Thermal cycling behavior of EB-PVD TBCs on CVD platinum modified aluminide coatings

Xu, Zhenhua; Wang, Zhankao; Huang, Guanghong; Mu, Rende; He, Limin

doi:10.1016/j.jallcom.2015.02.177

Cited by 18 publications

(4 citation statements)

References 33 publications

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“…The 20 µm Al-modi ed TBCs showed an optimal thermal cycle performance (Fig. 6a) compared to the other APS and EB-PVD TBCs [33][34][35][36][37][38][39][40][41][42][43][44][45][46][47][48] . In this work, the as-sprayed and Al-modi ed TBCs were compared, shown in Figs.…”

Section: Comparison Of Thermal Cycle Performancementioning

confidence: 99%

A solution to the challenges of particle erosion and thermal cycle for PS-PVD 7YSZ thermal barrier coatings

Zhang

et al. 2021

Preprint

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Advanced aero-engine is a key technique that is used all over the world, where many high-temperature components such as turbine blades and combustor, are made of Ni/Co/Fe based superalloys. However, they need high-temperature protection to avoid fast performance degradation. Generally, the superalloy high-temperature components are protected by thermal barrier coatings (TBCs) obtained via an atmospheric plasma spray (APS) and an electron beam-physical vapor deposition (EB-PVD). Here, a novel 3rd generation TBCs process using plasma spray-physical vapor deposition (PS-PVD) is presented, showing a more promising use than the traditional APS and EB-PVD. The PS-PVD feature uses evaporating ceramic powder, which results in the deposition of a feather-like columnar coating. This special microstructure showed good strain tolerance and non-line-of-sight (NLOS) deposition, giving great potential for application. In a working aero-engine, the high-temperature components face a serious environment, where foreign particle erosion is a great challenge and is the first barrier to the application of PS-PVD TBCs. As a solution, an Al-modification approach was proposed in this investigation. The results demonstrate that this approach can improve particle erosion resistance. Also, the thermal cycle performance had an apparent optimization.

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Section: Comparison Of Thermal Cycle Performancementioning

confidence: 99%

A solution to the challenges of particle erosion and thermal cycle for PS-PVD 7YSZ thermal barrier coatings

Zhang

et al. 2021

Preprint

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“…Modification of chemical and phase composition of aluminide coating makes it possible to apply them as a bond coatings for thermal barrier coating (TBC) systems on blades and vanes operating under the most severe conditions (Swadźba et al ., ). Incorporation of noble metals, particularly platinum, to aluminide coatings improves resistance to oxidation and hot corrosion (Zagula‐Yavorska & Sieniawski, ; Xu et al ., ). Platinum encourages formation of pure alumina oxide and reduces the oxide growth rate.…”

Section: Introductionmentioning

confidence: 97%

Degradation of nonmodified and rhodium modified aluminide coating deposited on CMSX 4 superalloy

Zagula-Yavorska

Wierzbińska

Gancarczyk

et al. 2016

Journal of Microscopy

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The Ni-base superalloy CMSX 4 used in the turbine blades of aircraft engines was coated with rhodium layer (0.5-μm thick). Next coated CMSX 4 superalloy was aluminized by the CVD method. The rhodium modified aluminide coating and nonmodified aluminide coating were oxidized at 1100°C at the air atmosphere. The rhodium modified aluminide coating showed about twice better oxidation resistance than the nonmodified one. The spallation equal 62% of the total area was observed on the surface of the nonmodified coating whereas only 36% spallation area was observed on the surface of the rhodium modified aluminide coating after the oxidation test. The oxide layer formed on the surface of the nonmodified coating was composed of nonprotective (Ni,Cr)Al2 O4 and (Ni,Cr)O phases. Aluminium in the coating reacts with oxygen, forming a protective α-Al2 O3 oxide on the surface of the rhodium modified aluminide coating. When the oxide cracks and spalls due to oxidation, additional aluminium from the coating diffuses to the surface to form the oxide. The presence of protective Al2 O3 oxide on the surface of the rhodium modified aluminide coating slows coating degradation. Therefore, rhodium modified aluminide coating has better oxidation resistance than the nonmodified one.

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“…The operating limit temperature of the superalloy materials used in gas turbine engines is known to be 900-1050 • C. With growing demands for the improved efficiency of gas turbine engines, considerable research efforts have been devoted to increase the engine operating temperature and reduce the weight of gas turbine parts. By applying thermal barrier coatings (TBCs) to the surface of Ni-based superalloy materials, the operating temperature of gas turbines can be increased [1][2][3][4][5][6][7][8][9]. In particular, TBCs inhibit the transfer of heat generated during gas turbine operation to the surface of the superalloy, thereby improving the life and operating temperature of gas turbine components.…”

Section: Introductionmentioning

confidence: 99%

“…In particular, TBCs inhibit the transfer of heat generated during gas turbine operation to the surface of the superalloy, thereby improving the life and operating temperature of gas turbine components. A TBC typically consists of a ceramic top coat, characterized by low thermal conductivity and excellent oxidation resistance, and a bond coat with excellent adhesion and oxidation resistance, located between the top coat and the substrate [7][8][9][10]. TBC's bond coat is typically made of MCrAlY (M = Ni, Co, or a mixture of both compositions) or a β-NiAl diffused aluminide layer.…”

Section: Introductionmentioning

confidence: 99%

Oxidation-Induced Changes in the Lattice Structure of YSZ Deposited by EB-PVD in High-Vacuum Conditions

Lee,

2023

Processes

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Yttria-stabilized zirconia (YSZ), a thermal barrier coating material characterized by low thermal conductivity, is typically deposited via electron beam-physical vapor deposition. Notably, oxygen depletion occurs during this process, causing color changes in YSZ. Therefore, YSZ is speculated to undergo phase transformation during this process, which demands careful consideration owing to its effect on the life of thermal coatings. To study this phenomenon, bulk samples were prepared, subjected to vacuum heat treatment to induce oxygen depletion, and followed by oxidative heat treatment. Experimental results showed that the color of the samples changed to black after the vacuum heat treatment and to a lighter color after the oxidative heat treatment. In addition, X-ray diffraction and Raman analyses were performed. The monoclinic phase formation was confirmed during the vacuum heat treatment; however, it disappeared after the oxidation heat treatment. The coating obtained in a high vacuum atmosphere exhibited a black color and cubic phase, which changed to a bright color and tetragonal phase after the oxidation heat treatment.

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Thermal cycling behavior of EB-PVD TBCs on CVD platinum modified aluminide coatings

Cited by 18 publications

References 33 publications

A solution to the challenges of particle erosion and thermal cycle for PS-PVD 7YSZ thermal barrier coatings

A solution to the challenges of particle erosion and thermal cycle for PS-PVD 7YSZ thermal barrier coatings

Degradation of nonmodified and rhodium modified aluminide coating deposited on CMSX 4 superalloy

Oxidation-Induced Changes in the Lattice Structure of YSZ Deposited by EB-PVD in High-Vacuum Conditions

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