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Ceramic matrix composite
About: Ceramic matrix composite is a research topic. Over the lifetime, 7807 publications have been published within this topic receiving 117020 citations.
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24 Dec 1996TL;DR: An abrasive coating suitable for forming an abrasive blade tip of a gas turbine engine is described in this paper, which is capable of abrading a ceramic shroud at elevated temperatures during the in-service operation of the engine, and being resistant to oxidation and hot corrosion within the engine environment.
Abstract: An abrasive coating suitable for forming an abrasive blade tip of a gas turbine engine. The coating is characterized as being capable of abrading a ceramic shroud at elevated temperatures during the in-service operation of the engine, and being resistant to oxidation and hot corrosion within the engine environment. The abrasive coating includes an MCrAl alloy layer, a ceramic layer overlying the alloy layer so as to form an outer surface of the abrasive coating, and abrasive particles dispersed between the alloy layer and the ceramic layer so that at least some of the abrasive particles are partially embedded in the alloy layer and also partially embedded in the ceramic layer. In addition, at least some of the abrasive particles project above the outer surface of the abrasive coating formed by the ceramic layer.
54 citations
TL;DR: In this article, four parameters have been derived from these measurements: the compliance change caused by matrix cracking, the frictional resistance of the interface, the interface debond resistance, and the residual stress.
Abstract: Hysteresis measurements obtained on 0/90 SiC/CAS and SiC/SiC have been used to analyze the interface responses. Four parameters have been derived from these measurements. These relate to the compliance change caused by matrix cracking, the frictional resistance of the interface, the interface debond resistance, and the residual stress. These parameters have been used to predict the stress/strain curves. Preliminary estimates of stress partitioning between the plies have been used to estimate constituent properties, such as the friction stress.
54 citations
TL;DR: In this article, the microstructure of the composite coating was characterized by X-ray diffraction, scanning electron microscopy and transmission electron microscope, respectively, and the results indicated that the composite composite coating exhibited dense and crack-free micro-structure with a number of spherical α-Fe and γ-Al 2 O 3 nano-grains embedded within equiaxed and columnar matrix.
53 citations
01 Jan 2001
TL;DR: In this paper, the failure strain of the matrix is lower than that of the fibers, whereas it is the reverse in most polymer or metal matrix composites, which is referred to as inverse composites.
Abstract: Ceramic matrix composites (CMCs) generally consist of ceramic fibers or whiskers in a ceramic matrix. CMCs are designed to overcome the main drawback of monolithic ceramics, namely their brittleness. They are referred to as inverse composites, which is to say that the failure strain of the matrix is lower than the failure strain of the fibers, whereas it is the reverse in most polymer or metal matrix composites. Hence, under load it is the matrix which fails first. In order to prevent an early failure of the brittle fibers when the matrix starts to microcrack, the fiber/matrix (FM) bonding should be controlled during processing. CMCs are tough materials and display a high failure stress when the FM bonding is not too strong or too weak, which is usually achieved through the use of a fiber coating referred to as the interphase. The fabrication of CMCs requires specific processing techniques. Gas-or liquid-phase routes (or a combination of both), in which the interphase and the matrix are formed around the fibers from gaseous or liquid precursors, are usually preferred. CMCs are used as thermostructural materials under severe service conditions, for example, high temperatures under load and in corrosive atmospheres, such as combustion gases. The most commonly used CMCs are nonoxide CMCs, namely carbon/carbon (C/C), carbon/silicon carbide (C/SiC), and silicon carbide/silicon carbide (SiC/SiC), the fibers being specified first.
53 citations
TL;DR: In this paper, a hybrid thermal protection system for aerospace applications based on carbon-bonded carbon fiber composite (CALCARB ® ) and ceramic matrix composites have been investigated.
Abstract: Hybrid thermal protection systems for aerospace applications based on carbon-bonded carbon fiber composite (CALCARB ® ) and ceramic matrix composites have been investigated. Two types of ceramic composite materials were considered, C f /SiC (SiCARBON™) and C/C-SiC. The ablative material and the ceramic matrix composite were joined using alumina, graphite and zirconia-zirconium silicate based commercial high temperature adhesives and their performance on thermal shock tests was evaluated. Microstructural analysis of the joints after thermal shock tests was conducted using optical microscopy and scanning electron microscopy (SEM) coupled with energy dispersive spectroscopy (EDS). Both material combinations survive the thermal shock tests for the structures in which zirconia-zirconium silicate and graphite based adhesives were employed.
53 citations