Analysis of Ablative Performance of C/C Composite Throat Containing Defects Based on X-ray 3D Reconstruction in a Solid Rocket Motor
-
Wei-Hua Hui
,
Fu-Ting Bao
Abstract
In this paper, a new measuring method of ablation rate was proposed based on X-ray three-dimensional (3D) reconstruction. The ablation of 4-direction carbon/carbon composite nozzles was investigated in the combustion environment of a solid rocket motor, and the macroscopic ablation and linear recession rate were studied through the X-ray 3D reconstruction method. The results showed that the maximum relative error of the X-ray 3D reconstruction was 0.0576%, which met the minimum accuracy of the ablation analysis; along the nozzle axial direction, from convergence segment, throat to expansion segment, the ablation gradually weakened; in terms of defect ablation, the middle ablation was weak, while the ablation in both sides was more serious. In a word, the proposed reconstruction method based on X-ray about C/C nozzle ablation can construct a clear model of ablative nozzle which characterizes the details about micro-cracks, deposition, pores and surface to analyze ablation, so that this method can create the ablation curve in any surface clearly.
Funding statement: Funding: This work was financially supported by the National Natural Science Foundation of China (Contract Nos.51005179).
Acknowledgments
We would also like to thank Mr. Chen Bo from School of Materials Science and Engineering in Northwestern Polytechnical University for the assistance of hot-fire testing.
Nomenclature
- Rm
mass ablation rates
- m1,m2
the mass of specimens before and after ablation
- S
ablated surface area
- R1
linear ablation rates
- d1,d2
the diameters of hole before and after ablation
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Articles in the same Issue
- Frontmatter
- Effect of Axial Velocity Density Ratio on the Performance of a Controlled Diffusion Airfoil Compressor Cascade
- Uncertainty Analysis in Fatigue Life Prediction of Gas Turbine Blades Using Bayesian Inference
- A New Turbo-shaft Engine Control Law during Variable Rotor Speed Transient Process
- Numerical Study of a Fuel Centrifugal Pump with Variable Impeller Width for Aero-engines
- Analysis of Ablative Performance of C/C Composite Throat Containing Defects Based on X-ray 3D Reconstruction in a Solid Rocket Motor
- Effects of Circumferential Casing Grooves on the Performance of a Transonic Axial Compressor
Articles in the same Issue
- Frontmatter
- Effect of Axial Velocity Density Ratio on the Performance of a Controlled Diffusion Airfoil Compressor Cascade
- Uncertainty Analysis in Fatigue Life Prediction of Gas Turbine Blades Using Bayesian Inference
- A New Turbo-shaft Engine Control Law during Variable Rotor Speed Transient Process
- Numerical Study of a Fuel Centrifugal Pump with Variable Impeller Width for Aero-engines
- Analysis of Ablative Performance of C/C Composite Throat Containing Defects Based on X-ray 3D Reconstruction in a Solid Rocket Motor
- Effects of Circumferential Casing Grooves on the Performance of a Transonic Axial Compressor
