Ceramic Matrix Composites for High Pressure Turbine Vanes

Boyle, Robert; Parikh, Ankur H.; Nagpal, Vinod K.; Halbig, Michael C.; DiCarlo, James A.

doi:10.1115/gt2014-27136

Cited by 5 publications

(2 citation statements)

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“…Owing to the excellent specific modulus and strength, and low density and non-brittle fracture behavior [1], silicon carbide ceramic matrix composite (CMC-SiC) has more and more extensive applications in high thrust-to-weight ratio aeroengine [2,3] (turbine shroud [4], exhaust nozzle [5], combustion chamber, turbine guide vane, turbine blade, etc. [6][7][8][9]). The thermomechanical-oxygenic coupling service environment puts forward higher requirements on CMC-SiC.…”

Section: Introduction mentioning

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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Section: Introduction mentioning

confidence: 99%

Long-term ceramic matrix composite for aeroengine

Song

Cheng

et al. 2022

J Adv Ceram

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“…The low density and good mechanical and thermal properties of Ceramic Matrix Composites (CMCs) at high temperatures make them favoured materials for use in rocket nozzles, thermal protection systems and gas turbine engines (Boyle et al, 2014;Class, 2008;Marshall and Cox, 2008;Raether, 2013;Wood, 2013). The driver for use in such applications is the potential for higher thermal efficiencies and lower emissions (Evans and Naslain, 1995).…”

Section: Introductionmentioning

confidence: 99%

Effects of in-plane extension on transverse thermal conductivity of a carbon–carbon 8-harness satin weave composite

Zhang

Hayhurst

2016

International Journal of Damage Mechanics

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A finite element-based technique for coupled thermo-mechanical analysis of woven Ceramic MatrixComposites sheets is presented for the prediction of the degradation of transverse thermal transport behaviour with in-plane extension. The thermal conductivity-strain characteristics have been determined, at the tow level, from the properties of the constituent elements, and then extended to tows and composite. The non-linear thermal conductivity-extension behaviour of the tow has been discretised by multi-linear curves, and implemented in a user-defined subroutine in ABAQUS to model the behaviour of the homogenised orthotropic unidirectional tow and its matrix. By using this approach, an 8-Harness Satin weave HITCO C/C composite unit cell has then been analysed. The variation of through-thickness thermal conductivity degradation with in-plane extension has been predicted and compared with the results of experiments. Very good agreement has been achieved. Two classes of behaviour have been experimentally observed: one that exhibits a brittle response, and another that shows a quasi-ductile behaviour. Both classes of behaviour have been predicted and shown to relate, respectively, to strain localisation and instantaneous pull-out deactivation, without localisation being invoked. These responses are reflected directly in the predicted and experimental rates of decay of transverse thermal conductivity with axial extension. It is advocated that the reduction in transverse thermal conductivity with extension and damage can be used as a Structural Integrity Monitor for CMC operational components.

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Numerical method for the thermal analysis of a ceramic matrix composite turbine vane considering the spatial variation of the anisotropic thermal conductivity

Mao

Jiang

et al. 2017

Applied Thermal Engineering

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Ceramic Matrix Composites for High Pressure Turbine Vanes

Cited by 5 publications

References 0 publications

Long-term ceramic matrix composite for aeroengine

Long-term ceramic matrix composite for aeroengine

Effects of in-plane extension on transverse thermal conductivity of a carbon–carbon 8-harness satin weave composite

Numerical method for the thermal analysis of a ceramic matrix composite turbine vane considering the spatial variation of the anisotropic thermal conductivity

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