Ablation Behavior of High-temperature Laminated Ta/Ta0.5Hf0.5C Cermets under High-frequency Plasma Wind Tunnel Test

doi:10.15541/jim20240506

Abstract

Abstract:

Laminated Ta/Ta_0.5Hf_0.5C cermets, characterized by high strength, high toughness, and high-temperature resistance, are excellent candidate materials for structural applications in aerospace field. To further investigate ablation performance of Ta/Ta_0.5Hf_0.5C cermets under high-temperature environment, a high-frequency plasma wind tunnel was utilized to evaluate their ablation resistance at nearly 3000 ℃. Their phase composition and microstructure before and after ablation were characterized and analyzed. Results revealed that the laminated Ta/Ta_0.5Hf_0.5C cermets demonstrated remarkable ablation resistance, with a mass ablation rate of 0.061 g/s and a linear ablation rate of 0.019 mm/s. During the ablation process, distinctive ridge-groove surface morphologies and internal cracks were produced along the layered structure direction. These features were attributed to inconsistent ablation rates and thermal expansion coefficients of Ta metal layer and Ta_0.5Hf_0.5C ceramic layer. Specifically, the ridge region primarily consisted of Hf₆Ta₂O₁₇ formed by oxidation of Ta_0.5Hf_0.5C ceramic layer. This compound could stably exist at high temperatures to protect the interior of ceramic layer from further oxidation. In contrast, the groove region primarily comprised Ta₂O₅, which was formed by oxidation of Ta metal layer. Yet Ta₂O₅ had a tendency to melt and vaporize at elevated temperatures, potentially leading to ejection or loss toward the ablation edge. The cracks formed within the layered structure during cooling process after ablation were mainly generated by thermal stress acting on the Ta_0.5Hf_0.5C ceramic layer due to differences in thermal expansion coefficients between the layers. Additionally, the Ta₂C interfaces between metal and ceramic layers played a crucial role in branching, deflecting, and initiating micro-cracks, which endowed the material with good thermal shock resistance.

Key words: Ta/Ta_0.5Hf_0.5C cermet, wind tunnel, ablation mechanism

CLC Number:

TB383

YU Yiping, XIAO Peng, ZHAO Changhao, XU Mengdi, YAO Lidong, LI Wei, WANG Song. Ablation Behavior of High-temperature Laminated Ta/Ta_0.5Hf_0.5C Cermets under High-frequency Plasma Wind Tunnel Test[J]. Journal of Inorganic Materials, 2025, 40(7): 790-798.

Figures/Tables 12

Fig. 1 Geometry of laminated Ta/Ta0.5Hf0.5C cermets sample for ablation

Fig. 2 Ablation schematic representation of laminated Ta/Ta0.5Hf0.5C cermets in plasma wind tunnel

Fig. 3 (a, b) Optical images of laminated Ta/Ta0.5Hf0.5C cermets before (a) and after (b) plasma wind tunnel ablation; (c) Ablation temperature curve

Table 1 Ablation resistance properties of typical high-temperature materials ablated under temperature of ~3000 ℃[19-23]

Material	Ablation method	Ablation temperature/℃	Ablation time/s	Linear ablation rate/(mm•s^-1)	Mass ablation rate/(g•s^-1)	Reference
C/C composites	Motor ground ignition test	~3000	60	0.142	-	[19]
C/C composites	Arc wind tunnel abltion	~3000	200	0.030	-	[20]
C/C-SiC composites	Oxyacetylene ablation	~3000	60	0.096	0.024	[21]
C/C-SiC-Ti₃SiC₂ composites	Oxyacetylene ablation	~3000	60	0.060	0.012	[21]
C/C-Zr_0.83Ti_0.17C composites	Oxyacetylene ablation	~3000	60	0.016	0.004	[22]
Zr_0.8Ti_0.2C_0.74B_0.26 coated C/C composites	Oxyacetylene ablation	~3000	60	0.001	0.008	[23]
Ta/Ta_0.5Hf_0.5C cermets	Plasma wind tunnel ablation	~3000	30	0.019	0.061	This work

Fig. 4 XRD patterns of laminated Ta/Ta0.5Hf0.5C cermets before (a) and after (b) plasma wind tunnel ablation

Fig. 5 Microstructure of laminated Ta/Ta0.5Hf0.5C cermets before plasma wind tunnel ablation (b) Local magnification of box area in (a)

Fig. 6 Microstructure and EDS analysis of central region of laminated Ta/Ta0.5Hf0.5C cermets after plasma wind tunnel ablation (a) Whole sample; (b, c) Ridge area; (d, e) Groove area. Insets in (c, e) are corresponding EDS analyses of the red dots

Fig. 7 Microstructure of edge region of laminated Ta/Ta0.5Hf0.5C cermets after plasma wind tunnel ablation (a, b) Ridge area and (c, d) groove area parallel to the layered structure; (e, f) Ridge area and (g, h) groove area perpendicular to the layered structure. Insets in (b, c) are corresponding EDS analyses of the red dots

Fig. 8 Cross-sectional microstructure of laminated Ta/Ta0.5Hf0.5C cermets after plasma wind tunnel ablation (a) Overall structure; (b-d) Ablation center; (e-g) Ablation edge

Table 2 Elements contents (in atom) of different areas in the cross section of laminated Ta/Ta0.5Hf0.5C cermets after ablation

Area	Ta/%	Hf/%	O/%	C/%
Ⅰ	9.89	11.01	40.06	39.05
Ⅱ	20.62	1.64	25.10	52.64
Ⅲ	4.31	3.69	31.07	60.92
Ⅳ	18.28	0	34.92	46.79
Ⅴ	14.83	3.87	14.23	67.07
Ⅵ	23.93	0.08	6.11	69.88

Fig. 9 Microstructure of crack generated inside laminated Ta/Ta0.5Hf0.5C cermets after plasma wind tunnel ablation (a) Macroscopic structure of the crack; (b) Crack branching and deflection at the interface; (c) Microcracks at the interface

Fig. 10 Schematic diagram of plasma wind tunnel ablation process of laminated Ta/Ta0.5Hf0.5C cermets

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