Turbine blade attachment curved rib stiffeners
The present disclosure provides a fir tree coupling for gas turbine engine parts comprising a load beam having a longitudinal axis, a rounded base, a first side, and a second side, wherein the rounded base has a radius of curvature from the first side to the second side, a tooth running parallel to the longitudinal axis and disposed on the first side of the load beam. The fir tree coupling may comprise a channel through the rounded base across a portion of the radius of curvature from the first side to the second side. The channel may comprise a sidewall having a sidewall step cut into a portion of the channel sidewall.
1. A fir tree coupling comprising: a load beam having a longitudinal axis, a rounded base, a first side, and a second side, wherein the rounded base has a radius of curvature from the first side to the second side, a tooth running parallel to the longitudinal axis and disposed on the first side of the load beam, and a plurality of channels, extending transverse to the longitudinal axis from the first side to the second side of the load beam, defining a plurality of rounded base portions therebetween.
2. The fir tree coupling of claim 1 , wherein the plurality of channels comprises a sidewall having a sidewall step cut into a portion of the sidewall.
3. The fir tree coupling of claim 1 , wherein the plurality of channels comprises at least one of a concave sidewall having a concave curvature into the plurality of rounded base portions or a vertical sidewall extending perpendicular into the rounded base from the plurality of rounded base portions.
4. The fir tree coupling of claim 1 , wherein the plurality of channels comprises a tapered sidewall wherein the tapered sidewall extends at a non-orthogonal angle into the rounded base from the plurality of rounded base portions.
5. The fir tree coupling of claim 1 , wherein the plurality of channels is disposed at a non-orthogonal angle to the longitudinal axis of the load beam.
6. The fir tree coupling of claim 1 , wherein the tooth includes a bearing surface.
7. The fir tree coupling of claim 1 , wherein the load beam comprises a top surface and a cooling passage passing through the load beam from the rounded base to the top surface.
8. The fir tree coupling of claim 1 , wherein the load beam comprises at least one of nickel, nickel alloy, titanium, or titanium alloy.
9. The fir tree coupling of claim 1 , wherein the load beam comprises a monocrystalline material.
10. A turbine blade assembly for a gas turbine engine comprising:
a platform having a dorsal surface and a ventral surface;
a turbine blade extending from the dorsal surface;
a fir tree coupling extending from the ventral surface, the fir tree coupling comprising a load beam having a longitudinal axis, a rounded base, a first side, and a second side,
wherein the rounded base has a radius of curvature from the first side to the second side,
a tooth running parallel to the longitudinal axis and disposed on the first side of the load beam,
and a plurality of channels, extending transverse to the longitudinal axis from the first side to the second side of the load beam, defining a plurality of rounded base portions therebetween.
11. The turbine blade assembly of claim 10 , wherein the plurality of channels comprises a sidewall having a sidewall step cut into a portion of the sidewall.
12. The turbine blade assembly of claim 10 , wherein the plurality of channels comprises at least one of a concave sidewall having a concave curvature into the plurality of rounded base portions or a vertical sidewall extending perpendicular into the rounded base from the plurality of rounded base portions.
13. The turbine blade assembly of claim 10 , wherein, the plurality of channels comprises a tapered sidewall wherein the tapered sidewall extends at a non-orthogonal angle into the rounded base from the plurality of rounded base portions.
14. The turbine blade assembly of claim 10 , wherein the plurality of channels is disposed at a non-orthogonal angle to the longitudinal axis of the load beam.
15. The turbine blade assembly of claim 10 , wherein the fir tree coupling comprises at least one of nickel, nickel alloy, titanium, or titanium alloy.
16. The turbine blade assembly of claim 10 , wherein the fir tree coupling comprises a monocrystalline material, wherein the fir tree coupling comprises a first cooling passage in fluid communication with a second cooling passage within at least one of the platform or the turbine blade.
17. A method of manufacturing a fir tree coupling comprising:
forming a load beam having a longitudinal axis, a rounded base, a first side, a second side, and tooth running parallel to the longitudinal axis and disposed on the first side of the load beam,
forming a radius of curvature on the rounded base from the first side to the second side, and
forming a plurality of channels, extending transverse to the longitudinal axis from the first side to the second side of the load beam and across the radius of curvature, defining a plurality of rounded base portions therebetween.
18. The method of claim 17 , wherein the plurality of channels is disposed at a non-orthogonal angle to the longitudinal axis of the load beam.