Industrial Gas Turbine Performance: Compressor Fouling and On-Line Washing

Igie, Uyioghosa; Pilidis, Pericles; Fouflias, Dimitrios; Ramsden, Kenneth; Laskaridis, Panagiotis

doi:10.1115/1.4027747

Cited by 25 publications

(15 citation statements)

References 18 publications

(22 reference statements)

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“…Igie et al. 1 shows that the impact of fouling is the alteration of the aerodynamic shape of the compressor blade, increases in surface roughness and reduction in the blade effective flow passage. This effect is characterised by implanting a flow capacity reduction (related to additional materials on the blade, as well as increased boundary layer) and a reduction of compressor efficiency (related to induced drag caused by roughened surface and change in blade geometry).…”

Section: Compressor Fouling Cases and Effectsmentioning

confidence: 99%

“…Aero engines are susceptible to compressor fouling as shown in Figures 1 and 2, which is the deposition and accretion of airborne particles on the compressor blades. 1 Unlike the application of gas turbines (GTs) for power generation, mechanical drive applications and helicopter engines, inlet air filtrations systems are not installed on jet engines given the nature of the operation. In addition to this, jet engines operate predominantly at cruise, which can be up to 12,000 m, where the concentration of fouling particles is negligible.…”

Section: Introductionmentioning

confidence: 99%

“…As the lower atmosphere is more predisposed to airborne fouling, also due to gravity, engines operated more frequently on the lower altitudes or more flight cycles such as short-haul mission (SHM) operations are likely to be more exposed to contaminants. From the knowledge gained from studies on compressor fouling for stationary applications, it is generally known that the impact includes the following: reduced mass flow, pressure ratio, compressor efficiency, thermal efficiency and shaft power for a given rotational speed/turbine entry temperature (TET), 1,3 increased fuel burn and TET to maintain the same level of shaft power 1,3 that can reduce the life of the turbine blades. …”

Section: Introductionmentioning

confidence: 99%

“…reduced mass flow, pressure ratio, compressor efficiency, thermal efficiency and shaft power for a given rotational speed/turbine entry temperature (TET), 1,3…”

Section: Introductionmentioning

confidence: 99%

“…increased fuel burn and TET to maintain the same level of shaft power 1,3 that can reduce the life of the turbine blades.…”

Section: Introductionmentioning

confidence: 99%

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Aero engine compressor fouling effects for short- and long-haul missions

Igie

Goiricelaya

Nalianda

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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The impact of compressor fouling on civil aero engines unlike the industrial stationary application has not been widely investigated or available in open literature. There are questions about the impact of fouling for short-and long-haul missions comparatively, given their unique operational requirements and market. The aim of this study is to quantify the effects of different levels of fouling degradation on the fan, for two different aircraft with different two-spool engine models for their respective typical missions. Firstly, the study shows the increase in turbine entry temperature for both aircraft engines, to maintain the same level of thrust as their clean condition. The highest penalty observed is during takeoff and climb, when the thrust setting is the highest. Despite take-off and climb segment being a larger proportion in the short-haul mission compared to the long-haul mission, the percentage increase in fuel burn due to fouling are similar, except in the worst case fouling level were the former is higher by 0.8% points. In addition to this, for all the cases, the additional fuel burn due to fouling and its cost is shown to be small. Likewise, the increase in turbine entry temperature for both missions at take-off are similar, except in the worst case fouling level for the short-haul mission were the turbine entry temperature is 7 K higher than the corresponding long-haul mission for the same level of degradation. The study infers that the penalty due to rise in temperature is of more concern than the additional fuel burn. Hence the blade technology (cooling and material) and engine thrust rating are key factors in determining the extent to which blade fouling would affect aero engine performance in short-and long-haul missions.

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Section: Compressor Fouling Cases and Effectsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

“…reduced mass flow, pressure ratio, compressor efficiency, thermal efficiency and shaft power for a given rotational speed/turbine entry temperature (TET), 1,3…”

Section: Introductionmentioning

confidence: 99%

“…increased fuel burn and TET to maintain the same level of shaft power 1,3 that can reduce the life of the turbine blades.…”

Section: Introductionmentioning

confidence: 99%

See 3 more Smart Citations

Aero engine compressor fouling effects for short- and long-haul missions

Igie

Goiricelaya

Nalianda

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part G:

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View full text Add to dashboard Cite

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Classification and prediction of gas turbine gas path degradation based on deep neural networks

et al. 2021

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Summary This paper mainly analyzes the performance degradation of turbomachinery in gas turbines, classifies the main types of degradation: increased tip clearance, corrosion/wear, fouling, and multiple degradation, and predicts the degradation trend through deep neural networks. The deep feedforward neural network is used to build the regression model and two classification models. The regression model uses a back propagation algorithm optimized by Lenvenberg Marquardt to convert the efficiency and flow capacity calculated by the thermodynamic model into the values under full load and ISO conditions to ensure that the comparison is performed on the same performance benchmark. Compared with deep feedforward neural network and random forest regression, the optimized model has higher accuracy and no overfitting. The data after the overhaul is selected as the performance benchmark, and the efficiency and flow capacity of different degradation types are calculated according to the benchmark and classified by the classification model. By testing the simulated data, the classification accuracy of the compressor and the turbine exceeds 99.9% and 99.5% respectively. Long short‐term memory is used to predict the degradation trends and the degradation of the predictions is classified by the classification model. The degradation classification accuracy of the prediction reached 93.65% and 81.65% in compressor and turbine, which shows that the prediction model has high accuracy.

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Analysis of the Impact of Degradation on Gas Turbine Performance Using the Support Vector Machine (SVM) Method

Asnawi

Lemma

2020

Lecture Notes in Mechanical Engineering

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Industrial Gas Turbine Performance: Compressor Fouling and On-Line Washing

Cited by 25 publications

References 18 publications

Aero engine compressor fouling effects for short- and long-haul missions

Aero engine compressor fouling effects for short- and long-haul missions

Classification and prediction of gas turbine gas path degradation based on deep neural networks

Analysis of the Impact of Degradation on Gas Turbine Performance Using the Support Vector Machine (SVM) Method

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