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

Liu, Xiaochong; Guo, Xiaojun; Xu, Youliang; Li, Longbiao; Zhu, Wang; Zeng, Yuqi; Li, Jian; Luo, Xiao; Hu, Xiaoan

doi:10.3390/ma14206104

Cited by 17 publications

(9 citation statements)

References 20 publications

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“…Figure 4A shows the aerodynamic load analysis of the guide vane. The maximum aerodynamic pressure occurred at the basin region of the guide vane, 8 and the value was σ = 1.6 MPa. The pressure at the back region of the guide vane was relatively low.…”

Section: Resultsmentioning

confidence: 98%

“…CMCs become the most promising alterative materials for advanced aero engine turbine parts 4–7 . The turbine parts work in a very harsh environment, that is, high temperature, thermal fatigue, thermal shock, and susception to oxidation and thermal corrosion 8 . Under the support of NASA's Ultra Efficient Engine Technology (UEET) program, Pratt & Whitney (P&W) and United Technologies Research Center (UTRC) designed and developed SiC/SiC turbine guide vanes (TGVs), which consisted of six plies of Sylramic SiC fiber cloth reinforced with chemical vapor infiltration (CVI) and melt‐infiltrated SiC matrix 9 .…”

Section: Introductionmentioning

confidence: 99%

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XCT damage evaluation and analysis of SiC/SiC turbine guide vanes after thermal shocks

Liu

Zhao²,

Guo³

et al. 2023

Int J Applied Ceramic Tech

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In this paper, the two-dimensional (2D) (0 • /90 • ) plain-woven Amosic-3 SiC/SiC turbine guide vane (TGV) was fabricated using the chemical vapor infiltration method. Thermal and stress analysis of the TGV was conducted using the finite element method analysis. Multiple thermal shock tests at T = 1250, 1350, 1400, 1420, 1450, 1470, and 1480 • C were conducted for N = 100, 100, 400, 300, 200, 200, and 700 cycles. After thermal shock tests, the surface damage of the TGV was observed visually, and the micro damage mechanism was analyzed using the scanning electronic microscopy. Micro X-ray computed tomography was adopted to characterize the internal damages in the SiC/SiC guide vanes. The delamination occurred at the positions approaching internal hollow, due to the weak binding force along the thickness direction and the high thermal shock stress caused by the temperature change. The diameter, area, volume, and sphericity distributions of the pores inside of the guide vanes were also obtained.

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Section: Resultsmentioning

confidence: 98%

Section: Introductionmentioning

confidence: 99%

XCT damage evaluation and analysis of SiC/SiC turbine guide vanes after thermal shocks

Liu

Zhao²,

Guo³

et al. 2023

Int J Applied Ceramic Tech

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“…The C/SiC ceramic-matrix composites (CMCs) have excellent properties such as high-temperature resistance, thermal shock resistance, high strength, toughness, hardness, wear resistance, chemical stability, design tolerance, and low density and thermal expansion coefficients [ 1 , 2 , 3 , 4 , 5 ]. It can meet the requirements of long service life at a high temperature of 1650 °C and has broad application prospects in high thrust-to-weight ratio (TWR) aero engines, hypersonic ramjet engines, space shuttle thermal protection systems (TPS), and so on [ 6 , 7 , 8 , 9 , 10 ]. The HERMES, MSTP, ARD, GSTP, and FLPP programs of the European Space Agency (ESA) and the NASP, ISTP, Future-X, Hyper-X, and OTV programs of NASA have carried out relevant research and demonstration verification tests on C/SiC TPS.…”

Section: Introductionmentioning

confidence: 99%

Design, Fabrication, and Mechanical Properties of T-700TM Multiaxial-Warp-Knitting–Needled–C/SiC Composite and Pin

Luo

He²,

Liu

et al. 2022

Materials

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In this paper, the 12k T-700TM Multiaxial-Warp-Knitting–Needle (MWK–N) C/SiC composite and pin were designed and fabricated using the isothermal chemical vapor infiltration (ICVI) method. The composite’s microstructure and mechanical properties were examined by subjection to tensile and interlaminar shear tests. Three types of double-shear tests were conducted for C/SiC pins, including shear loading perpendicularly, along, and at 45° off-axial to the lamination. The fracture surface of the tensile and shear failure specimens was observed under scanning electronic microscope (SEM). The relationships between the composite’s microstructure, mechanical properties, and damage mechanisms were established. The composite’s average tensile strength was σuts = 68.3 MPa and the average interlaminar shear strength was τu = 38.7 MPa. For MWK–N–C/SiC pins, the double-shear strength was τu = 76.5 MPa, 99.7 MPa, and 79.6 MPa for test types I, II, and III, respectively. Compared with MWK–C/SiC pins, the double-shear strength of MWK–N–C/SiC pins all decreased, i.e., 26.7%, 50.8%, and 8% for test types I, II, and III, respectively. The MWK–N–C/SiC composite and pins possessed high interlaminar shear strength and double-shear strength, due to the needled fiber in the thickness direction, low porosity (10–15%), and high composite density (2.0 g/cm3).

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“…SiC/SiC ceramic-matrix composites (CMCs) have already been applied in hot-section components of gas turbine engine, e.g., turbine guide vanes and blades, combustion chamber. 1-6…”

Section: Introductionmentioning

confidence: 99%

“…SiC/SiC ceramicmatrix composites (CMCs) have already been applied in hot-section components of gas turbine engine, e.g., turbine guide vanes and blades, combustion chamber. [1][2][3][4][5][6] Under tensile loading, matrix cracking and opening occur at low applied stress. [7][8][9] Forna-Kreutzer et al 10 observed the interface cracks, inclined cracks, and crack opening behavior in Nextel TM 720/Alumina oxide-oxide composite at room temperature and 1050 o C using X-ray computed micro-tomography (XCT) and digital volume correlation (DVC).…”

Section: Introductionmentioning

confidence: 99%

Interface wear effects in ceramic composite crack opening

2022

Journal of Composite Materials

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For fiber-reinforced ceramic-matrix composites (CMCs), crack opening behavior controls oxidation atmosphere ingress into the internal composite, which affects the operation reliability and durability of engineering CMC components. Under cyclic fatigue loading, interface wear affects the crack opening behavior in CMCs. In this paper, the stress/cyclic-dependent crack opening behavior in CMCs is analyzed considering interface wear effect. The analytical crack opening displacement (COD) and related damage parameters (e.g., interface debonding ratio (IDR)) are determined based on the microstress analysis in the fiber and the matrix. Experimental CODs of different matrix cracks in SiC/SiC minicomposite are predicted under tensile loading. Considering cyclic-dependent interface wear effect, CODs and related damage parameters are analyzed for different cycles. Theoretical relationships between the COD, peak stress level, cycle number, and composite constitutive properties are established. Effects of constitutive properties, peak stress level, and damage state on cyclic-dependent COD and related damage parameters are discussed. Under tensile loading, with increasing tensile stress, COD first increases nonlinearly and then linearly with applied stress corresponding to change of the interface debonding from partial to complete debonding. The increasing rate of COD curve is relatively low upon initial loading due to short interface debonding range. However, the increasing rate of COD curve decrease again at high stress level at the condition of complete interface debonding. Under cyclic fatigue loading, the change of interface debonding condition with increasing applied cycles affects the COD and IDR curves.

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

Cited by 17 publications

References 20 publications

XCT damage evaluation and analysis of SiC/SiC turbine guide vanes after thermal shocks

XCT damage evaluation and analysis of SiC/SiC turbine guide vanes after thermal shocks

Design, Fabrication, and Mechanical Properties of T-700TM Multiaxial-Warp-Knitting–Needled–C/SiC Composite and Pin

Interface wear effects in ceramic composite crack opening

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