Tangential rotor blade slot spacer for a gas turbine engine
A rotor disk assembly for a gas turbine engine includes a rotor disk that defines an axis, the rotor disk comprising a slot within a rim of the disk and a spacer within the slot, the spacer having a clearance feature sized to permit rotation of a rotor blade from an insertion position to an installed position.
1. A rotor disk assembly for a gas turbine engine, comprising:
a rotor disk that defines an axis, the rotor disk comprising a tangential blade slot within a rim of the disk;
a multiple of arrays of rotor blades, each rotor blade in the multiple of arrays of rotor blades comprising a blade lug that defines a maximum blade lug width; and
a spacer inserted within the tangential blade slot forming a blade slot assembly, the spacer having a clearance feature sized to permit rotation of the rotor blade 90 degrees using the clearance feature from an insertion position to an installed position, the tangential blade slot defines a maximum slot width, the slot width 5%-15% larger than the maximum blade lug width.
2. The assembly as recited in claim 1 , wherein the clearance feature is a dimple.
3. The assembly as recited in claim 1 , wherein the clearance feature is a cut.
4. The assembly as recited in claim 1 , wherein the spacer is comprised of a multiple of circumferential segments.
5. The assembly as recited in claim 1 , wherein the clearance feature is one of a multiple of clearance features, each two of the multiple of the clearance features are circumferentially spaced to receive 4 to 8 rotor blades therebetween.
6. The assembly as recited in claim 1 , wherein the slot within the rim of the disk comprises a forward rail and an aft rail spaced apart by a slot opening that is smaller than a rotor slot bottom.
7. The assembly as recited in claim 6 , wherein the forward rail and the aft rail are continuous.
8. The assembly as recited in claim 6 , wherein the spacer is comprised of a forward portion and an aft portion, each of the respective portions sized to fit through the slot opening.
9. The assembly as recited in claim 1 , further comprising a blade lock between each two arrays of the multiple of arrays of rotor blades.
10. The assembly as recited in claim 1 , wherein each array of the multiple of arrays of rotor blades comprise 4-8 rotor blades.
11. A method for assembling a rotor disk assembly, comprising the steps of:
providing a disk having a tangential blade slot;
installing a spacer within the tangential blade slot forming a blade slot assembly, the spacer having a clearance feature sized to allow for blade rotation from an insertion position to an installed position;
inserting the blade in the tangential blade slot assembly proximate to the clearance feature;
rotating the blade 90 degrees using the clearance feature to the installed position.
12. The method as recited in claim 11 , further comprising installing the spacer in a multiple of circumferential segments.
13. The method as recited in claim 11 , further comprising installing the spacer in a multiple of portions, the multiple of portions comprising a forward portion and an aft portion, each of the respective portions sized to fit through a slot opening of the tangential blade slot.
14. The method as recited in claim 11 , wherein the clearance feature is a dimple.
15. The method as recited in claim 11 , wherein the clearance feature is a cut.
16. The method as recited in claim 11 , further comprising inserting a lock into the blade slot assembly.
17. The method according to claim 16 , further comprising inserting a plurality of blades prior to inserting the lock.