Featherseal having tapered radial portion
A section of a gas turbine engine according to an exemplary aspect of this disclosure includes, among other things, a vane assembly including a featherseal slot. The section further includes a featherseal at least partially received in the featherseal slot. The featherseal includes a radial portion having at least one tapered side.
1. A section of a gas turbine engine, comprising:
a vane assembly including a featherseal slot; and
a featherseal at least partially received in the featherseal slot, the featherseal including a radial portion having opposed first and second circumferential sides, each of the first and second circumferential sides having a taper, the taper of one of the first and second circumferential sides being emphasized such that the emphasized taper is provided over a larger radial dimension of the radial portion as compared to the taper that is not emphasized, the emphasized taper corresponding to a circumferential incline of the featherseal.
2. The section as recited in claim 1 , wherein:
the radial portion of the featherseal extends outward from the axial portion of the featherseal to the end of the radial portion by a radial distance;
a taper of the first circumferential side begins within a range of 0.62-0.72 of the radial distance and extends to the end of the radial portion; and
a taper of the second circumferential side begins within a range of 0.38-0.48 of the radial distance and extends to the end of the radial portion.
3. The section as recited in claim 2 , wherein the taper of the first circumferential side is provided by a first angle and the taper of the second circumferential side is provided by a second angle different in magnitude than the first angle.
4. The section as recited in claim 3 , wherein the first angle is within a range of 7.9-8.1 degrees and the second angle is within a range of 8.2-8.4 degrees.
5. A featherseal, comprising:
an axial portion; and
a radial portion having opposed first and second circumferential sides, each of the first and second circumferential sides having a taper, the taper of one of the first and second circumferential sides being emphasized such that the emphasized taper is provided over a larger radial dimension of the radial portion as compared to the taper that is not emphasized, the emphasized taper corresponding to a circumferential incline of the featherseal,
wherein the radial portion is asymmetrical, and
wherein the radial portion of the featherseal extends outward from the axial portion of the featherseal to an end of the radial portion by a radial distance,
wherein a taper of the first circumferential side begins within a range of 0.62-0.72 of the radial distance and extends to the end of the radial portion, and
wherein a taper of the second circumferential side begins within a range of 0.38-0.48 of the radial distance and extends to the end of the radial portion.
6. The featherseal as recited in claim 5 , wherein the taper of the first circumferential side is provided by a first constant angle, and the taper of the second circumferential side is provided by a second constant angle different in magnitude than the first constant angle.
7. The featherseal as recited in claim 6 , wherein the first constant angle is within a range of 7.9-8.1 degrees and the second constant angle is within a range of 8.2-8.4 degrees.
8. The featherseal as recited in claim 5 , wherein a single, monolithic structure provides both the axial portion and the radial portion of the featherseal.
9. The featherseal as recited in claim 8 , wherein the monolithic structure includes a bend between the axial portion and the radial portion of the featherseal.