Effect of thermal cycling of SiCf/SiC composites on their mechanical properties

Udayakumar, A.; Stalin, M.; Abhayalakshmi, M.B.; Hariharan, Ramya; Balasubramanian, M.

doi:10.1016/j.jnucmat.2013.04.067

Cited by 13 publications

(6 citation statements)

References 16 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…The damage of matrix cracking and delamination induced by thermal shock was determined using the flexure testing and dynamic resonance measurement. Udayakumar et al [12] investigated the effect of thermal cycling of 2D plain-woven SiC/SiC composites on the mechanical properties, e.g., the proportional limit stress, percentage elongation, fracture toughness, and interfacial bonding strength. Zhang et al [13] investigated the effect of thermal cycles between 900 and 300 • C in air atmosphere on the tensile properties of 2.5D woven C/SiC composite.…”

Section: Introductionmentioning

confidence: 99%

Cyclic Thermal Shock Damage Behavior in CVI SiC/SiC High-Pressure Turbine Twin Guide Vanes

Liu

Guo²,

Xu³

et al. 2021

Materials

View full text Add to dashboard Cite

In this paper, the SiC/SiC high-pressure turbine twin guide vanes were fabricated using the chemical vapor infiltration (CVI) method. Cyclic thermal shock tests at different target temperatures (i.e., 1400, 1450, and 1480 °C) in a gas environment were conducted to investigate the damage mechanisms and failure modes. During the thermal shock test, large spalling areas appeared on the leading edge and back region. After 400 thermal shock cycles, the spalling area of the coating at the basin and back region of the guide vane was more than 30%, and the whole guide vane turned gray, due to the formation of SiO2. When the thermal shock temperature increased from 1400 to 1450 and 1480 °C, the spalling area of the basin and the back region of the guide vane did not increase significantly, but the delamination occurred at the tenon, upper surface of the guide vane near the trailing edge of the guide vane. Through the X-ray Computed Tomography (XCT) analysis for the guide vanes before and after thermal shock, there was no obvious damage inside of guide vanes. The oxidation of SiC coating and the formation of SiO2 protects the internal fibers from oxidation and damage. Further investigation on the effect of thermal shock on the mechanical properties of SiC/SiC composites should be conducted in the future.

show abstract

Section: Introductionmentioning

confidence: 99%

Cyclic Thermal Shock Damage Behavior in CVI SiC/SiC High-Pressure Turbine Twin Guide Vanes

Liu

Guo²,

Xu³

et al. 2021

Materials

View full text Add to dashboard Cite

show abstract

“…Continuous SiC/SiC fiber-reinforced ceramic-matrix composites (CMCs) have excellent properties such as high specific strength, high specific modulus, wear resistance, oxidation resistance, corrosion resistance, radiation resistance, and insensitivity to cracks and noncatastrophic fracture, which make it a new type of thermal structural material in the application prospects of aviation, aerospace, and energy [1][2][3]. SiC/SiC composites are mainly used for hot section components of high-performance aeroengines and industrial gas turbines and have potential applications in nuclear fusion reactors and fission reactors [4][5][6][7][8][9]. Solar Turbines Company uses SiC/SiC as the combustion chamber lining of Solar's Centaur 505 engine.…”

Section: Introductionmentioning

confidence: 99%

Temperature-dependent proportional limit stress of SiC/SiC fiber-reinforced ceramic-matrix composites

2020

High Temperature Materials and Processes

View full text Add to dashboard Cite

AbstractIn this paper, the temperature-dependent proportional limit stress (PLS) of SiC/SiC fiber-reinforced ceramic-matrix composites (CMCs) is investigated using the micromechanical approach. The PLS of SiC/SiC is predicted using an energy balance approach considering the effect of environment temperature. The relation between the environment temperature, PLS, and composite damage state is established. The effects of the fiber volume, interface properties, and matrix properties on the temperature-dependent PLS and composite damage state of SiC/SiC composite are analyzed. The experimental PLS and interface debonding length of 2D SiC/SiC composites with the PyC and BN interphase at elevated temperatures are predicted. The temperature-dependent PLS of SiC/SiC composite increases with the fiber volume, interface shear stress and interface debonding energy, and the matrix fracture energy and decreases with the interface frictional coefficient at the same temperature.

show abstract

“…The flexural strength and Young's modulus decreased and the internal friction increased with increasing of the applied cycle numbers, attributed to the viscous flow of the glass matrix, the oxidation of the fiber/matrix interface and fibers. Udayakumar et al 8) investigated the effect of thermal cycling on the mechanical properties of Nicalon•-SiC/SiC composite at the elevated temperature between 413 and 1273 K. The matrix microcrackings are generated under thermal fatigue cycling, leading to the oxidation of the BN interface and the strengthen of the fiber/matrix bonding. Mei and Cheng 9),10) investigated the strain response of a C/SiC composite simultaneously subjected to the thermal fatigue cycling and mechanical cycling in an oxidizing atmosphere.…”

Section: Introductionmentioning

confidence: 99%

Damage and fracture of fiber-reinforced ceramic-matrix composites under thermal fatigue loading in oxidizing atmosphere

2019

J. Ceram. Soc. Japan

View full text Add to dashboard Cite

In this paper, the damage and fracture of fiber-reinforced ceramic-matrix composites (CMCs) subjected to thermal cyclic fatigue loading at elevated temperatures in oxidizing atmosphere are investigated. The temperature/ cyclic dependent fiber/matrix interface shear stress is determined as a function of testing temperature, applied cycle number and material properties, which affects multiple thermal fatigue damage mechanisms. The microstress field of the thermal fatigue damaged composite is analyzed using the Budiansky-Hutchinson-Evans shear-lag model, considering matrix stochastic cracking, fiber/matrix interface debonding/sliding and fibers fracture. The matrix stochastic cracking, fiber/matrix interface debonding and sliding, fibers fracture in the interface damage zones are determined using the micromechanical approach. The relationships between the thermal fatigue cycling, multiple thermal fatigue damage mechanisms, fatigue hysteresis-based damage parameters and thermal fatigue lifetime are established. The effects of fiber/matrix interface properties, fiber radius, fiber volume fraction, matrix crack spacing and fatigue peak stress on thermal fatigue damage evolution in fiberreinforced CMCs are analyzed. The thermal fatigue damage evolution and lifetime prediction of two different fiber-reinforced CMCs, i.e., cross-ply SiC/MAS and 2D SiC/SiC composites, subjected to thermal cycling fatigue in oxidizing atmosphere are predicted.

show abstract

Effect of thermal cycling of SiCf/SiC composites on their mechanical properties

Cited by 13 publications

References 16 publications

Cyclic Thermal Shock Damage Behavior in CVI SiC/SiC High-Pressure Turbine Twin Guide Vanes

Cyclic Thermal Shock Damage Behavior in CVI SiC/SiC High-Pressure Turbine Twin Guide Vanes

Temperature-dependent proportional limit stress of SiC/SiC fiber-reinforced ceramic-matrix composites

Damage and fracture of fiber-reinforced ceramic-matrix composites under thermal fatigue loading in oxidizing atmosphere

Contact Info

Product

Resources

About