Segmented rim seal spacer for a gas turbine engine
A seal segment for a gas turbine engine includes a first axial span that extends between the first radial span and the second radial span. A second axial span extends between the first radial span and the second radial span, the first radial span, the second radial span, the first axial span and the second axial span forming a torque box.
1. A seal segment for a gas turbine engine, comprising:
a first radial span;
a second radial span;
a first axial span that extends between said first radial span and said second radial span;
a second axial span that extends between said first radial span and said second radial span, said first radial span, said second radial span, said first axial span, and said second axial span form a torque box;
a seal span that extends between said first radial span and said second radial span, said seal span including a multiple of knife edge seals, said seal span includes at least one aperture.
2. The seal segment as recited in claim 1 , wherein said second radial span is generally parallel to said first radial span.
3. The seal segment as recited in claim 1 , wherein said second radial span includes at least one aperture.
4. The seal segment as recited in claim 1 , further comprising a first and second flow discourager that respectively extends from said first radial span and said second radial span.
5. A seal segment for a gas turbine engine, comprising:
a first radial span;
a second radial span;
a first axial span that extends between said first radial span and said second radial span;
a second axial span that extends between said first radial span and said second radial span, said first radial span, said second radial span, said first axial span, and said second axial span form a torque box; and
an internal beam between said first radial span and said second radial span, said internal beam is arranged between said first axial span and said second axial span, said internal beam includes at least one aperture.
6. A seal segment for a gas turbine engine, comprising:
a first radial span;
a second radial span;
a first axial span that extends between said first radial span and said second radial span;
a second axial span that extends between said first radial span and said second radial span, said first radial span, said second radial span, said first axial span, and said second axial span form a torque box; and
a first and second axial support that respectively extend from said first radial span and said second radial span, a groove within said first and second axial support, said groove operable to receive a wire seal.
7. A section within a gas turbine engine, comprising:
a first rotor disk mounted along a longitudinal engine axis;
a second rotor disk along said longitudinal engine axis; and
a segmented interstage seal assembly axially between said first rotor disk and said second rotor disk, said segmented interstage seal assembly including a multiple of seal segments, each of said multiple of seal segments form a torque box, said segmented interstage seal assembly is operable to direct secondary cooling air from a full ring shroud assembly toward said second rotor disk.
8. The section as recited in claim 7 , wherein each of said multiple of seal segments are circumferentially engaged with an adjacent seal segment.
9. The section as recited in claim 8 , further comprising a shiplap interface between each of said multiple of seal segments.
10. The section as recited in claim 7 , further comprising a first and second flow discourager that extends from each of said multiple of seal segments to seal with said respective first rotor disk and second rotor disk.
11. The section as recited in claim 7 , wherein each of said multiple of seal segments includes a multiple of knife edge seals.
12. The section as recited in claim 7 , further comprising an internal beam within said torque box of each of said multiple of seal segments.
13. The section as recited in claim 7 , wherein said segmented interstage seal assembly is supported on a pilot diameter of said first rotor disk and said second rotor disk.
14. The section as recited in claim 7 , further comprising an anti-rotation tab that extends from at least one of said multiple of seal segments, said anti-rotation tab interfaces with a stop on at least one of said first rotor disk and said second rotor disk.