Heat-Resistance Tests of High-Temperature Composite Materials via Laser Heating in a Supersonic Flow
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AND MASS TRANSFER AND PHYSICAL GASDYNAMICS
Heat-Resistance Tests of High-Temperature Composite Materials via Laser Heating in a Supersonic Flow K. Yu. Aref’eva, b, *, S. V. Kruchkova, b, **, A. V. Glushnevac, A. S. Savelievc, E. E. Sonc, A. S. Boreishod, and M. Yu. Khomskiid aCentral
Institute of Aviation Motors, Moscow, 111116 Russia Bauman Moscow State Technical University, Moscow, 105005 Russia c Joint Institute for High Temperatures, Russian Academy of Sciences, Moscow, 125412 Russia d Laser Systems LLC, St. Petersburg, 198515 Russia *e-mail: [email protected] **e-mail: [email protected] b
Received December 12, 2019; revised December 24, 2019; accepted December 24, 2019
Abstract—A method is proposed for the study of the heat resistance of samples of high-temperature composite materials via local laser heating of their surface in a supersonic flow. The performed studies allow the strategic selection of high-temperature materials based on the intensity of erosion with simultaneous laser and gasdynamic effects. The ablation rates of composite materials were experimentally determined at implemented surface temperatures of 2100–2300 K and blowing with a supersonic flow at a Mach number M = 2. The effect of the various additive materials, including carbides and oxides of Hf, Si, Ta, and Zr, on the ablation rate was studied. The data can be used as recommendations in the selection of formulations for high-temperature composite materials. DOI: 10.1134/S0018151X20030025
INTRODUCTION Currently, one of the current trends in the development of technical systems is an increase in their share of the use of composite materials (CMs) [1, 2]. This is due to the unique properties of various CMs. One of the directions of CM development is the creation of high-temperature CMs (HTCMs), including those capable of functioning in an oxidizing environment [3]. The introduction of HTCMs is important for aerospace, oil and gas, nuclear, and other industries. HTCMs can be used in structural elements of intraatmospheric aircraft and their engines [4, 5], heatloaded elements of ground and object power plants, and various technological and industrial installations. Preliminary data analysis [6–8] shows that the use of HTCMs will make it possible to increase the working temperature of the gas flow, reduce the structural mass, expand the operability ranges, and increase the resource of heat-loaded elements of various technical systems. Carbon HTCMs based on a ceramic matrix are promising materials with high oxidative stability. They are able to maintain their performance in an oxidizing environment for a long time at temperatures above 2000 K [8–10]. To date, there are a large number of varieties of carbon HTCMs that differ both in their chemical composition and in the preparation method [10]. Differences
in the technology of HTCM manufacturing significantly affect the material characteristics. Thus, comparative tests of samples are necessary before the selection of an HTCM for the manufacture of various parts operating at high tempera
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