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4 edition of Ultrasonic characterization of a platinum aluminide coating on a gas turbine blade found in the catalog.

Ultrasonic characterization of a platinum aluminide coating on a gas turbine blade

John MacQuarrie

Ultrasonic characterization of a platinum aluminide coating on a gas turbine blade

by John MacQuarrie

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Published by National Library of Canada = Bibliothèque nationale du Canada in Ottawa .
Written in English


Edition Notes

SeriesCanadian theses = Thèses canadiennes
The Physical Object
FormatMicroform
Pagination2 microfiches : negative.
ID Numbers
Open LibraryOL14726345M
ISBN 100315741473
OCLC/WorldCa29912222

  The thickness of a diffusion aluminide coating on a gas turbine engine component is typically about 10 to about micrometers. Diffusion aluminide coatings can be formed by vapor phase aluminiding (VPA), pack cementation, or chemical vapor deposition (CVD) techniques, although it is foreseeable that other techniques could be used as well. Cyclic Oxidation Behavior of Aluminide, Platinum Modified Aluminide, and MCrAlY Coatings on GTD J. Eng. Gas Turbines Power (January, ) Role of Platinum in Thermal Barrier Coatings Used in Gas Turbine Blade ApplicationsAuthor: J. Liburdi, V. Moravek, P. Lowden.

Similar measurements to above have been conducted on a turbine blade. Figure 3 shows a picture of the turbine blade. The six rod-like projections shown are surface­ normal vectors generated by the blade's computer aided design (CAD) model. The blade was scanned on the high and low pressure sides at 4 heights above the. ) []. With these ceramic coatings, gas turbines reach temperatures ranging from oC to oC, above the superalloy’s melting point (around oC) [1,15,19]. Figure 2 illustrates gas turbine operational temperatures as a function of materials development during the last decades [20]. Thus, whilst the primary role.

aluminide coatings were formed by the gas phase aluminizing technique and using the single step HTHA aluminizing process. In addition, the effect of pack composition on coating microstructures has been discussed. EXPERIMENTAL The coating apparatus used for the gas phase aluminizing process is shown schematically in Figure 1. Progress Toward a Tungsten Alloy Wire/High Temperature Alloy Composite Turbine Blade F.J. Ritzert and R.L. Dreshfield Lewis Research Center Cleveland, Ohio Prepared for the International Conference on Tungsten and Tungsten Alloys sponsored by the Metal Powder Industries Federation Washington, D.C., November , NASA.


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Ultrasonic characterization of a platinum aluminide coating on a gas turbine blade by John MacQuarrie Download PDF EPUB FB2

A platinum aluminide coating without prior platinum diffusion process contains PtAl 2 which is rich in aluminium reservoir with trace of Ni 2 Al 3.

The phases present in the platinum aluminide coating on CMLC DS blade without prior Pt diffusion is shown in Fig. The diffusion treatment of platinum electroplating allows enriching the Cited by: In this operation, a gas turbine is taken apart, each blade is dismantled, its surface cleaned and a new coating applied.

With, on one hand, the prospect of coating failure leading to catastrophic blade loss, and on the other hand an extremely expensive maintenance process, it is no surprise that much research is dedicated to improving the. This work presents the degradation mechanism of the platinum modified aluminide diffusion coating of the GTD SC Ni-base superalloy turbine blades after h of exposition at different thermal cycles (critical heating temperatures reported ~°C and °C).

The initial coating condition and the evolution of degradation were characterized applying conventional microscopy and Cited by: 1. Thus, another blade was cleaned by this method prior to aluminizing.

Fig. 5 shows the microstructure of the aluminide coating on an oxide free internal surface. The microstructure and thickness of the coating are acceptable. Although some residual oxide particles are still present within the coating, the diffusion process has not been hindered and IDZ layer has been : Mahdi Bozorg Nezhad-Nobijari, Michael Isakhani-Zakaria, Ali Bakhshi.

Journal Article: Ultrasonic Detection of Delamination and Material Characterization of Thermal Barrier Coatings. The Zr modified aluminide coatings is an alternative concept for replacing Pt-modified aluminide bondcoat for thermal barrier coatings.

In the paper the influence of process parameters on the chemical composition and the thickness of aluminide coatings will be presented. The zirconia-doped aluminide coating was deposited on turbine blades made from ZS6K nickel superalloy during the low Cited by: 1.

coating, and almost all of the remainder were discarded after a further hours. With the aim of finding a coating that would serve for engine operating hours they have assess- ed: nickel aluminides supplied by two different vendors, platinum-modified aluminide, platinum.

ADVANCED MATERIALS AND COATINGS FOR FUTURE GAS TURBINE APPLICATIONS Magnetron sputtering is a very versatile process to produce coatings of almost any chemistry, first explored in the early ’s as a deposition process for titanium matrices on monofilaments [8].

Matrix deposition onto the fibers is the first. Platinum Aluminide Coatings on Turbine Blades Q. I would like to know, why the crack develops when platinum aluminide is coated on the gas turbine blades. What are the implications of it. What might be the causes. Shashidhar U.G Simulation Center, Bangalore, India.

Request PDF | The Influence of Turbine Blade Geometry and Process Parameters on the Structure of Zr Modified Aluminide Coatings Deposited by CVD Method on the ZS6K Nickel Superalloy | The Zr. Degradation of Aluminide Coating The aluminide coating on grain P-NiAl structure in the HPT blade consisted of a coarse the outer containing Tic, layer and a M23C6 carbides and sigma phases.

diffusion zone Three modes of coating degradation have been observed in the service exposed turbine blades. We claim: 1. A method of improving oxidation resistance of a platinum modified aluminide diffusion coating on a substrate, comprising electroplating the substrate with a layer comprising platinum from an aqueous caustic electroplating solution based on a hydroxide solution and aluminizing the electroplated substrate at an elevated temperature to grow a platinum modified aluminide diffusion.

Thermal barrier coatings (TBCs) are deposited on the turbine blade to reduce the temperature of underlying substrate, as well as providing protection against the oxidation and hot corrosion from high temperature gas. Optimal ceramic top-coat thickness distribution on the blade can improve the performance and efficiency of the coatings.

Design of the coatings thickness is a multiobjective Cited by: 5. Hot corrosion is a serious problem in gas turbines due to poor quality fuels which contain Na, V, S and Cl. To resolve the problem, Cr-aluminide was coated on INLC superalloy with a two steps.

An investigation was carried out to determine the thermal stability of a platinum aluminide coating on the directionally solidified alloy MAR M and its single-crystal version alloy, atand °C.

The morphology, structure and microchemical composition of the coating were characterized using scanning electron microscopy, transmission electron microscopy, energy Cited by: An ion-plasma method for depositing alloy diffusion aluminide coatings on high-temperature alloys, which favorably differs from the traditional processes, is considered.

The special features of formation of ion-plasma diffusion coatings on the surface of high-temperature alloys in single-stage and double-stage processes are by: 3.

A platinum-silicon powder is electrophoretically deposited on a nickel or cobalt base superalloy substrate. The deposited powder is heated to form a transient liquid phase on the substrate and initiate diffusion of Pt and Si into the substrate.

An aluminum-chromium powder is then electrophoretically deposited on the Pt-Si enriched substrate and diffusion heat treated to form a corrosion- and Cited by: example of corrosion is illustrated in Fig. 1, where an uncoated gas turbine blade is compared with an aluminide coated blade.

Both blades were removed and inspected after hr sea flight service at low altitude. Fig. Illustration of the corrosion effect of an uncoated (left) and a.

Ultrasonic Characterization The samples were studied in two ways. The ultrasonic attenuation was measured in the frequency range from about 5 to i00 MHz on samples A and B with nominally similar pore size distributions.

The shear wave backscattered power was measured in the frequency range MHz on samples C and A described in detail in the. terms of the dissolution of coating grain boundaries once the solution has passed through the oxide scales.

Keywords: soft chemical stripping, aluminide coating, oxide scales, Ni-base superalloy. Introduction. During the last decades, the temperature of gas turbine engines has been increased in order to improve the combustion by: 9.

distribution of a TBC coating on a gas turbine blade is presented and discussed. Application of the coating deposition model in combination with the OLP technique enables a full-cycle digital coating program development, considerably optimizing development time and costs.The blade tips of gas turbine blades, As the coating on the blade deteriorates the size and/or velocity of the resulting acoustic wave changes.

This is an indication that a blade must be serviced. Chimenti D.E. Review of air-coupled ultrasonic materials characterization. Ultrasonics. ; – doi: Cited by: 4.HEFAT 9th International Conference on Heat Transfer, Fluid Mechanics and Thermodynamics 16 – 18 July Malta EXPERIMENTAL STUDIES ON THERMAL PROTECTIVE COATING FOR LOW PRESSURE GAS TURBINE BLADES Vinoth Kumar Annamalai., Vijay Anand M., Jerish Duthie J., Archana S., Srinivasan K † and Sanal Kumar V.R.* †Hindustan Aeronautics Limited, Bangalore.