초록

A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation and a plurality of core gas path seals which extend from the rotor ring, each of the plurality of core gas path seals extend from the rotor ring at an interface, the interface defined along a spoke.

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1. A spacer for a gas turbine engine comprising: a rotor ring defined along an axis of rotation; anda plurality of core gas path seals which extend from said rotor ring, each of said plurality of core gas path seals extend from said rotor ring at an interface, said interface defined along a spoke, a

1. A spacer for a gas turbine engine comprising: a rotor ring defined along an axis of rotation; anda plurality of core gas path seals which extend from said rotor ring, each of said plurality of core gas path seals extend from said rotor ring at an interface, said interface defined along a spoke, and wherein said interface includes a heat treat transition. 2. The rotor as recited in claim 1, wherein said rotor ring is manufactured of a first material and said plurality of core gas path seals are manufactured of a second material, said first material different than said second material. 3. The spacer as recited in claim 1, wherein each spoke is parallel to said axis of rotation. 4. The spacer as recited in claim 1, wherein each spoke is angled with respect to said axis of rotation. 5. The spacer as recited in claim 1, wherein at least one of said plurality of core gas path seals includes an inlet. 6. The spacer as recited in claim 5, wherein said inlet is to a passage adjacent to said spoke. 7. A spacer for a gas turbine engine comprising: a rotor ring defined along an axis of rotation; anda plurality of core gas path seals which extend from said rotor ring, each of said plurality of core gas path seals extend from said rotor ring at an interface, said interface defined along a spoke, and wherein said interface includes a bond. 8. A spacer for a gas turbine engine comprising: a rotor ring defined along an axis of rotation and wherein said ring defines a first circumferential flange and a second circumferential flange, said second circumferential flange thicker than said first circumferential flange, and further comprising a ramped interface between said second circumferential flange and said first circumferential flange; anda plurality of core gas path seals which extend from said rotor ring, each of said plurality of core gas path seals extend from said rotor ring at an interface, said interface defined along a spoke. 9. A spool for a gas turbine engine comprising: a first rotor disk defined along an axis of rotation;a plurality of first blades which extend from said first rotor disk;a rotor ring defined along said axis of rotation, said rotor ring in contact with said first rotor disk;a plurality of core gas path seals which extend from said rotor ring, said plurality of core gas path seals adjacent said plurality of first blades, each of said plurality of core gas path seals extend from said rotor ring at an interface, said interface defined along a spoke; and a first circumferential wire seal between said plurality of core gas path seals and said plurality of first blades. 10. The spool as recited in claim 9, further comprising a wire seal between each pair of said plurality of core gas path seals. 11. The spool as recited in claim 9, wherein said plurality of core gas path seals interface with a platform of said plurality of first blades. 12. The spool as recited in claim 9, wherein each spoke is parallel to said axis of rotation. 13. The spool as recited in claim 9, wherein each spoke is angled with respect to said axis of rotation. 14. A spool for a gas turbine engine comprising: a first rotor disk defined along an axis of rotation;a plurality of first blades which extend from said first rotor disk, each of said plurality of blades extend from said first rotor disk at a first interface, said first interface defined along a first spoke;a second rotor disk defined along said axis of rotation;a plurality of second blades which extend from said second rotor disk, each of said plurality of second blades extend from said second rotor disk at a second interface, said second interface defined along a second spoke;a rotor ring defined along said axis of rotation, said rotor ring in contact with said first rotor disk and said second rotor disk; anda plurality of core gas path seals which extend from said rotor ring between said plurality of first blades and said plurality of second blades, each of said plurality of core gas path seals extend from said rotor ring at a third interface, said third interface defined along a third spoke, and wherein at least one of said plurality of core gas path seals includes an inlet in communication with a passage in communication with said second spoke and said first spoke. 15. The spool as recited in claim 14, wherein said first spoke, said second spoke and said third spoke are axially aligned. 16. A spool for a gas turbine engine comprising: a first rotor disk defined along an axis of rotation;a plurality of first blades which extend from said first rotor disk, each of said plurality of blades extend from said first rotor disk at a first interface, said first interface defined along a first spoke;a second rotor disk defined along said axis of rotation;a plurality of second blades which extend from said second rotor disk, each of said plurality of second blades extend from said second rotor disk at a second interface, said second interface defined along a second spoke;a rotor ring defined along said axis of rotation, said rotor ring in contact with said first rotor disk and said second rotor disk; a plurality of core gas path seals which extend from said rotor ring between said plurality of first blades and said plurality of second blades, each of said plurality of core gas path seals extend from said rotor ring at a third interface, said third interface defined along a third spoke; and a first circumferential wire seal between said plurality of core gas path seals and said plurality of first blades and a second circumferential wire seal between said plurality of core gas path seals and said plurality of second blades.