Corrigendum to “Spiderweb inspired SiC/SiC composite aero-engine integrated turbine rotor and its multi-scale simulation” (Composites Part B (2025) 307, (S1359836825008261), (10.1016/j.compositesb.2025.112920))

Due to the lack of citation explanation for the experimental data sources used in the validation of the simulation model established for this work, in this corrigendum, we add the necessary references to address the omissions in the original publication. Added reference. 4. Experimental validation. Fig. 3. Standard specimen tensile test [48,49]. Fig. 4. Turbine disk experimental device diagram and load spectrum [48–52]. 5. Results and discussions.[Figure presented] Fig. 9. The variation of natural frequencies for blades and turbine discs with rotational speed [48]. (Reference specifically refers to the experimental data in Fig. 9). Fig. 10. Detailed analysis on the fracture of turbine disk blades [48,51]. Reference [48] Xiaojun Guo. Design, fabrication and verification of spider web-like SiC_f/SiC monolithic turbine disk [D]. Central South University, 2023. https://doi.org/10.27661/d.cnki.gzhnu.2023.001121. (In Chinese). [49] F. Wang, X.F. Teng, X.A. Hu, Y. Jiang, X.J. Guo, L.B. Li, X.C. Liu, X. Li, H.Y. Lu. Damage and failure analysis of a SiC_f/SiC ceramic matrix composite using digital image correlation and acoustic emission, Ceramics International 48 (2022) 4699–4709. https://doi.org/10.1016/j.ceramint.2021.11.006 [50] X.C. Liu, Y.L. Xu, J. Li et al. Design, fabrication and testing of ceramic-matrix composite turbine blisk. Acta Materiae Compositae Sinica, 2023,40 (03):1696–1706. https://doi.org/10.13801/j.cnki.fhclxb.20220407.001 [51] Guo X, Li J, Zeng Y, Huang X, Li L, Xu Y and Hu X. Design, fabrication, and testing of CVI-SiC/SiC turbine blisk under different load spectrums at elevated temperature, High Temperature Materials and Processes, 2022, 41: 279–288. https://doi.org/10.1515/htmp-2022-0007. [52] Guo X, Xu Y, Li J, et al. Damage monitoring of SiC/SiC turbine blisk under overspeed rotation testing using X-ray computed tomography and natural frequency, Proceedings of the Institution of Mechanical Engineers, Part L: Journal of Materials - Design and Applications, 2024, 238 (6):1–12. DOI:10.1177/14644207231205875. In the above-mentioned article, we pointed out that “During testing, the turbine disk reached a maximum rotational speed exceeding 10⁵ rpm, with a peak transient temperature surpassing 1350 °C.". However, the original article did not specify the source of the 1350 °C value or the detailed calculation. We hereby provide the following information to clarify these points. Detailed calculation for 1350 °C (Fig. 11). We have decided to update Fig. 11 to the following image [51]. Turbo disk original parameters: diameter 84.3mm (Fig. 1(g), actual measurement); rotational speed 105000 rpm (Fig. 11(b), test data [51]); maximum outlet temperature 930 °C = 1203K (Fig. 11(b), test data [51])). The specific heat at constant pressure (c_p) of the gas is taken as 1140 J/(kg·K).[Figure presented] The calculation of turbine inlet temperature (T_in) is based on the principles of turbomachinery, using the following formula. Here, the enthalpy drop (Δh) is related to the tangential speed (U) of the turbine, which is calculated from the rotational speed (N) and the turbine radius (r). The load coefficient (ψ) and the specific heat at constant pressure (c_p) of the gas are used to calculate the temperature change (ΔT). [Table presented] Import temperature calculation formula. 1. Angular velocity (w): w = 2πN/60.2. Turbine radius (r): r = D/2, where D is the turbine diameter.3. Tangential velocity (U): U = w × r.4. Enthalpy drop (△h): △h = ψU², where the load coefficient is taken as ψ = 2.25.5. Temperature change (△T): △T = △h/c_p, where c_p is the specific heat capacity at constant pressure (typical value for gas turbine engines).6. Inlet temperature (T_in): T_in = T_out +△TSpecifically, the numerical calculation process is as follows: w = 2 × 3.1415926 × 105000/60 ≈ 10996 rad/s r = 0.04215 m. U = w × r = 10996 × 0.04215 ≈ 463.48 m/s. U²=(441.3948)²≈214813.71m²/s² △h = ψU² = 2.25 × 214813.71 ≈ 483330.85J/kg. c_p=1140 J/(kg·K). △T = 483330.85/1140 ≈ 423.97K. T_in = T_out+△T = 1203 + 423.97 = 1626.97K. T_in = 1626.97-273 = 1353.97 °C. Based on the above calculation, the ideal import temperature is approximately 1350 °C. Besides, the acknowledgment of the National Natural Science Foundation of China Grant No. 12002288 has been deleted, as it was mistakenly included in the original version. This correction serves to strengthen the scholarly rigor of the original publication without altering its fundamental conclusions. The authors apologize for any confusion and hope this addition will ensure clarity for our readers.