Life extension of power turbine disks exposed to in-service corrosion damage
A repair method ( 72 ) for extending a service life of a power turbine disk ( 12 ) having corrosion damage, wherein the power turbine ( 14 ) includes stages ( 16, 18, 20, 22 ) and interstage gaps ( 26, 28, 30, 32 ). The method ( 72 ) includes conducting a first thermal analysis ( 74 ) of a baseline configuration of a baseline disk that does not have corrosion to determine a first steady state temperature distribution ( 44 ). A corrosion damaged disk ( 12 ) is then machined ( 76 ) to a depth suitable for repairing the corrosion to form a machined disk. A second thermal analysis ( 78 ) of the machined disk is conducted to determine a second steady state temperature distribution of the machined disk. A first predicted safe cyclic life (PSCL) ( 80 ) is then calculated for disk axisymmetric features ( 1 - 10 ) of the machined disk. A second PSCL ( 82 ) is also calculated for disk firtree features ( 70 ) of the machined disk. Further, the method ( 72 ) is qualified ( 84 ) to ensure that the quality of the machined disk is consistent with a new disk.
1. A repair method for extending a service life of a power turbine disk having corrosion damage, wherein the power turbine includes stages and interstage gaps, comprising:
conducting a first thermal analysis of a baseline configuration of a baseline disk that does not have corrosion to determine a first steady state temperature distribution;
machining a corrosion damaged disk to a depth suitable for repairing the corrosion to form a machined disk;
conducting a second thermal analysis of the machined disk to determine a second steady state temperature distribution of the machined disk;
calculating a first predicted safe cyclic life (PSCL) for disk axisymmetric features of the machined disk;
calculating a second PSCL for disk firtree features of the machined disk; and
qualifying the repair method to ensure that the quality of the machined disk is consistent with a new disk.
2. The method of claim 1 , wherein the depth for machining the machined disk is established statistically.
3. The method of claim 2 , wherein the depth for machining the machined disk is established statistically by studying an observed depth of subsurface damage induced by Low Temperature Hot Corrosion (LTHC).
4. The method of claim 1 , wherein the second thermal analysis includes a determination of steady state temperature variation between the baseline configuration and worst case interstage gaps due to machining of the machined disk.
5. The method according to claim 1 , wherein the first PSCL is based on rim temperature reference points.
6. The method according to claim 1 , wherein the disk firtree features include upper, middle and lower notches of the disk firtree.
7. The method according to claim 1 , wherein the PSCL of a disk feature is ⅔ rd of a minimum life to burst.
8. A repair method for extending a service life of a power turbine disk having corrosion damage, wherein the power turbine includes stages and interstage gaps, comprising:
conducting a first thermal analysis of a baseline configuration of a baseline disk that does not have corrosion to determine a first steady state temperature distribution;
machining a corrosion damaged disk to a depth suitable for repairing the corro- sion to form a machined disk, wherein the depth for machining the disk is established statistically;
conducting a second thermal analysis of the machined disk to determine a second steady state temperature distribution of the machined disk;
calculating a first predicted safe cyclic life (PSCL) for disk axisymmetric features of the machined disk;
calculating a second PSCL for disk firtree features of the machined disk; and
qualifying the repair method to ensure that the quality of the machined disk is consistent with a new disk.
9. The method of claim 8 , wherein the depth for machining the machined disk is established statistically by studying an observed depth of subsurface damage induced by Low Temperature Hot Corrosion (LTHC).
10. The method of claim 8 , wherein the second thermal analysis includes a determination of steady state temperature variation between the baseline configuration and interstage gaps due to machining of the machined disk.
11. The method according to claim 8 , wherein the first PSCL is based on rim temperature reference points.
12. The method according to claim 8 , wherein the disk firtree features include upper, middle and lower notches of the disk firtree.
13. The method according to claim 8 , wherein the PSCL of a disk feature is ⅔ rd of a minimum life to burst.
14. A repair method for extending a service life of a power turbine disk having corrosion damage, wherein the power turbine includes stages and interstage gaps, comprising:
conducting a first thermal analysis of a baseline configuration of a baseline disk that does not have corrosion to determine a first steady state temperature distribution;
machining a corrosion damaged disk to a depth suitable for repairing the corrosion to form a machined disk, wherein the depth for machining the disk is established statistically;
conducting a second thermal analysis of the machined disk to determine a second steady state temperature distribution of the machined disk;
calculating a first predicted safe cyclic life (PSCL) for disk axisymmetric features of the machined disk;
calculating a second PSCL for disk firtree features of the machined disk; and
qualifying the repair method to ensure that the quality of the machined disk is consistent with a new disk, wherein qualifying the repair method includes machining trials, mechanical property and metallographic evaluations and residual stress evaluations.
15. The method of claim 14 , wherein the depth for machining the machined disk is established statistically by studying an observed depth of subsurface damage induced by Low Temperature Hot Corrosion (LTHC).
16. The method of claim 14 , wherein the second thermal analysis includes a determination of steady state temperature variation between the baseline configuration and interstage gaps due to machining of the machined disk.
17. The method according to claim 14 , wherein the first PSCL is based on rim temperature reference points.
18. The method according to claim 14 , wherein the disk firtree features include upper, middle and lower notches of the disk firtree.
19. The method according to claim 14 , wherein the PSCL of a disk feature is ⅔ rd of a minimum life to burst.
20. The method according to claim 14 , wherein damage contributions from low cycle fatigue (LCF) and creep are evaluated separately.