Dear Kourosh Vaferi

The corrosion on rotor blades is always worse for two reasons. First, the rotating blades of a rotor bear more mechanical stress than stators. Second, salt particles collide and adhere together more often with the rotating blades of a rotor. So pitting corrosion, crevice corrosion, and stress corrosion are commonly found on rotating blades.

Dear Kourosh Vaferi

The corrosion on rotor blades is always worse for two reasons. First, the rotating blades of a rotor bear more mechanical stress than stators. Second, salt particles collide and adhere together more often with the rotating blades of a rotor. So pitting corrosion, crevice corrosion, and stress corrosion are commonly found on rotating blades.

Dear kourosh

I do agree with Mohsen Naderi

The corrosion in rotor blades of gas turbine is worse.

corrosion occur when the blade is operated under conditions of high humidity. at higher temperatures both rotor and stator blades faced corrosion but the rotor's is more.

Seriously! Stress corrosion cracking in the gas turbines??? High humidity in gas turbines??????? And dozens of recommendations....What is wrong with you people?

Something wrong going on here which is totally rigged. Please leave the RG to real scientific discussion and follow your social media culture elsewhere!

Dear Kourosh Vaferi

Read this articles for stress corrosion in gas turbines:

Article Stress corrosion of Ni-based superalloys

Article Investigation on the effects of blade corrosion on compresso...

Article Pitting Corrosion Induced Fatigue Fracture on a Gas Turbine ...

Stress corrosion is not stress corrosion cracking (SCC). Initially stress corrosion cracking, pitting, crevice were mentioned in the answer, now SCC has been replaced by stress corrosion. The paper you referred to is not typical stress corrosion cracking that is observed in aqueous conditions, where you talk about humidity. The paper is on type II hot corrosion - stress cracking. This is a research article with a high magnitude of stress - not practical condition that was mentioned in the question. You can conveniently edit your answers after mistakes are pointed out. Nothing wrong in it. Now post papers on pitting and crevice corrosion of gas turbine blades. Again, those will be based on hot corrosion.

In any case, your group is rigging RG. As long as you post correct answers that is OK. I would not have commented anything if hot corrosion had been mentioned in the initial answers. It is not too late, go and read more on hot corrosion of gas turbine blades and edit your answers.

OK, now some useful info addressing the question:

One survey pointed out that among gas turbine failures, 28% was attributed to rotor components, and 18% was due to stationary components. High cycle fatigue and failure of thermal barrier coating (TBC) were accounted for 62% of the total failures of turbine blades in another survey. Corrosion attack becomes critical only when the TBC fails.

Perhaps I've missed something here. However, as far as I can see, Mohsen Naderi mentioned 'stress corrosion' in his list in the first response. In his response, Krishnan Raja interpreted that to mean 'stress corrosion cracking' and then decided to berate Mohsen Naderi for 'his' mistake. So far as I can see, Mohsen Naderi never mentioned stress corrosion cracking until later - when he correctly indicated that SCC can occur in turbine blades, but in steam turbines rather than in gas turbines.

In my opinion, stress corrosion can and does occur on gas turbine blades. Again, Krishnan Raja appears to have (mis)interpreted TBCs to mean only ceramic coatings, but there are dozens of sprayed metal coatings on various types that certainly can and do sustain degradation due to stress-enhancement of high-temperature corrosion on the surfaces of blades.

There is also strong evidence of stress-assisted intergranular attack of gas turbine blades, which looks very much akin to stress corrosion cracking when examined retrospectively using a metallurgical cross-section but is actually due to an unrelated high temperature anodic dissolution reaction, as indicated by the presence of corrosion product down the cracks, whereas if it were true SCC the corrosion product wouldn't be present.