Experimental Investigation of Particulate Deposition on a Simulated Film-Cooled Turbine Vane Pressure Surface in a High Pressure Combustion Facility

Murphy, Robert G.

doi:10.33915/etd.290

Cited by 3 publications

(14 citation statements)

References 11 publications

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“…The results from the study found that deposition formed on only one side of the test articles. Deposit formation on only one side of the test articles was due to a large deposit structure forming on the transition piece of the test section upstream of the test articles [13] [14]. The deposit structure on the test section transition piece created aswirl effect.…”

Section: Test Articles and Experimental Methodsmentioning

confidence: 99%

Microstructural Degradation of Thermal Barrier Coatings on an Integrated Gasification Combined Cycle (IGCC) Simulated Film-Cooled Turbine Vane Pressure Surface Due to Particulate Fly Ash Deposition

Luo¹

2015

IJCCE

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Research is being conducted to study the degradation of thermal barrier coatings (TBC) employed on IGCC turbine hot section airfoils due to particulate deposition from contaminants in coal synthesis gas (syngas). West Virginia University (WVU) had been working with US Department of Energy, National Energy Technology Laboratory (NETL) to simulate deposition on the pressure side of an IGCC turbine first stage vane. To simulate the contaminant deposition, several TBC coated, angled film-cooled test articles were subjected to accelerated coal fly ash, which was injected into the flow of a combustor facility with a high pressure (approximately 4 atm) and a high temperature (1560 K) environment. To investigate the degradation of the TBCs due to particulate deposition, non-destructive tests were performed using scanning electron microscopy (SEM) evaluation and energy dispersive X-ray spectroscopy (EDS) examinations. The SEM evaluation was used to display the microstructure change within the layers of the TBC system directly related to the fly ash deposition. The SEM micrographs showed that deposition-TBC interaction made the YSZ coating more susceptible to delamination and promoted a dissolution-reprecipitation mechanism that changed the YSZ morphology and composition. The EDS examination provided elemental maps of the shallow infiltration depth of the fly ash and chemical composition spectrum results which showed yttria migration from the YSZ into the deposition.K. Luo et al.2

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Section: Test Articles and Experimental Methodsmentioning

confidence: 99%

Microstructural Degradation of Thermal Barrier Coatings on an Integrated Gasification Combined Cycle (IGCC) Simulated Film-Cooled Turbine Vane Pressure Surface Due to Particulate Fly Ash Deposition

Luo¹

2015

IJCCE

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“…The one sided deposit formation was due to a large deposit structure forming on the transition piece of the test section. Figure 2 shows the transition piece with a deposit structure on the left side of the piece [14] [15]. The structure on the test section transition piece created a swirl effect leading to an uneven distribution of fly ash into the test section.…”

Section: Test Articles and Experimental Methodsmentioning

confidence: 99%

“…Heavy deposition can be observed on the left side of the face on test article 1 (see Figure 3(a)). The roughness results were computed for the deposition on test article 1 using an Olympus LEXT OLS 3100 laser confocal microscope [14]. A detailed view of the roughness characteristics is shown in Figure 4(a) [14].…”

Section: Test Articles and Experimental Methodsmentioning

confidence: 99%

“…The roughness results were computed for the deposition on test article 1 using an Olympus LEXT OLS 3100 laser confocal microscope [14]. A detailed view of the roughness characteristics is shown in Figure 4(a) [14]. The blue line represents the mean average roughness of the article when unexposed to testing.…”

Section: Test Articles and Experimental Methodsmentioning

confidence: 99%

“…Figure 4(b) contains the image of where the surface roughness scan of the deposition was taken on test article 1. The roughness values for test article 1 prior to sectioning are given in Table 3 [14].…”

Section: Test Articles and Experimental Methodsmentioning

confidence: 99%

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Effects of Syngas Particulate Fly Ash Deposition on the Mechanical Properties of Thermal Barrier Coatings on Simulated Film-Cooled Turbine Vane Components

Luo¹,

Nix²,

Kang³

et al. 2014

IJCCE

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Research is being conducted to study the effects of particulate deposition from contaminants in coal synthesis gas (syngas) on the mechanical properties of thermal barrier coatings (TBC) employed on integrated gasification combined cycle (IGCC) turbine hot section airfoils. West Virginia University (WVU) had been working with US Department of Energy, National Energy Technology Laboratory (NETL) to simulate deposition on the pressure side of an IGCC turbine first stage vane. To model the deposition, coal fly ash was injected into the flow of a combustor facility and deposited onto TBC coated, angled film-cooled test articles in a high pressure (approximately 4 atm) and a high temperature (1560 K) environment. To investigate the interaction between the deposition and the TBC, a load-based multiple-partial unloading micro-indentation technique was used to quantitatively evaluate the mechanical properties of materials. The indentation results showed the Young's Modulus of the ceramic top coat was higher in areas with deposition formation due to the penetration of the fly ash. This corresponds with the reduction of strain tolerance of the 7% yttria-stabilized zirconia (7YSZ) coatings.

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Degradation of thermal barrier coatings on an Integrated Gasification Combined Cycle (IGCC) simulated film-cooled turbine vane pressure surface due to particulate fly ash deposition

Luo¹

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Coal synthesis gas (syngas) can introduce contaminants into the flow of an Integrated Gasification Combined Cycle (IGCC) industrial gas turbine which can form molten deposits onto components of the first stage of a turbine. Research is being conducted at West Virginia University (WVU) to study the effects of particulate deposition on thermal barrier coatings (TBC) employed on the airfoils of an IGCC turbine hot section. WVU had been working with U.S. Department of Energy, National Energy Technology Laboratory (NETL) to simulate deposition on the pressure side of an IGCC turbine first stage vane to study the effects on film cooling. To simulate the particulate deposition, TBC coated, angled film-cooled test articles were subjected to accelerated deposition injected into the flow of a combustor facility with a pressure of approximately 4 atm and a gas temperature of 1560 K. The particle characteristics between engine conditions and laboratory are matched using the Stokes number and particulate loading [1]. To investigate the degradation on the TBC from the particulate deposition, non-destructive evaluations were performed using a load-based multiple-partial unloading micro-indentation technique and were followed by scanning electron microscopy (SEM) evaluation and energy dispersive X-ray spectroscopy (EDS) examinations. The micro-indentation technique used in the study was developed by Kang et al. [2] and can quantitatively evaluate the mechanical properties of materials. The indentation results found that the Young's Modulus of the ceramic top coat is higher in areas with deposition formation due to the penetration of the fly ash. The increase in the modulus of elasticity has been shown to result in a reduction of strain tolerance of the 7% yttria-stabilized zirconia (7YSZ) TBC coatings [3]. I would like to extend my gratitude to Dr. Bruce S. Kang and his Ph.D. student Dumbi A. Otunyo for providing the multiple partial unloading indentation system. Without guidance and use of the system, I would not have been able to perform a quantitative strain tolerance analysis. I've had the pleasure of having Dr. Kang as a supportive figure in my life since I was a young lad at Christian & Missionary Alliance (C&MA) Church.

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Experimental Investigation of Particulate Deposition on a Simulated Film-Cooled Turbine Vane Pressure Surface in a High Pressure Combustion Facility

Cited by 3 publications

References 11 publications

Microstructural Degradation of Thermal Barrier Coatings on an Integrated Gasification Combined Cycle (IGCC) Simulated Film-Cooled Turbine Vane Pressure Surface Due to Particulate Fly Ash Deposition

Microstructural Degradation of Thermal Barrier Coatings on an Integrated Gasification Combined Cycle (IGCC) Simulated Film-Cooled Turbine Vane Pressure Surface Due to Particulate Fly Ash Deposition

Effects of Syngas Particulate Fly Ash Deposition on the Mechanical Properties of Thermal Barrier Coatings on Simulated Film-Cooled Turbine Vane Components

Degradation of thermal barrier coatings on an Integrated Gasification Combined Cycle (IGCC) simulated film-cooled turbine vane pressure surface due to particulate fly ash deposition

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