Modeling the Thermostructural Stability of Meltinfiltrated SiC/SiC Composites

DiCarlo, James A.; Bhatt, Ramesh S.; McCue, Terry R.

doi:10.1002/9780470294826.ch67

Cited by 5 publications

(5 citation statements)

References 4 publications

(7 reference statements)

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“…Some of the strength loss can explained by time‐temperature‐dependent diffusion of the silicon through the CVI SiC cladding to the fibers, which then degrades the outer fiber coating and fibers as has been observed for annealed specimens above 1300°C 14 . The strength loss after annealing at 100 and 500 h at 1315°C would be expected to be about 5% and 15%, respectively 14,15 . However, this only accounts for about one‐third of the strength loss for crept specimens at 1315°C.…”

Section: Resultsmentioning

confidence: 92%

“… ‡ The data in parenthesis for 2D‐5HS includes the scatter from Morscher et al , 8,15 two different vendors, whereas the individual data values are from Morscher and Pujar 8 (the same vendor, GE, used to fabricate the other composites of this study) and was also used in Morscher et al 1 …”

Section: Resultsmentioning

confidence: 99%

“… RT as‐produced stress–strain after 1315°C creep, and retained RT stress–strain behavior of after‐creep (a) 3D‐O‐unbalanced‐R specimen and (b) 3D‐O‐unbalanced‐Z specimen plotted in the strain domain. The room‐temperature retained strength normalized by as‐produced room‐temperature strength for the specimens of this study and N24A composites from Bhatt and colleagues 14,15 is plotted in (c). …”

Section: Resultsmentioning

confidence: 99%

See 2 more Smart Citations

Tensile Creep of Melt‐Infiltrated SiC/SiC Composites with Unbalanced Sylramic‐iBN Fiber Architectures

Morscher¹

2010

Int J Applied Ceramic Tech

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The in-plane creep-rupture behavior at 13151C was measured in air for melt-infiltrated SiC/SiC composite panels reinforced by Sylramic-iBN SiC fibers with unbalanced three dimensional (3D)-woven and 2D-braided fiber architectures that displayed a high stress for the onset of through-thickness matrix cracking at room temperature. It was found that a significant improvement in the creep-rupture behavior at 13151C was observed, if the primary fiber direction was aligned with the direction of stress. Optical microscopy was used to examine postcreep microstructures in order to determine the extent of matrix cracking, and long-time rupture stress and strain conditions were identified for the different architectures.

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Section: Resultsmentioning

confidence: 92%

Section: Resultsmentioning

confidence: 99%

Section: Resultsmentioning

confidence: 99%

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Tensile Creep of Melt‐Infiltrated SiC/SiC Composites with Unbalanced Sylramic‐iBN Fiber Architectures

Morscher¹

2010

Int J Applied Ceramic Tech

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“…After SiC/SiC was exposed at 1400 ℃ for 500 h, the ultimate tensile strength decreased to about 50% of that before exposure. Dicarlo et al [58] further established a simple diffusion-based analytical model to predict the effect of stress-free thermal exposure on the residual tensile strength of MI SiC/SiC. It was meaningful to avoid the catastrophic damage if the duration can be properly predicted after MI SiC/SiC was fabricated.…”

Section: Melt Infiltration (Mi) Technologymentioning

confidence: 99%

Long-term ceramic matrix composite for aeroengine

Song

Cheng

et al. 2022

J Adv Ceram

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Three strategies were proposed to prolong the service life of continuous fiber-reinforced silicon carbide ceramic matrix composite (CMC-SiC), which served as thermal-structure components of aeroengine at thermo-mechanical-oxygenic coupling environment. As for some thermal-structure components with low working stress, improving the degree of densification was crucial to prolong the service life, and the related process approaches were recited. If the thermal-structure components worked under moderate stress, the matrix cracking stress (σmc) should be improved as far as possible. The fiber preform architecture, interface shear strength, residual thermal stress, and matrix strengthening were associated with σmc in this review. Introducing self-healing components was quite significant with the appearance of matrix microcracks when CMC-SiC worked at more severe environment for hundreds of hours. The damage can be sealed by glass phase originating from the reaction between self-healing components and oxygen. The effective self-healing temperature range of different self-healing components was first summarized and distinguished. The structure, composition, and preparation process of CMC-SiC should be systematically designed and optimized to achieve long duration target.

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“…This is the reason that the CMCs are being aggressively researched and developed for use in future gas turbine engines. [1][2][3][4][5][6][7] The potential of the CMCs in revolutionizing the performance of the gas turbine engines is shown schematically in Figure 1. 8 In this figure, the x-axis represents the approximate period of dominance in usage of the particular class of high-temperature materials (and associated cooling technologies), while the y-axis denotes the temperature capability of the material class in question.…”

Section: The Basics Of Ceramic-matrix Compositesmentioning

confidence: 99%

Multi-length-scale derivation of the room-temperature material constitutive model for SiC/SiC ceramic-matrix composites

Grujičić

Snipes

Galgalikar

et al. 2015

Proceedings of the Institution of Mechanical Engineers, Part L:

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In the present work, multi-length-scale physical and numerical analyses are used to derive a SiC/SiC ceramic matrix composite (CMC) material model suitable for use in a general room-temperature, finite element-based, structural/ damage analysis of gas turbine engine components. Due to its multi-length-scale character, the material model incorporates the effects of fiber/tow (e.g. the volume fraction of the filaments, thickness of the filament coatings, decohesion properties of the coating/matrix interfaces, quality, as quantified by the Weibull distribution parameters, of the filament, coating, and matrix materials, etc.) and ply/lamina (e.g. the 0 /90 cross-ply vs. plain-weave architectures, the extent of tow crimping in the case of the plain-weave plies, cohesive properties of the inter-ply boundaries, etc.) length-scale microstructural/architectural parameters on the mechanical response of the CMCs. To identify and quantify the contribution of the aforementioned parameters on the material response, detailed numerical procedures involving the representative volume elements and the virtual mechanical tests are developed and utilized. The resulting homogenized turbine-engine component-level material model is next integrated into a user-material subroutine and used, in conjunction with a commercial finite element program, to analyze the foreign object damage experienced by a toboggan-shaped turbine shroud segment. The results obtained clearly revealed the role different fiber/tow and ply/lamina microstructural parameters play in the structural/damage response of the gas-turbine CMC components.

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Modeling the Thermostructural Stability of Meltinfiltrated SiC/SiC Composites

Cited by 5 publications

References 4 publications

Tensile Creep of Melt‐Infiltrated SiC/SiC Composites with Unbalanced Sylramic‐iBN Fiber Architectures

Tensile Creep of Melt‐Infiltrated SiC/SiC Composites with Unbalanced Sylramic‐iBN Fiber Architectures

Long-term ceramic matrix composite for aeroengine

Multi-length-scale derivation of the room-temperature material constitutive model for SiC/SiC ceramic-matrix composites

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