Overview.

Background

Stress corrosion cracking (SCC) of low-pressure steam turbine rotor blade attachments is an industry issue on older fossil and nuclear units. Many units have experienced forced outages and/or extended repairs due to direct or collateral damage. Cracks that initiate in rotor steeples can eventually propagate to failure resulting in blade loss and significant damage. Since SCC is a chronic and time dependent failure mechanism, older units that have not previously experienced problems are not immune from future problems.

However risks related to SCC can be mitigated through good inspection and repair contingency planning. Understanding the causes, available inspection techniques, and repair options is key to preventing this issue from impacting unit availability.

Fig 1 Crack Locations
Fig 1 Crack Locations
Fig 2 SCC Conditions
Fig 2 SCC Conditions

Causes

Several factors must be present for SCC to occur including high tensile surface stress, material susceptibility to corrosion, corrosive environment, and service time. Low-pressure blade attachments on older units that operate near the Wilson Line, where the sudden transition from superheat to high quality steam occurs, often meet these conditions.

Blade attachments are high stress locations due to the transfer of blade loads to the rotor. Many older blade attachments, designed before the advent of finite element analysis, were not optimized for stress concentrations. This often results in very high peak surface stresses as confirmed by post failure analysis of designs that had experienced SCC.

High yield strength materials used on early rotor designs are especially susceptible to SCC. Testing shows crack growth rates can vary from 0.005 mils/year to over 0.500 inches per year depending on material and temperature. The generally recommended purchase specification upper yield strength limit is 120 ksi for a new nuclear or fossil LP turbine retrofit. Many older disc construction rotors have yields above this limit.

Corrosive environments arise from sodium chloride concentration near the Wilson line (salt zone). For a fossil low-pressure design, this occurs near the L-2 thru L-0 stages. Nuclear Units operate at lower steam design conditions, and the salt zone occurs further upstream in the generally lower stressed L-6 thru L-3 rows. Units with frequent condenser leaks and once through boiler designs are more susceptible due to poorer steam chemistry control.

Since stress corrosion cracking is a time dependent phenomena, crack initiation does not occur until after some period of operation. Older units that previously did not exhibit SCC are still susceptible. Any unit with over 20 years of service should be inspected for SCC. The unit load profile has an impact since any existing cracks can grow significantly faster if a unit is cycled on and off. Base loading a unit with existing cracking reduces growth rates.

Fig 3 Blade Failures
Fig 3 Blade Failures
Fig 4 GE Blades
Fig 4 GE Blades
Fig 5 GE SCC
Fig 5 GE SCC

Inspection

With side entry blade designs, the inlet and exhaust side of the disc should be grit blasted and polished with scotch bright abrasives. These inspections should concentrate in the highest stress locations of the hook fit or Christmas tree root area. If cracking is suspected, a blade group should be removed and light polishing done as necessary to confirm findings.

Tangential reverse steeple/disc attachments cannot be directly inspected. In these cases, NDE technologies such as phased array must be employed. OEMs and many other inspection companies offer this as a service. If cracking is detected, a few blades should be removed to confirm sizing.

Repair

In general, cracks of up to 10 mils depth can be polished out. Cracks of up to 20 mils depth may be removed depending on the design. In all cases, the grinding/polishing tool radius employed should be equal or greater than the original hook fit radius to not adversely affect the stress concentration factor. Care must also be taken to avoid altering blade bearing stress surfaces and potentially introducing galling/fretting concerns. Since the stress intensity of a polished out area is less than a crack tip, carefully removing cracks results in improved remaining service life.

If a crack is larger than what can be safely removed, weld repair is generally required. All OEMs offer removal of the attachment and either weld build-up or welding on a ring and machining to form a new attachment. If the current outage does not allow time for repair, an analysis of growth rates and estimate of remaining life must be made to determine if a repair can be deferred. For analysis, the material yield strength should be confirmed. This can be accomplished with local hardness readings correlated to ultimate tensile stress (UTS), which is typically 15 ksi higher than the yield.

Fig 6 SCC Weld
Fig 6 SCC Weld
Fig 7 SCC MT
Fig 7 SCC MT

Case Study

TG Advisers was brought in to assist a client with last stage blade steeple SCC. The 200 MW unit had accumulated 500,000 hrs of load cycling with some periods of stop/start operation since going in service in 1954. Following last stage blade removal, the steeples were glass bead peened to facilitate a Magnetic Particle inspection. Cracking was identified in most steeples and on almost all lugs. The cracking was all concentrated in peak stress locations and clearly visible by black light inspection.

Exploratory grinding/polishing determined crack depth in each of the 3 steeple regions. Most cracks were less then 10 mils deep with a few at or near 15 mils. Removing the cracks was the first choice. However the web thickness on the top lug on the leading side was fairly narrow. Removing the required material to eliminate the indication was a concern. A stress analysis determined the estimated reduction in safety factor with cracks removed was acceptable.

Based on the analysis, the client elected to clear the indications. Special tooling was developed to ensure a radius greater then the original and to keep any material removal away from load bearing attachment surfaces.

Quality control of the manual process was accomplished by rubber molds of the final, as polished steeples. Approximately 10% of the steeples were checked. This process took 5 days and the unit was successfully returned to service.

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