Metal-Reinforced Ceramic Composites for Turbine Vanes

1972 ◽  
Author(s):  
S. A. Bortz
Keyword(s):  
Ceramic Matrix Composites ◽  
Ceramic Composites ◽  
Matrix Composites ◽  
Fiber Reinforced ◽  
Metal Fiber ◽  
Turbine Engine ◽  
Turbine Vanes ◽  
The Matrix ◽  
The Relationship ◽  
Structural Matrix

Experiments have been performed which indicate the potential of metal-fiber reinforced-ceramic matrix composites for use as a high temperature structural matrix. The results of this work reveal that metal-fiber reinforced ceramics obey compostie theory, and that after cracks occur in the matrix, a pseudo-ductility can be introduced into the composite. This toughness can be predicted from equations of work required to pull the fibers through the matrix. The relationship between strength, toughness, and crack depths, are dependent on the inter-facial bond between the fibers and matrix as well as fiber diameter and length. Based on the results of these experiments, multicomponent materials with superior resistance to failure from oxidation, thermal shock, and high mechanical stresses in air above 2400 F can be postulated. These materials have potential for use as gas turbine engine vanes.

scholarly journals Applications of Continuous Fiber Reinforced Ceramic Composites in Military Turbojet Engines

1996 ◽  
Author(s):  
Patrick Spriet ◽  
Georges Habarou
Keyword(s):  
Weight Ratio ◽  
Ceramic Matrix Composites ◽  
Thermodynamic Cycle ◽  
Ceramic Composites ◽  
Matrix Composites ◽  
Fiber Reinforced ◽  
Continuous Fiber ◽  
Operating Life ◽  
Performance Improvements ◽  
Temperature Capability

Over the last twenty years, significant performance improvements of turbojet engines have been achieved by optimizing engine thermodynamic cycle along with the introduction of new materials providing higher temperature capability and weight reduction. Metal Matrix Composites (MMC) and Ceramic Matrix Composites (CMC) are candidate material systems to meet the required thrust-to-weight ratio of 15 or higher. Continuous fiber reinforced ceramic composites, which have been developed by SEP for more than 15 years for thermostructural applications in oxidative environment, aim at increased operating temperature over superalloys and intermetallic alloys. This paper is a review of the main CMC component demonstrations performed by SEP over the last 10 years for turbojet engines along with an analysis of consequences on materials development and design methodology. The development status of a new thermostructural material specifically developed for turbojet environment with the prospect of higher design stress allowables and longer operating life at high temperature is presented.

Effects of Meso-Structure in Grinding of 2.5D Woven Fiber-Reinforced Ceramic Composites

2017 ◽  
Vol 1142 ◽  
pp. 152-158
Author(s):  
Y.G. Wang ◽  
Chao Ding ◽  
Bin Lin
Keyword(s):  
Ceramic Matrix Composites ◽  
Ceramic Composites ◽  
High Tech ◽  
Interface Debonding ◽  
Matrix Composites ◽  
Fiber Reinforced ◽  
Grinding Mechanism ◽  
Specific Frequency ◽  
Specific Fracture ◽  
Ae Signals

Fiber-reinforced ceramic composites are relatively promising materials in aerospace and other high-tech area. In this work, the grinding mechanism of 2.5-dimensional woven quartz fiber-reinforced ceramic matrix composites was researched by experimental analysis. The acoustic emission (AE) combined with wavelet analysis was adopted to evaluate the grinding process. The ratio of energy which may indicate the mode of fracture of the composites was used for analyzing each of the AE signals levels. The effects of meso-structure on AE frequency distribution have been discussed. It was found that that specific frequency band is corresponding to the specific fracture mode, such as fiber fracture, interface debonding and matrix fracture. It indicates that grinding mechanism is highly dependent on the meso-structure of the composites.

Constituent Development for Higher-Temperature Capable Ceramic Matrix Composites

2018 ◽  
Author(s):  
M. K. Cinibulk ◽  
Z. D. Apostolov ◽  
E. E. Boakye ◽  
T. S. Key ◽  
D. S. King
Keyword(s):  
Stress Rupture ◽  
Ceramic Matrix Composites ◽  
Matrix Composites ◽  
Turbine Engine ◽  
Sic Fiber ◽  
The Matrix ◽  
Higher Temperature ◽  
Oxidation Resistant ◽  
Service Environments ◽  
And Behavior

This paper highlights research that is addressing the need for improved high-temperature-capable CMCs, with a focus on CMC constituents and an understanding of their processing, microstructure, and behavior in relevant service environments. The most pervasive lifetime and temperature limitations for SiC/SiC CMCs are related to oxidation, creep and stress rupture of the fibers, oxidation-induced instability of the fibermatrix interface, and instability of the matrix at temperatures > 1400°C. Consequently, we are addressing these shortcomings by developing technologies to enable higher-temperature capable SiC fiber, oxidation-resistant fiber-matrix interfaces, and improvements in processing of refractory matrices for both turbine engine and hypersonic applications.

Multilayered Fiber-Reinforced Oxide Composites Produced by Lamination of Thermoplastic Prepregs

2014 ◽  
Vol 89 ◽  
pp. 145-150 ◽  
Author(s):  
Paula O. Guglielmi ◽  
Diego Blaese ◽  
Murilo Hablitzel ◽  
Gabriel Nunes ◽  
Victor R. Lauth ◽  
...  
Keyword(s):  
Bending Strength ◽  
Mechanical Performance ◽  
Hierarchical Structures ◽  
Ceramic Matrix Composites ◽  
Organic Matrix ◽  
Ceramic Composites ◽  
Processing Route ◽  
Failure Behavior ◽  
Matrix Composites ◽  
Fiber Reinforced

For advanced ceramic composites, affordable manufacturing is still the most essential shortcoming with respect to successful commercial use. This holds particularly for components made out of composites with complex hierarchical structures and high demands of mechanical performance and reliability at the same time, e.g. fiber-reinforced ceramic matrix composites (FRCMCs). Therefore, a new processing route is presented here, which is based on the lamination of thermoplastic prepregs. This route allows not only affordable manufacturing, but also advanced mechanical reliability. Powder metallurgy techniques are combined here with concepts from the prepreg technology in a route consisting of the following steps (a) manufacturing of 2 D prepregs using commercial fiber fabrics which are infiltrated with compounds of ceramic particles embedded in an organic matrix, (b) followed by respective stacking and joining, (c) burn out of the organic matrix and (d) sintering to consolidate the matrix. Composites consisting of a porous Al2O3/ZrO2 matrix, reinforced by 8 layers of NextelTM 610 fiber fabric exhibit a bending strength of ~440 MPa, with graceful failure behavior, e.g. a stepwise stress reduction after peak nominal stress. The fracture of these composites is controlled by a series of interfacial delamination events, which enhance energy dissipation during failure.

scholarly journals Micromechanical Modeling Tensile and Fatigue Behavior of Fiber-Reinforced Ceramic-Matrix Composites Considering Matrix Fragmentation and Closure

2021 ◽  
Vol 5 (7) ◽  
pp. 187
Author(s):  
Longbiao Li
Keyword(s):  
Fatigue Behavior ◽  
Constitutive Models ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Fatigue Loading ◽  
Micromechanical Modeling ◽  
Interface Debonding ◽  
Matrix Composites ◽  
Fiber Reinforced ◽  
The Matrix

In this paper, micromechanical constitutive models are developed to predict the tensile and fatigue behavior of fiber-reinforced ceramic-matrix composites (CMCs) considering matrix fragmentation and closure. Damage models of matrix fragmentation, interface debonding, and fiber’s failure are considered in the micromechanical analysis of tensile response, and the matrix fragmentation closure, interface debonding and repeated sliding are considered in the hysteresis response. Relationships between the matrix fragmentation and closure, tensile and fatigue response, and interface debonding and fiber’s failure are established. Experimental matrix fragmentation density, tensile curves, and fatigue hysteresis loops of mini, unidirectional, cross-ply, and 2D plain-woven SiC/SiC composites are predicted using the developed constitutive models. Matrix fragmentation density changes with increasing or decreasing applied stress, which affects the nonlinear strain of SiC/SiC composite under tensile loading, and the interface debonding and sliding range of SiC/SiC composite under fatigue loading.

scholarly journals Fiber-Matrix Interfaces in Ceramic Composites

1996 ◽  
Vol 458 ◽  
Author(s):  
T. M. Besmann ◽  
D. P. Stinton ◽  
E. R. Kupp ◽  
S. Shanmugham ◽  
P. K. Liaw
Keyword(s):  
Ceramic Matrix Composites ◽  
High Strength ◽  
Pyrolytic Carbon ◽  
Ceramic Composites ◽  
Matrix Composites ◽  
The Matrix ◽  
Oxidation Resistant ◽  
Oxide Matrix ◽  
Service Environments ◽  
Interface Materials

ABSTRACTThe mechanical properties of ceramic matrix composites (CMCs) are governed by the relationships between the matrix, the interface material, and the fibers. In non-oxide matrix systems the use of compliant pyrolytic carbon or BN have been demonstrated to be effective interface materials, allowing for absorption of mismatch stresses between fiber and matrix and offering a poorly bonded interface for crack deflection. The resulting materials have demonstrated remarkable strain/damage tolerance together with high strength. Carbon or BN, however, suffer from oxidative loss in many service environments, and thus there is a major search for oxidation resistant alternatives. This paper will review the issues related to developing a stable and effective interface material for non-oxide matrix CMCs.

Modeling of Creep of Misaligned Short-Fiber Reinforced Ceramic Composites

1992 ◽  
Vol 59 (1) ◽  
pp. 27-32 ◽  
Author(s):  
John R. Pachalis ◽  
Tsu-Wei Chou
Keyword(s):  
Creep Behavior ◽  
Elevated Temperatures ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Ceramic Composites ◽  
Short Fiber ◽  
Matrix Composites ◽  
Fiber Reinforced ◽  
Lag Model ◽  
Multiaxial Creep

A model is developed to predict the steady-state creep behavior of misaligned short-fiber-reinforced ceramic matrix composites. The approach is based on an advanced shear-lag model and uses the multiaxial creep law for the fibers and matrix. The analysis incorporates some unique characteristics of ceramic matrix composites, such as the fiber/matrix interface sliding effect, shear and axial loads carried by the matrix, and the fact that both the fibers and matrix creep at elevated temperatures. Several parameters are varied to determine their effect on the creep behavior.

SiC Fiber Reinforced Ceramic Matrix Composites for Turbine Engine Applications

2000 ◽  
Author(s):  
Kenneth Hatton ◽  
Dennis Landini ◽  
Stan Hemstad ◽  
R. Craig Robinson
Keyword(s):  
Silicon Carbide ◽  
Ceramic Matrix Composite ◽  
Chemical Vapor ◽  
Ceramic Matrix Composites ◽  
Ceramic Matrix ◽  
Chemical Vapor Infiltration ◽  
Matrix Composites ◽  
Fiber Reinforced ◽  
Turbine Engine ◽  
Nozzle Guide

Honeywell Advanced Composites Inc. (ACI) has been working with OEM’s to develop, fabricate, and test ceramic matrix composite (CMC) materials for partial and full replacement of hot section turbine engine components. Using Chemical Vapor Infiltration (CVI) technology, silicon carbide fiber reinforced silicon carbide matrix parts, such as full annular combustion liners and inserts for leading edges on nozzle guide vanes have been fabricated and tested.

Effect of temperature on matrix multicracking evolution of C/SiC fiber-reinforced ceramic-matrix composites

2020 ◽  
Vol 39 (1) ◽  
pp. 189-199
Author(s):  
Longbiao Li
Keyword(s):  
Strain Energy ◽  
Ceramic Matrix Composites ◽  
Critical Value ◽  
Matrix Cracking ◽  
Interface Debonding ◽  
Matrix Composites ◽  
Temperature Dependent ◽  
Damage State ◽  
The Matrix ◽  
Sic Composites

AbstractIn this paper, the temperature-dependent matrix multicracking evolution of carbon-fiber-reinforced silicon carbide ceramic-matrix composites (C/SiC CMCs) is investigated. The temperature-dependent composite microstress field is obtained by combining the shear-lag model and temperature-dependent material properties and damage models. The critical matrix strain energy criterion assumes that the strain energy in the matrix has a critical value. With increasing applied stress, when the matrix strain energy is higher than the critical value, more matrix cracks and interface debonding occur to dissipate the additional energy. Based on the composite damage state, the temperature-dependent matrix strain energy and its critical value are obtained. The relationships among applied stress, matrix cracking state, interface damage state, and environmental temperature are established. The effects of interfacial properties, material properties, and environmental temperature on temperature-dependent matrix multiple fracture evolution of C/SiC composites are analyzed. The experimental evolution of matrix multiple fracture and fraction of the interface debonding of C/SiC composites at elevated temperatures are predicted. When the interface shear stress increases, the debonding resistance at the interface increases, leading to the decrease of the debonding fraction at the interface, and the stress transfer capacity between the fiber and the matrix increases, leading to the higher first matrix cracking stress, saturation matrix cracking stress, and saturation matrix cracking density.

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