel, and
a gas path heat shield made from ceramic matrix composite materials, the gas path heat shield comprising:
an airfoil having a pressure side wall and a suction side wall, the suction side wall having a circumferential thickness greater than a circumferential thickness of the pressure side wall, and
an end wall having a pressure side portion that extends circumferentially from the pressure side wall of the airfoil and a suction side portion that extends circumferentially from the suction side wall of the airfoil, the suction side portion of the end wall being a thickened suction side portion with a radially-measured thickness greater than the pressure side portion of the end wall, the thickened suction side portion of the end wall engages the load transfer flange of the turbine vane support to provide an aero-load transfer interface configured to carry circumferentially directed aerodynamic loads applied to the pressure side wall of the airfoil from the gas path heat shield to the turbine vane support,
wherein the load transfer flange includes a load transfer pad extending circumferentially towards the thickened suction side portion of the end wall to form a load transfer interface, and
wherein the thickened suction side portion of the end wall engages the load transfer pad.
18. The turbine vane assembly of claim 17 , further comprising a flange protector wall extending circumferentially from the gas path heat shield.
19. The turbine vane assembly of claim 17 , wherein the airfoil and the outer end wall of the gas path heat shield are co-infiltrated with ceramic matrix material such that the gas path heat shield is a one piece, integral component.