Bending fatigue behavior in an advanced SiC/SiC ceramic matrix composite component at elevated temperature in air

Patel, Amit; Satô, Eiichi; Takagi, Takeshi; Shichijo, Naohiro

doi:10.1016/j.jcomc.2021.100127

Cited by 7 publications

(4 citation statements)

References 27 publications

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“…As in the scientific community, C/SiC braking materials have grabbed the public's curiosity. e C/SiC brake disk was first introduced in Porsche 911 GT2 in 2001 [31]. Elevator and crane emergency brakes have been made from brake materials of C/SiC.…”

Section: Ceramic Matrix Composite Brake Materials For Aircraftmentioning

confidence: 99%

A Comprehensive Study of Ceramic Matrix Composites for Space Applications

Dhanasekar¹,

Ganesan²,

Rani

et al. 2022

Advances in Materials Science and Engineering

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Ceramic matrix composites (CMCs) have grown in popularity as a material for a range of high as well as protection components, increasing the need to better understand the impacts of multiple machining methods. It is primarily composed of ceramic fibers embedded in the matrix. Ceramic materials, especially carbon fibers and carbon were used to create the matrix and fibers. These ceramics include a huge variety of non-metallic inorganic materials that are regularly utilized under high temperatures. The aircraft industry became revolutionized by this unique combination of materials, which made parts better resistant under extreme conditions as well as lighter than the earlier technology. The development, properties, and production of ceramic matrix composites, as well as space applications, are discussed in this article. Ceramic materials have an interesting set of properties, including great strength and stiffness under extremely high temperatures, chemical inertness, low density, etc. In CMC, ceramics are used in the matrix as well as reinforcement. The matrix material keeps things running smoothly while the reinforcement delivers unique special properties. Ceramic matrix composites are developed for applications that required high thermal and mechanical characteristics, which include nuclear power plants, aircraft, chemical plants, space structures, and transportation services. Even though advanced aircraft relies on high-performance propulsion systems, improving the total impulses over the total mass ratio for rocket engines becomes essential for improving their performance that demands reduced engine structural weight as well as higher component heat resistance. The evolution of new ultra-high-temperature composites having high-temperature resistance as well as low density that a substitute super alloy and refractory metal material has become so essential and laid the foundation for high-performance engine design. The benefits of continuous fiber- reinforced CMC with high-temperature engine designs have long been recognized as a better measure of a country’s ability to design and produce spacecraft, modern aircraft, and weapons. Ceramic matrix composites materials are used in various aircraft type engines, aircraft brake disks, high-temperature gas turbines components, slide bearing components, hot gas duct, flame holders and components for burners are made by using oxide CMCs.

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Section: Ceramic Matrix Composite Brake Materials For Aircraftmentioning

confidence: 99%

A Comprehensive Study of Ceramic Matrix Composites for Space Applications

Dhanasekar¹,

Ganesan²,

Rani

et al. 2022

Advances in Materials Science and Engineering

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“…The typical CMCs used in turbine engines consist of a SiC matrix and a reinforcing SiC fiber, and this combination can lead to a composite with superior mechanical properties under high temperatures [9][10][11][12]. However, these materials undergo rigorous operating conditions in the turbine engine that lead to durability and damage issues.…”

Section: Introductionmentioning

confidence: 99%

Thermo-Mechanical Stress Distributions in a Ceramic Matrix Composites Turbine Vane Coated with Environmental Barrier Coatings

Chen,

Fang,

Gao

et al. 2024

Coatings

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It is of great significance to obtain an accurate stress assessment when replacing traditional metal components with ceramic matrix composites (CMCs) in turbine engines. The current study aims to investigate the stress characteristics of CMCs turbine vanes with multilayer-structured environmental barrier coatings (EBCs) using numerical simulation techniques. A three-dimensional finite element model of CMCs turbine vanes coated with EBCs was formulated. The distribution of thermal residual stresses generated during the manufacturing process of EBCs and the distribution of stresses under different loading conditions were calculated and compared. The results show that the hoop stress (σ11) and spanwise stress (σ22) in the turbine vanes are significantly higher than the through-thickness stress (σ33) under coupled loads. The maximum hoop stress (σ11) is approximately 346 MPa. The thermal residual stress induced during the EBCs manufacturing process reaches a maximum of approximately 360 MPa. The loading conditions significantly influence the stress distribution of EBCs, and the stress distribution of EBCs exhibits certain regularities at different heights under varying loading conditions. These results enable us to gain a deeper understanding of the failure mechanism of CMCs/EBCs turbine vanes and can improve the optimization capabilities for these components.

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“…[6][7][8][9][10] Ceramic particles containing zirconium are particularly suitable for anti-ablation modification of materials due to the ultra-high melting point of the oxide. [11][12][13] Zhaoqi Niu et al 14 studied Zirconium chelated hybrid phenolic resin thermal insulation composites, and the results showed that the formation of ZrC and ZrO 2 thermal barrier ceramics is the main reason for enhanced thermal and anti-ablation properties. Masoud Salavati-Niasari et al [15][16][17][18][19][20][21] studied nanoparticles in the catalysis application.…”

Section: Introductionmentioning

confidence: 99%

Anti-ablation properties of ZrB₂ modified carbon/phenolic composites in plasma wind tunnel

Lin,

Huang,

Wang

et al. 2023

Journal of Composite Materials

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Improving the ablative resistance of carbon/phenolic (C/Ph) composites is an urgent need in the field of thermal protection of hypersonic vehicles. In this paper, novel C/Ph composites are fabricated by introducing different contents of ZrB2 ceramic particles, and the anti-ablation properties of the composites are tested in plasma wind tunnel. Under mainstream conditions with enthalpy of 21.84 MJ/kg, heat flux of 1.6 MW/m2, and pressure of 1.6 kPa, the effects of ZrB2 ceramic content on the thermal stability, linear ablation rate and surface temperature of C/Ph composites are further analyzed. The maximum ablative surface temperature is positively correlated with the content of ZrB2. As the ZrB2 content increases, the back face temperature of the materials decreases gradually, while the linear ablation rate increases slightly after a significant decrease. When the ablation time is 50 s, The linear ablation rate of the sample with 7% ZrB2 content is the lowest (0.0184 mm/s). These dates of the plasma wind tunnel test could provide a reference for applications of C/Ph composites. The oxidation of ZrB2 in the materials contributes significantly to improving its anti-ablation properties in severe environments. Accordingly, optimizing the ZrB2 content enables the development of high-performance C/Ph composites with enhanced thermal properties, and reduced ablation rates, making them well-suited for thermal protection applications.

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Bending fatigue behavior in an advanced SiC/SiC ceramic matrix composite component at elevated temperature in air

Cited by 7 publications

References 27 publications

A Comprehensive Study of Ceramic Matrix Composites for Space Applications

A Comprehensive Study of Ceramic Matrix Composites for Space Applications

Thermo-Mechanical Stress Distributions in a Ceramic Matrix Composites Turbine Vane Coated with Environmental Barrier Coatings

Anti-ablation properties of ZrB₂ modified carbon/phenolic composites in plasma wind tunnel

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Bending fatigue behavior in an advanced SiC/SiC ceramic matrix composite component at elevated temperature in air

Cited by 7 publications

References 27 publications

A Comprehensive Study of Ceramic Matrix Composites for Space Applications

A Comprehensive Study of Ceramic Matrix Composites for Space Applications

Thermo-Mechanical Stress Distributions in a Ceramic Matrix Composites Turbine Vane Coated with Environmental Barrier Coatings

Anti-ablation properties of ZrB2 modified carbon/phenolic composites in plasma wind tunnel

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Product

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Anti-ablation properties of ZrB₂ modified carbon/phenolic composites in plasma wind tunnel