Outer diameter platform cooling hole system and assembly
An airfoil component is described herein. The airfoil component may include an OD platform comprising a gaspath face and a non-gaspath face coupled together via a plurality of cooling holes. The airfoil component may include an airfoil extending in from the outer diameter platform. The plurality of cooling holes comprises a plurality of groups of cooling holes disposed in the outer diameter platform proximate a suction side of the airfoil and a pressure side of the airfoil.
1. An airfoil component comprising:
an outer diameter platform comprising:
a non-gaspath face;
a gaspath face coupled to the non-gaspath face via a plurality of cooling holes; and
an airfoil extending from the outer diameter platform, wherein the plurality of cooling holes comprise a plurality of groups of cooling holes disposed in the outer diameter platfortii proximate a suction side of the airfoil and a pressure side of the airfoil, wherein a plenum is formed adjacent to the non-gaspath face, wherein the plurality of cooling holes are coupled to the plenum;
wherein a second group of the plurality of cooling holes is disposed in the outer diameter platform proximate the pressure side and near a leading edge of the airfoil,
wherein the second group of the plurality of cooling holes has five cooling holes disposed within two rows.
2. The airfoil component of claim 1 , wherein the airfoil component is a first stage turbine vane.
3. The airfoil component of claim 1 , wherein a first group of the plurality of cooling holes is disposed in the outer diameter platform proximate the suction side.
4. The airfoil component of claim 3 , wherein the first group of the plurality of cooling holes has four cooling holes.
5. The airfoil component of claim 1 , wherein the two rows are perpendicular to each other.
6. The airfoil component of claim 1 , wherein a third group of the plurality of cooling holes is disposed in the outer diameter platform proximate the suction side and near a center of the airfoil.
7. The airfoil component of claim 6 , wherein the third group of the plurality of cooling holes has two cooling holes.
8. The airfoil component of claim 1 , wherein a fourth group of the plurality of cooling holes is disposed in the outer diameter platform proximate the suction side and near a trailing edge of the airfoil.
9. The airfoil component of claim 8 , wherein the fourth group of the plurality of cooling holes has two cooling holes.
10. The airfoil component of claim 1 , wherein a fifth group of the plurality of cooling holes is disposed in the outer diameter platform proximate a leading edge of the airfoil.
11. The airfoil component of claim 10 , wherein the fifth group of the plurality of cooling holes has three cooling holes.
12. The airfoil component of claim 1 , wherein the plurality of cooling holes are configured to eject coolant in a direction that film cools gaspath exposed surfaces of the outer diameter platform.
13. The airfoil component of claim 1 , wherein the plurality of cooling holes are formed in substantial conformance with outer diameter platform cooling hole locations, wherein the locations of the cooling holes are described in terms of Cartesian coordinates defined by along x, y, and z axes and the coordinates of the cooling holes are:
Hole No.
X
Y
Z
First Hole
0.406
0.808
2.493
Second Hole
0.278
0.884
2.504
Third Hole
0.263
0.747
2.508
Fourth Hole
0.250
0.597
2.510
Fifth Hole
0.237
0.138
2.500
Sixth Hole
0.222
0.292
2.509
Seventh Hole
0.237
0.450
2.510
Eighth Hole
1.326
0.440
2.347
Ninth Hole
1.187
0.324
2.356
Tenth Hole
1.050
0.209
2.377
Eleventh Hole
0.913
0.094
2.394
Twelfth Hole
1.424
0.982
2.341
Thirteenth Hole
1.274
0.875
2.344
Fourteenth Hole
1.431
1.217
2.327
Fifteenth Hole
1.313
1.250
2.321.
14. A gas turbine engine comprising:
a compressor section;
a combustor section; and
a turbine section including a plurality of airfoils, wherein each airfoil projects from an outer diameter platform;
the outer diameter platform comprising:
a non-gaspath face; and
a gaspath face coupled to the non-gaspath face via a plurality of cooling holes,
wherein the plurality of cooling holes comprise a plurality of groups of cooling holes disposed in the outer diameter platform proximate a suction side of a vane and a pressure side of the vane:
wherein a second group of the plurality of cooling holes is disposed in the outer diameter platform proximate the pressure side and near a leading edge of the airfoil,
wherein the second group of the plurality of cooling holes has five cooling holes disposed within two rows.
15. The gas turbine engine of claim 14 , further comprising five groups of cooling holes.
16. The gas turbine engine of claim 15 , wherein two of the five groups of cooling holes are disposed in the outer diameter platform on the pressure side and proximate a leading edge of the airfoil, wherein three of the five groups of cooling holes are disposed in the outer diameter platform proximate the suction side of the airfoil, wherein a first group of cooling holes disposed in the outer diameter platform on the suction side of the airfoil is located proximate the leading edge of the airfoil, wherein a second group of cooling holes disposed in outer diameter platform on the suction side of the airfoil is located towards a middle section of the airfoil, and wherein a third group of cooling holes disposed in the outer diameter platform on the suction side of the airfoil are located proximate a trailing edge of the airfoil.
17. The gas turbine engine of claim 14 , wherein the plurality of cooling holes are formed in substantial conformance with outer diameter platform cooling hole locations, wherein the locations of the cooling holes are described in terms of Cartesian coordinates defined by along x, y, and z axes and the coordinates of the cooling holes are:
Hole No.
X
Y
Z
First Hole
0.406
0.808
2.493
Second Hole
0.278
0.884
2.504
Third Hole
0.263
0.747
2.508
Fourth Hole
0.250
0.597
2.510
Fifth Hole
0.237
0.138
2.500
Sixth Hole
0.222
0.292
2.509
Seventh Hole
0.237
0.450
2.510
Eighth Hole
1.326
0.440
2.347
Ninth Hole
1.187
0.324
2.356
Tenth Hole
1.050
0.209
2.377
Eleventh Hole
0.913
0.094
2.394
Twelfth Hole
1.424
0.982
2.341
Thirteenth Hole
1.274
0.875
2.344
Fourteenth Hole
1.431
1.217
2.327
Fifteenth Hole
1.313
1.250
2.321.
18. An apparatus, comprising:
an outer diameter platform comprising:
a non-gaspath face; and
a gaspath face coupled to the non-gaspath face via a plurality of cooling holes; and an airfoil extending from the outer diameter platform, wherein the plurality of cooling holes are formed in substantial conformance with platform cooling hole locations, wherein the locations of the cooling holes are described in terms of Cartesian coordinates defined by along x, y, and z axes and the coordinates of the cooling holes are:
Hole No.
X
Y
Z
First Hole
0.406
0.808
2.493
Second Hole
0.278
0.884
2.504
Third Hole
0.263
0.747
2.508
Fourth Hole
0.250
0.597
2.510
Fifth Hole
0.237
0.138
2.500
Sixth Hole
0.222
0.292
2.509
Seventh Hole
0.237
0.450
2.510
Eighth Hole
1.326
0.440
2.347
Ninth Hole
1.187
0.324
2.356
Tenth Hole
1.050
0.209
2.377
Eleventh Hole
0.913
0.094
2.394
Twelfth Hole
1.424
0.982
7.341
Thirteenth Hole
1.274
0.875
2.344
Fourteenth Hole
1.431
1.217
2.327
Fifteenth Hole
1.313
1.250
2.321.
19. The apparatus of claim 18 , wherein the plurality of cooling holes comprise a plurality of groups of cooling holes disposed in the outer diameter platform proximate a suction side of a vane and a pressure side of the vane; wherein a second group of the plurality of cooling holes is disposed in the outer diameter platform proximate the pressure side and near a leading edge of the airfoil, wherein the second group of the plurality of cooling holes has five cooling holes disposed within two rows.