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

Morscher, Gregory N.

doi:10.1111/j.1744-7402.2010.02524.x

Cited by 12 publications

(9 citation statements)

References 15 publications

Supporting

Mentioning

Contrasting

Unclassified

Order By: Relevance

“…Also included is the predicted curve if an NRMI CMC were fabricated in the same manner using the developmental Super Sylramic-iBN fiber. For example, no matter the test conditions, the HNS CMC typically ruptures at ∼0.6% total strain; whereas the iBN CMC ruptures at ∼0.4% [38]. In Figure 7.2, one can see that the LM approach appears to be a good empirical method for predicting SiC/SiC rupture life in that the rupture strength data for various fiber types not only fall consistently near one best-fit curve for each type, but also the curves closely follow the creep ranking of the different SiC fiber types as measured on single fibers in Figure 7.1.…”

Section: Advances In Sic/sic Microstructural Design Methodsmentioning

confidence: 99%

Advances in SiC/SiC Composites for Aero‐Propulsion

DiCarlo¹

2014

Ceramic Matrix Composites

View full text Add to dashboard Cite

INTRODUCTIONSilicon carbide (SiC) ceramic matrix composites (CMCs) reinforced by continuous-length, high performance, smalldiameter (∼10 to 15 μm), polycrystalline SiC fibers are considered enabling materials for a variety of advanced applications where lightweight reusable structural materials are required to operate for long time periods within extreme high temperature environments. Today the first generations of SiC/SiC CMCs with thermo-structural capability to ∼1250 • C are being introduced into the hot-section components of military and commercial gas turbine engines [1,2]. In comparison to superalloy metallic components, which at best operate at as high as ∼1100 • C, these CMC components will not only offer reduced engine weight, but also reduced component cooling-air requirements. Reduction in cooling air would then have the additional engine benefits of improved thrust-to-weight ratio, reduced fuel burn, and reduced harmful exhaust emissions. In order to seek further increases in these engine benefits, research has been ongoing within NASA aimed at developing SiC/SiC CMCs with even higher structural reliability and temperature capability.The objective of this chapter is to detail, both fundamentally and practically, the key advances from recent SiC/SiC CMC research activities within NASA. Although these advances are primarily still under development and optimization, they do show various degrees of improvement over the materials and processes currently being implemented for SiC/SiC engine components. To this end, Section 7.2 presents information on the general constituent materials and process requirements for structurally reliable high temperature SiC/SiC engine components. Section 7.3 then discusses the primary fabrication routes currently being employed for production-ready SiC/SiC components in terms of their benefits and limitations. Section 7.4 then details recent advancements in the materials and processes for the SiC fiber, the fiber interfacial coating, the fiber geometry or architecture, the SiC-based matrix, and in the design methods for assembling these microstructural constituents into higher temperature and higher performance SiC/SiC composites and components. Where possible, CMC property data will be presented and analyzed that directly compares the materials and processes of the advanced approaches against those of current approaches. This property comparison will focus primarily on such key CMC properties as in-plane and thru-thickness tensile strength, thermal conductivity, creep resistance, and rupture behavior since it is these properties that directly control the CMC structural and upper temperature capability. Finally, Section 7.5 summarizes these results into current design guidelines for achieving SiC/SiC microstructures with improved intrinsic thermo-structural capability, and then discusses potential issues, such as thermo-mechanical shock, environmental attack, and creep-related residual stress development, which still require further research to understand whether they will be ...

show abstract

Section: Advances In Sic/sic Microstructural Design Methodsmentioning

confidence: 99%

Advances in SiC/SiC Composites for Aero‐Propulsion

DiCarlo¹

2014

Ceramic Matrix Composites

View full text Add to dashboard Cite

show abstract

“…Typically, the PL stress is considered to be a maximum design stress; however, for high temperature stress-rupture lives, it is necessary to operate well below PL stress and perhaps even below first AE event stress if very long times are desired (>1000 h). 30 Also, all of the creep data shown in this paper are essentially at or above the first AE event stress which indicates that at least tunnel cracking can be expected to occur during loading and creep.…”

Section: Creep Comparison Of Woven Melt-infiltrated Matrix Compositesmentioning

confidence: 95%

“…Consequently, increasing the fraction of fibers in the loading direction is expected to improve creep rupture properties for this 2D five-harness lay-up fiber architecture as well as other fiber architectures. 30 In addition, further improvements to fiber creep and rupture properties 40 should also result in improved composite and rupture properties.…”

Section: Stress-rupture Comparison Of Different Fiber Compositesmentioning

confidence: 99%

See 1 more Smart Citation

Tensile creep and rupture of 2D-woven SiC/SiC composites for high temperature applications

Morscher

2010

Journal of the European Ceramic Society

Self Cite

View full text Add to dashboard Cite

“…In the last several decades, significant efforts have been devoted to the development of SiC matrix composites reinforced with (Hi-)Nicalon fibers [8], Tyranno fibers [9] and Sylramic fibers [10], etc. Meanwhile, equal progress has been made in fields closely related, such as SiC nanowires [11] and SiC whiskers [12,13].…”

Section: Introductionmentioning

confidence: 99%