Analysis of gas turbine compressor fouling and washing on line
This work presents a model of the fouling mechanism and the evaluation of compressor
washing on line. The results of this research were obtained from experimental and
The experimental model analyzed the localization of the particle deposition on the blade
surface and the change of the surface roughness condition. The design of the test rig was
based on the cascade blade arrangement and blade aerodynamics. The results of the
experiment demonstrated that fouling occurred on both surfaces of the blade. This
mechanism mainly affected the leading edge region of the blade. The increment of the
surface roughness on this region was 1.0 ?m. This result was used to create the CFD
model (FLUENT). According to the results of the CFD, fouling reduced the thickness of
the boundary layer region and increased the drag force of the blade.
The model of fouling was created based on the experiment and CFD results and was
used to calculate the engine performance in the simulation code (TURBOMATCH).
The engine performance results demonstrated that in five days fouling can affect the
overall efficiency by 3.5%. The evaluation of the compressor washing on line was based
on the experimental tests and simulation of the engine performance. This system
demonstrated that it could recover 99% of the original blade surface. In addition, this
system was evaluated in a study case of a Power Plant, where it proved itself to be a
techno-economic way to recover the power of the engine due to fouling.
The model of the fouling mechanism presented in this work was validated by
experimental tests, CFD models and information from real engines. However, for
further applications of the model, it would be necessary to consider the specific
conditions of fouling in each new environment.
Advisor:Pilidis, P. (supervisor)
School Location:United Kingdom
Source Type:Master's Thesis
Keywords:techno electric cascade blade experiment roughness cfd
Date of Publication:01/01/2007