Beveled coverplate
A gas turbine engine includes a platform that has a gas path side, a non-gas path side, a first mate face, and a second mate face. The second mate face has a beveled edge sloping towards the first mate face. The gas turbine engine also includes a coverplate that includes a first bend, a flat portion substantially parallel to the first mate face and a first wing substantially parallel to the second mate face.
1. A gas turbine engine component comprising:
a platform having a gas path side, a non-gas path side, a platform floor, a first mate face parallel to the platform floor, and a second mate face having a beveled edge sloping towards the first mate face such that the second mate face forms a first angle with the first mate face; and
a coverplate including a first bend of a second angle that is equal to the first angle, a flat portion coupled to the first mate face and parallel to the first mate face, and a first wing coupled to the second mate face and parallel to the second mate face,
wherein the platform and the coverplate define a cavity therebetween, and a first distance between the first wing and the platform floor is greater than a second distance between the flat portion and the platform floor.
2. The gas turbine engine component of claim 1 , wherein the platform is an outer diameter platform.
3. The gas turbine engine component of claim 1 , wherein the platform is an inner diameter platform.
4. The gas turbine engine component of claim 1 , wherein the coverplate defines an impingement cooling hole.
5. The gas turbine engine component of claim 1 , wherein the cavity includes an opening for at least one of channel flow cooling and axial flow cooling.
6. The gas turbine engine component of claim 1 , wherein the second angle is between 10 degrees and 45 degrees.
7. The gas turbine engine component of claim 6 , wherein the second angle is between 20 degrees and 30 degrees.
8. The gas turbine engine component of claim 1 , further comprising a cooling hole defined by the first wing.
9. The gas turbine engine component of claim 1 , further comprising:
a third mate face on the non-gas path side, the third mate face having a beveled edge partially facing the beveled edge of the second mate face,
wherein the coverplate has a second bend and a second wing that partially faces the first wing with the second wing parallel to the third mate face.
10. The gas turbine engine component of claim 9 , wherein the second bend is bent at an angle and the first bend is bent at a transverse of the angle.
11. The gas turbine engine component of claim 9 , wherein the first wing defines a first cooling hole and the second wing defines a second cooling hole.
12. The gas turbine engine component of claim 1 , wherein the platform and the coverplate define an opening to a core of the gas turbine engine component.
13. The gas turbine engine component of claim 1 , further comprising a leading edge and a trailing edge wherein the first bend extends from the leading edge to the trailing edge.
14. The gas turbine engine component of claim 1 , further comprising an airfoil positioned on the gas path side of the platform.
15. A gas turbine engine component comprising:
a platform having a gas path side, a non-gas path side, a platform floor, a first mate face parallel to the platform floor, a second mate face having a beveled edge sloping towards the first mate face such that the second mate face forms a first angle with the first mate face, and a third mate face adjacent the second mate face on the non-gas path side; and
a coverplate including a first bend of a second angle that is equal to the first angle, a flat portion coupled to the first mate face and parallel to the first mate face, a first wing coupled to the second mate face and parallel to the second mate face, a second bend, and a second wing parallel to the third mate face,
wherein the platform and the coverplate define a cavity therebetween, and a first distance between the first wing and the platform floor is greater than a second distance between the flat portion and the platform floor.
16. The gas turbine engine component of claim 1 , wherein the beveled edge of the platform contacts and is coupled to the first wing of the coverplate.