Wyniki wyszukiwania - Biblioteka Nauki

1

Thermophysical properties of selected powders for thermal barrier coatings

100%

Drajewicz M. , Góral M. , Pytel M. , Sieniawski J.

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2012

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tom Vol. 55, nr 2

902--906

EN

Purpose: Plasma-sprayed thermal barrier coatings often have the problems of spallation and cracking in service owing to their poor bond strength and high residual stresses. Functionally graded thermal barrier coatings with a gradual compositional variation from heat resistant ceramics to fracture-resistant metals are proposed to mitigate these problems. Design/methodology/approach: The results of measurements of thermal diffusivity by using one of the most modern experimental sets LFA 427 (Laser Flash Apparatus) produced by Netzsch Company. In order to measure the specific heat cp(T) and density p(T), two methods of termogravimetry analysis were used STA 449 Jupiter F3 Netzsch Company and gas displacement density analyzer AccuPyc II 1340 Micromeritics Company. Research limitations/implications: This paper presents the results of measurements of thermal diffusivity coefficient as a function of temperature for Sulzer powders, AMDRY 997, AMDRY 365C, METCO 45C NS, METCO 202 NS, METCO 204 NS. Practical implications: Optimal technical and technological parameters of powders for thermal barrier coatings have been selected. Originality/value: The presented method undoubtedly develops new possibilities for thermal barrier coatings.

2

Diffraction and Microscopic Studies on the Structure of Plasma Sprayed Coatings Containing Composites based on Al2O3

100%

Górski L. , Pawłowski A. , Wiśniewski Z.

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tom Vol. 55, iss. 1

287-292

EN

Plasma sprayed coatings of thermal barrier type (TBC) based on A1203 and Zr02 with metallic bondcoat are studied by X-ray diffraction, scanning and transmission electron microscopy. Phase transitions and presence of various layers : amorphous, nano and polycrystalline of equiaxial and columnar shape are observed. Local fluctuations of chemi-cal and phase composition are mainly connected with the conditions of plasma spraying process. In the result of thermal treatment changes directed to morę ordered state occur.

PL

Powłoki natryskiwane plazmowo typu barier termicznych na bazie A1203 i Zr02 zawierające metaliczną warstwę wiążącą badane były metodami dyfrakcji rentgenowskiej oraz skaningowej i transmisyjnej mikroskopii elektronowej. Zaobserwowano występowanie przemian fazowych oraz obecność oddzielnych warstw: amorficznych, nanokrystalicznych oraz polikrystalicznych charakteryzujących się równoosiowymi i kolumnowymi kształtami krystalitów. Lokalne fluktuacje składu chemicznego i fazowego są związane z warunkami procesu natryskiwania plazmowego. Zmiany zachodzące w wyniku obróbki termicznej powłok prowadzą do stanu bardziej uporządkowanego.

3

Analiza mikrostruktury powłokowych barier cieplnych TBC po teście cyklicznego utleniania w temperaturze 1100°C

100%

Swadźba R. , Wiedermann J. , Rozmus R.

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tom T. 65, nr 3

29--34

PL

Powłokowe bariery cieplne (Thermal Barrier Coatings – TBC) wytwarzane metodą EB-PVD (Electron Beam Physical Vapor Deposition) stosowane są na łopatki wirujące oraz kierujące nowoczesnych silników lotniczych oraz turbin stacjonarnych w celu obniżenia temperatury pracy stopów, z których te elementy są wykonane. Stanowią one system powłok, w których skład wchodzi zewnętrzna powłoka ceramiczna ZrO2*Y2O3 (Yttria Stabilized Zirconia – YSZ) zapewniająca ochronę przed skutkami wysokiej temperatury oraz żaroodporna międzywarstwa chroniąca przed utlenianiem. W artykule przedstawiono wyniki analizy zjawisk zachodzących w powłokowych barierach cieplnych na międzywarstwie aluminidkowej modyfikowanej platyną podczas testu cyklicznego utleniania w temperaturze 1100°C. Przeprowadzono analizę zmian w mikrostrukturze międzywarstwy oraz warstwy tlenkowej Al2O3 wzrastającej podczas utleniania wysokotemperaturowego oraz scharakteryzowano obszary, w których następuje degradacja powłokowej bariery cieplnej przez odpadanie zewnętrznej powłoki ceramicznej.

EN

Thermal Barrier Coatings (TBC) produced using EB-PVD (Electron Beam Physical Vapor Deposition) method are applied on rotary and stationary blades of modern jet engines and stationary turbines in order to provide temperature reduction of the alloys these components are made of. This coating system includes a ceramic coating ZrO2*2O3 (Yttria Stabilized Zirconia – YSZ), providing protection from high temperature, and oxidation resistant bond coating. The article presents the results of phenomena analysis that occur in thermal barrier coatings on platinum modified aluminide bond coating during cyclic oxidation test at 1100°C. Changes that occur in the microstructure of the bond coat and Al2O3 oxide layer that grows during high temperature oxidation were analyzed as well as areas where the degradation of the thermal barrier coatings occurs by delamination of the top ceramic coating.

4

Thermal barrier coatings manufactured by suspension plasma spraying - a review

84%

Łatka L.

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tom Vol. 18, nr 3(57)

95--117

EN

Thermal barrier coatings (TBC) is one of the most intensively studied of coatings’ applications area. From 1970’s TBC are developed in two independent ways: (i) development in new materials, with lower thermal conductivity, better erosion resistance and better thermal shock resistance or (ii) development in new deposition techniques. On this field besides conventional atmospheric plasma spraying (APS) and almost conventional (because of very common use) EB-PVD method, in the past 20 years two new techniques have been developed, namely suspension plasma spraying (SPS) and solution precursor plasma spraying (SPPS). In this paper only SPS method was described, as well as, new materials, which could be used in industrial applications of TBC. Moreover, the key issues, like suspension preparation, type of suspension injection, interaction between liquid droplets and plasma jet and deposition mechanism were described.

5

Technologia i mikrostruktura powłokowej bariery cieplnej uzyskanej metodami natryskiwania plazmowego i aluminiowania gazowego na stopie Re 80

84%

Nowotnik A. , Góral M. , Filip R. , Sieniawski J.

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tom Vol. 32, nr 4

645-647

PL

Intensywny rozwój przemysłu lotniczego związany ze zwiększeniem się liczby pasażerów determinuje opracowywanie nowocześniejszych konstrukcji silników lotniczych. Obecnie najbardziej zaawansowanym sposobem ochrony powierzchni łopatek turbin oraz elementów komory spalania przed wysoką temperaturą oraz oddziaływaniem korozyjnym spalin jest stosowanie powłokowych barier cieplnych. Powłoki złożone są z dwóch warstw pełniących odmienne funkcje. Powłokę wewnętrzną stanowi warstwa aluminidkowa uzyskiwana metodami dyfuzyjnymi lub wieloskładnikowy stop typu MeCrAlY. Chroni ona materiał podłoża przed utlenianiem i kompensuje różnice we właściwościach fizycznych pomiędzy warstwą zewnętrzną a materiałem podłoża. Warstwa zewnętrzna zapewnia izolację cieplną - tworzy ją tlenek cyrkonu stabilizowany tlenkiem itru. W artykule przedstawiono charakterystykę mikrostruktury powłokowej bariery cieplnej o budowie gradientowej, wielowarstwowej, wytworzonej na powierzchni odlewniczego nadstopu niklu typu Re 80. Międzywarstwę wytworzono w procesie natryskiwania plazmowego (APS) wieloskładnikowego stopu typu MeCrAlY, który następnie poddano aluminiowaniu metodą gazową. Analiza mikrostruktury i składu chemicznego wykazała zwiększenie zawartości aluminium w strefie przypowierzchniowej (do ok. 40% at.) i powstanie fazy NiAl. Stwierdzono obecność licznych tlenków typowych dla procesu natryskiwania plazmowego w warunkach ciśnienia atmosferycznego (APS). Wytworzona warstwa pośrednia miała budowę charakterystyczną dla procesu niskoaktywnego. Zewnętrzną warstwę ceramiczną (tlenek cyrkonu stabilizowany tlenkiem itru) osadzono metodą natryskiwania plazmowego APS. Uzyskana wielowarstwowa powłokowa bariera cieplna może stanowić alternatywę dla konwencjonalnych powłok TBC stosowanych na elementach komory spalania i złożonych z międzywarstwy na bazie stopu MeCrAlY oraz warstwy ceramicznej ZrO2-Y2O3. Niewielka grubość powłoki w porównaniu z konwencjonalnymi powłokami TBC natryskiwanymi plazmowo pozwoli na jej zastosowanie również do ochrony powierzchni łopatek turbiny silnika lotniczego.

EN

Dynamical development of aviation industry is connected with the increase of passengers quantity and determines the research on more advanced aircraft engines construction. The usage of thermal barrier coatings (TBC) is the most advanced way of protecting the turbine blade surface and combustion chamber elements, against high temeprature and corrosive influence of the exhaust gases. The TBC coatings consist of two layers, that introduce different functionality. The aluminide layer obtained with diffusive methods or multicomponent MeCrAlY alloy form the inner layer. It protects the base material against oxidation and compensates the differences in physical properties between the outer layer and the base material. The outer layer is yttrium oxide stabilized zirconium oxide. It provides the thermal isolation. One introduced in the article the microstructure characteristics of the thermal barrier coating with the gradient, mulitlayer structure, obtained on the surface of Re 80 nickel superalloy. The bond-coat was deposited during the plasma spraying process in the conditions of atmospheric pressure (APS) of the multicomponent MeCrAlY alloy, followed by submission it to the gasaluminizing process. The microstructure and chemical composition analysis proofed the increase of aluminium content in the near-surface zone (up to 40% at.) and the formation of grains of the NiAl phase. One confirmed the existence of many other oxides, characteristic for the plasma spraying proces under atmospheric pressure (APS). The structure of created bond-coat was characteristic for the low activity processes. The outer ceramic layer (yttrium oxide stabilized zirconium oxide) wad deposited with a use of APS plasma spraying method. The obtained mulitlayer thermal barrier coating will create the alternative for the conventional TBC coating, which includes the bond-coat, formed on the basis of MeCrAlY alloy, and the ceramic ZrO2-Y2O3 layer used for combustion chamber elements. Small thickness of the coating, in comparison to the conventional TBC coatings obtained during the plasma spraying process, will enable its application for protection of surface of the turbine blade in the construction of aircraft engines.

6

Modeling of residual stresses developed in thermal barrier coatings during thermal cycling

84%

Srivathsa B. , Alam M. Z. , Kamat S. V. , Das D. K.

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tom Vol. 16, no 3

869-883

EN

Thermal barrier coatings (TBCs) are widely used on Ni-based superalloy components of gas turbine engines. Although several mechanisms for the failure of the TBCs have been suggested, it is largely accepted that the durability of these coatings is primarily determined by the residual stresses that are introduced due to the growth of the TGO during operation. In the present study, the residual stress build-up in a TBC system during thermal cycling is modeled. A two-dimensional plane strain finite element analysis is carried out. The model includes both flat and undulated growth fronts for the TGO layer. The stress distribution pattern in the TBC system in the case of a planar TGO front was found to be markedly different from that of an undulated front. The ceramic layer was found to be prone to delamination at concave undulations.

7

Thermal barrier ZrO2 - Y2O3 obtained by plasma spraying method and laser melting

84%

Kobylańska-Szkaradek K.

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2009

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tom Vol. 36, nr 1

12-19

EN

Purpose: The aim of the paper is to determine the influence of laser melting upon the selected physical properties of ZrO2 - Y2O3 ceramic coatings deposited by APS (Air Plasma Spraying) method on super-alloys which function as TBC (Thermal Barriers Coatings). Design/methodology/approach: Laser melting which helps eliminate pores and other structural defects of coatings deposited by plasma spraying method should contribute to the improvement of their density and durability as thermal barriers. In order to prove the assumptions made in the paper, coatings featuring varied porosity and deposited upon the nickel base super-alloys surface with the initially sprayed NiCrAlY bond coat have been subjected to laser melting and then their structure, thermal conductivity and thermal life prediction in the conditions of cyclic temperature changes from 20 to 1200°C have been examined. Findings: It has been revealed that the coatings featuring low porosity laser melted on part of their thickness and heated up to about 700°C demonstrate the highest thermal life prediction under the conditions mentioned and at slightly lower thermal conductivity. Heating is intended to lower the structural stresses which are connected with the change of ceramic volume at crystallization as well as thermal stresses resulting from varied expansion of coating and metal substrate. Research limitations/implications: Low wettability of metal by ceramic which results from various surface tensions of these materials is the cause of their lower adhesion to the substrate during laser melting all through their thickness. It is so because delaminations occur between phases the boundary and cracks. Practical implications: The worked out conditions of laser melting might be used in the process of creation of ZrO2 - Y2O3 coats which feature high working durability upon super-alloy elements. Originality/value: It has been found that homogenization of chemical composition of coatings occurs during laser melting leading to the reduction of ZrO2 - Y2O3 phase with monoclinic lattice participation as well as to the reduction of structural stresses which accompany this phase transformation during heating and cooling process.

8

The application of tumble finishing in surface preparation process for deposition of TBC coatings

84%

Kotowski S. , Nowotnik A. , Sieniawski J. , Butkiewicz A.

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2017

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tom Vol. 38, nr 1

8--14

EN

Thermal barrier coatings (TBC) are widely used for protection of turbine blades against aggressive thermomechanical and chemical degradation during operation in hot section of aircraft engine. Quality and properties of TBC coating is strictly related to preparation of substrate material (grinding, and rounding off edges, polishing and cleaning). In the article, tumble finishing as method for surface preparation before deposition of thermal barrier coatings has been described. The process was performed for different types of ceramic feedstock and base material in order to obtain homogeneous roughness. Tumbling was carried out using centrifugal polishing machine. The research was divided into three stages. The first one consisted in investigation of the influence of rotational velocity and water flow, on the course of tumbling process. Afterwards, proper type of ceramic feedstock has been selected. During the last stage, ready-to-use recipes for polishing of samples made of for CMSX–4, Inconel® 718 and stainless steel 1.4016 were developed.

PL

W artykule przedstawiono procedurę wytwarzania powłokowych barier cieplnych (TBC) na przykładzie łopatki turbiny stosowanej jako element konstrukcji części gorącej silnika lotniczego. Opisano proces odlewania łopatki wykonanej z nadstopu niklu CMSX- 4, procedurę przygotowania powierzchni, obróbkę cieplną oraz metody wytwarzania dwuwarstwowej powłoki TBC; z metaliczną warstwą pośrednią oraz ceramiczną warstwą wierzchnią. Międzywarstwa i warstwa wierzchnia zostały wytworzone w procesie, odpowiednio, chemicznego osadzania z fazy gazowej (CVD) oraz fizycznego osadzania z fazy gazowej z odparowaniem za pomocą wiązki elektronów (EB-PVD). Obróbka wirowa jest jedną z metod przygotowania powierzchni materiału bazowego i międzywarstwy do osadzania warstw powłoki TBC. W trakcie badań wykonano obróbkę wirową dla różnych wartości przepływu wody, prędkości obrotowej komory roboczej (bębna) oraz typów wsadu ceramicznego (geometrii kształtek ceramicznych). Celem badań było opracowanie procedury przygotowania powierzchni próbek wykonanych z nadstopów niklu CMSX–4 i Inconel® 718 oraz stali nierdzewnej 1.4016.

9

Lifetime prediction on gas turbine components with thermal barrier coatings, using micromechanics

84%

Sjostrom S. , Burman J. , Jinnestrand M.

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tom Vol. 7, no 1

205-220

EN

Lifetime prediction of thermal barrier coatings on gas turbine hot components is described. Existing modelling strategies are discussed. A more fundamental strategy, based on micromechanical analyses of the coating system is finally presented.

10

Nowoczesne technologie wytwarzania powłokowych barier cieplnych w Laboratorium Badań Materiałów dla Przemysłu Lotniczego

67%

Sieniawski J. , Kubiak K. , Filip R. , Góral M. , Nowotnik A.

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tom Vol. 32, nr 4

734-737

PL

Dynamiczny rozwój lotnictwa cywilnego i wymagania dotyczące ochrony środowiska determinują rozwój zaawansowanych silników turbowentylatorowych o większych osiągach i mniejszym zużyciu paliwa. Jedną z możliwości sprostania tym wymaganiom jest podwyższenie temperatury pracy silnika. Wymaga to modyfikacji konstrukcji oraz zastosowania zaawansowanych materiałów na łopatki turbin oraz ochronnych warstw żaroodpornych. Najczęściej do ochrony powierzchni łopatek turbin są stosowane wielowarstwowe powłokowe bariery cieplne (TBC). Warstwę wewnętrzną - międzywarstwę - chroniącą przed oddziaływaniem korozyjnym spalin, stanowią dyfuzyjne warstwy aluminidkowe modyfikowane platyną lub warstwy złożone z wieloskładnikowych stopów typu MeCrAlY wytwarzane metodami fizycznego osadzania z fazy gazowej (PVD). Warstwa zewnętrzna zwykle jest złożona z tlenku cyrkonu stabilizowanego tlenkiem itru osadzanych metodą fizycznego osadzania z fazy gazowej z odparowaniem za pomocą wiązki elektronów (Electron Beam Physical Vapour Deposition, EB-PVD). W pracy przedstawiono nowoczesne metody wytwarzania powłok rozwijane w Uczelnianym Laboratorium Badań Materiałów dla Przemysłu Lotniczego Politechniki Rzeszowskiej (LBMPL). Obecnie prowadzone są w laboratorium badania nad wytwarzaniem dyfuzyjnych warstw aluminidkowych modyfikowanych hafnem oraz cyrkonem. Warstwy te powstają w procesie chemicznego osadzania z fazy gazowej (CVD). Jednocześnie są realizowane prace badawcze dotyczące modyfikowania platyną i palladem warstw aluminidkowych wytwarzanych metodą CVD. Stanowią one warstwy pośrednie dla warstw ceramicznych osadzanych metodami EB-PVD i LPPS-Thin Film. Badania doświadczalne są realizowane za pomocą urządzenia EB-PVD typu Smart Coater firmy ALD. Stanowi ono prototypowe rozwiązanie, pozwalające na wytwarzanie powłok ceramicznych na małej liczbie elementów konstrukcyjnych, np. łopatek turbin w celach badawczych. Inną rozwijaną technologię stanowi proces natryskiwania plazmowego pod obniżonym ciśnieniem cienkich warstw (LPPS Thin Film) opracowany przez firmę Suzler Metco. Cechą unikatową urządzenia LPPS-Thin Film jest możliwość odparowania cząstek proszku ceramicznego w strumieniu plazmy. Obniżenie ciśnienia oraz obecność fazy gazowej pozwala na uzyskanie warstw o budowie kolumnowej, o większej odporności na pękanie, charakterystycznych dla procesu EB-PVD. Jednocześnie w laboratorium są prowadzone badania odporności na utlenianie izotermiczne i cykliczne, korozję siarkową, odporność erozyjną, w tym w wysokiej temperaturze oraz oceny stopnia oddziaływania wytworzonych powłokowych barier cieplnych na właściwości mechaniczne materiału podłoża.

EN

Dynamic development of civil aviation and the requirements concerning the environment protection determine the development of advanced turbofans, characterized by better performance and lower fuel consumption. The increase of engine service temperature is one of possibilities to achieve this goal. It requires the modification of its construction and the application of advanced materials for turbine blades and the usage of protective and high temperature resistant coatings. The mulitlayer Thermal Barrier Coatings (TBC) are most often used for protection of turbine blades surface. The diffusion, platinum modified aluminide coatings or the MeCrAlY layers consisting of multicomponent alloys obtained with methods of physical vapour deposition (PVD) constitute the inner layer (bond-coat) which protects against the corrosive influence of exhaust gases. The outer layer consisting, in most cases, of yttrium oxide stabilized zirconium oxide deposited with method of physical vapour deposition, involves vaporization with a use of electron beam (Electron Beam Physical Vapour Deposition, EB-PVD). The modern techniques of coating deposition, developed in the Research and Development Laboratory for Aerospace Materials (LBMPL) at Rzeszow University of Technology are introduced in this paper. In the laboratory, there is currently a research on obtaining the diffusion hafnium or zirconium modified aluminide layer being conducted. Those layers are formed during the process of chemical vapour deposition (CVD). Simultaneously, one conducts a research on modifying of aluminide layers with platinum and palladium during the CVD process. They have an application as the bond-coats for ceramic layer deposited by EB-PVD i LPPSThin Film method. The experimental research are realized with a use of ALD Smart Coater EB-PVD device. It is the prototype machine, which allows to create, for scientific purposes, the ceramic coating on a small amount of construction elements i.e. turbine blades. The plasma spraying process under low pressure (LPPS Thin Film) developed by Sulzer Metco company is the alternative process for creating layers. The unique property of LPPS-Thin Film device is the possibility of ceramic powder particles vaporization in the plasma jet. Decrease of pressure and existence of gas phase are the factors that allow to form layer with columnar structure, that have better crack resistance and are characteristic for the EB-PVD process. Simultaneously, one conducts in the laboratory a research on isothermal oxidation resistance, sulfur corrosion resistance, erosion resistance (also for high temperature) and on assessment of influence of Thermal Barrier Coatings on the mechanical properties of base material.

11

Isothermal Oxidation of Thermal Barrier Coatings Deposited Using LPPS, CVD, and PS-PVD Methods on MAR M247 Nickel Superalloy

67%

Góral M. , Kubaszek T. , Pytel M.

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tom Vol. 44, nr 1

9--14

EN

The article presents the results of microstructural characterization of newly developed three-layer thermal barrier coating (TBC) after isothermal oxidation test. Bond coats were deposited by the overaluminizing of MCrAlY coating deposited by low-pressure plasma spraying (LPPS) process. The outer ceramic layer of yttria-stabilized zirconia was deposited by the plasma spray physical vapor deposition process. The TBCs with MCrAlY bond coat without aluminizing process was produced by LPPS as well. The isothermal oxidation test at 1,100°C for 1,000 h showed that the thickness of the thermally grown oxides alumina oxide layer on overaluminized bond coats was significantly thinner in comparison with conventional LPPS-sprayed MCrAlY bond coats. The possibility of the presence of NiAl and Ni3Al phases in the outer zone of overaluminized bond coat after the oxidation test was observed.

12

Microstructure, mechanical and thermal properties of YSZ thermal barrier coatings deposited by axial suspension plasma spraying

67%

Poliarus O. , Morgiel J. , Żórawski W. , Góral A. , Pomorska M. , Wojciechowski K. T. , Cherniushok O.

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tom Vol. 23, no. 2

art. no., e89, 2023

EN

Yttrium-stabilized zirconia (YSZ) thermal barrier coatings (TBCs) are indispensable elements of present-day turbine propulsion systems. The ones deposited with atmospheric plasma spraying (APS) are characterized by required low thermal conductivity, but they are unable to survive frequent thermomechanical loading and therefore their application is limited to parts remaining stationary. Expanding capability of TBCs is sought in various areas, but the one realized through modification of most proliferated apparatus used for plasma spraying (PS) (from radial to axial injection) and substituting micrometric powders with the nano-structured suspension needs least changes in the industry established procedures and offers the highest property improvement. The present experiment covered the deposition of ZrO2-8Y2O3 YSZ TBC using both atmospheric and suspension PS processes. They were performed with commercial micrometric and nano-structured YSZ (8% Y2O3) powders. The coatings morphology and microstructure were characterized with 3D profilometry, scanning and transmission electron microscopy (SEM/TEM) methods. Finally, the coating’s hardness and heat conductivity were measured. This complex approach allowed to state that PS of micrometric t’-ZrO2 powder having an admixture of m-ZrO2 phase is capable of only partial improvement in its homogenization. However, the suspension PS process of nano-structured powder eliminated any traces of the monoclinic phase from the coating. The TEM microstructure observations indicated that the suspension PS coating is built by in-flight solidified droplets as well as by the melted ones flattened on arrival. A surface layer of liquefied material on solid droplets increases their adhesion to surface asperities promoting pseudo-columnar growth of the coating. The preservation of monotonic slow increase of thermal conductivity during heating of the suspension PS coating means, that its pseudo-columnar microstructure is better suited to withstand high strains during such treatment.

13

The formation of pyrochlores during plasma spraying of REO and zirconia oxides powder mixture

67%

Kubaszek T. , Nowak W. J. , Pędrak P. , Góral M. , Rybus K. , Ślemp K.

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tom Vol. 3, No 2

141--147

EN

The pyrochlores are the promising low-thermal conductive materials for Thermal Barrier Coatings applications. In present work the concept of pyrochlore formation during APS spraying of ZrO2 and ReO was analyzed. The specially prepared agglomerated mixtures of ZrO2 with Nd2O3, Yb2O3, Er2O3 and Gd2O3 oxides were plasma sprayed using A60 plasma torch on NiCoCrAlY-type bond coat. The influence of plasma gasses composition on coatings’ microstructure was investigated. The results of XRD phase analysis proved formation of pyrochlores from Gd2O3 +ZrO2 and Nd2O3+ZrO2 mixtures. The formation of Er4O12Zr3 from Er2O3+ ZrO2 mixture as well as Zr3Yb4 from Yb2O3+ ZrO2 powder was detected. The presence of pure rare earth oxides (REO) and zirconia oxides was observed in all types of sprayed coatings. The microstructural assessment showed differences in porosity and thickness of obtained ceramic coatings depending of type of REO oxides. The analysis of results showed that it is possible to obtain pyrochlore ceramic coatings from pure oxides mixture. The plasma energy was not efficient for full formation of pyrochlores, therefore the presence of pure oxides was observed.