Lock for retaining minidisks with rotors of a gas turbine engine

1. An assembly, comprising;

a rotor, comprising:

a disk having a central axis;

an airfoil radially extending from the disk;

a bayonet tab extending radially from the disk; and

a lock having a short tab and a long tab, the short and long tabs extending radially from the disk with respect to the central axis and in an axial direction with respect to the central axis, the long tab having a first axial length and the short tab having a second axial length, wherein the first axial length is greater than the second axial length, and

a minidisk operatively associated with the rotor, the minidisk including a first locking tab formed thereon;

wherein the first locking tab on the minidisk aligns with a first space separating the bayonet tab and the lock of the rotor;

wherein the minidisk moves in a first direction such that the first locking tab of the minidisk moves through the first space separating the bayonet tab and the lock of the rotor;

wherein the minidisk rotates until the first locking tab on the minidisk aligns with a second space separating the short tab and the long tab of the lock; and

wherein the minidisk moves in a second direction opposite to the first direction until the first locking tab on the minidisk is positioned between the short tab and the long tab of the lock.

2. The rotor of claim 1 , wherein the second axial length of the short tab of the lock is greater than an axial width of the bayonet tab.

3. The rotor of claim 1 , wherein a first circumferential distance around the disk separating the bayonet tab and the lock is equal to a second circumferential distance around the disk separating the short tab and the long tab of the lock.

4. The rotor of claim 1 , wherein the bayonet tab, the short tab, and the long tab extend radially outward from the disk of the rotor with respect to the central axis.

5. The rotor of claim 1 , wherein a plurality of the locks are evenly distributed about the circumference of the disk.

6. The rotor of claim 1 , wherein a plurality of the bayonet tabs are evenly distributed about the circumference of the disk.

7. The rotor of claim 1 , wherein the minidisk has a second locking tab proximate the bayonet tab of the rotor.

8. The rotor of claim 1 , wherein a plurality of the locking tabs are evenly distributed about the circumference of the minidisk.

9. The rotor of claim 1 , wherein the rotor is a turbine of a gas turbine engine and the minidisk is an air seal.

10. The rotor of claim 1 , wherein the lock further includes a connector spanning between and joining the short and long tabs of the lock.

11. A method of assembling a rotor and a minidisk, comprising:

aligning a first locking tab on the minidisk with a first space separating a bayonet tab and a lock of the rotor, the lock of the rotor comprising a short tab and a long tab;

moving the minidisk in a first direction such that the first locking tab of the minidisk moves through the first space separating the bayonet tab and the lock of the rotor;

rotating the minidisk until the first locking tab on the minidisk is aligned with a second space separating the short tab and the long tab of the lock of the rotor; and

moving the minidisk in a second direction opposite to the first direction until the first locking tab on the minidisk is positioned between the short tab and the long tab of the lock of the rotor.

12. The method of claim 11 , wherein the minidisk is moved in the first direction until the minidisk comes in contact with the bayonet tab of the rotor.

13. The method of claim 11 , wherein the minidisk is rotated until the first locking tab on the minidisk comes into contact with the long tab of the lock of the rotor.

14. The method of claim 11 , wherein the minidisk is moved in the second direction until a second locking tab on the minidisk comes into contact with the bayonet tab of the rotor.

15. The method of claim 11 , further including disassembling the rotor and the minidisk; moving the minidisk in the first direction such that the first locking tab of the minidisk is moved from between the short tab and long tab of the lock; rotating the minidisk until the first locking tab is aligned with the first space separating the bayonet tab and the lock of the rotor; and moving the minidisk in the second direction to free the minidisk from the rotor.

16. The method of claim 15 , wherein the minidisk is moved in the first direction until the minidisk contacts the bayonet tab.

17. The method of claim 15 , wherein the minidisk is rotated until the first locking tab contacts the long tab of the lock.

18. A gas turbine engine, comprising:

a compressor;

a combustor downstream of the compressor;

a turbine downstream of the combustor, wherein at least one of the compressor and the turbine includes a rotor including a disk, a plurality of airfoils radially extending from the disk, a bayonet tab radially extending from the disk, a lock radially extending from the disk, and the lock including a short tab and a long tab, and a minidisk operatively associated with the rotor, the minidisk including a first locking tab positioned between the short tab and the long tab of the lock; and

wherein the first locking tab on the minidisk aligns with a first space separating the bayonet tab and the lock of the rotor;

wherein the minidisk moves in a first direction such that the first locking tab of the minidisk moves through the first space separating the bayonet tab and the lock of the rotor;

wherein the minidisk rotates until the first locking tab on the minidisk aligns with a second space separating the short tab and the long tab of the lock; and

wherein the minidisk moves in a second direction opposite to the first direction until the first locking tab on the minidisk is positioned between the short tab and the long tab of the lock.

19. The gas turbine engine of claim 18 , wherein the rotor is a first stage of the turbine and the minidisk is an air seal directing a flow of compressed air from the compressor to the turbine.