Ablation Properties of ZrO₂-MgO and Mo Nozzle Produced by Plasma Spray Forming

Abstract:

ZrO₂-MgO and Mo powder coating on a substrate material prepared by an high temperature plasma spraying forming (PSF) for lease-shaped engine nozzles, and its total thickness is about 300 μ m. The surface coating changes of microstructure were investigated by a small solid rocket motor static ablation and the results were discussed for preliminary ions after ablation. The results show that the plasma spraying throat coat is a layer structure and the pore consist in micro-gap between layer and layer.That throat coating erosion is so severe were found after the ablation test , which is because of the metal oxide particles caused by mechanical denudation and high temperature thermal chemical ablation.Whereas the coating interface have no significant cracks after erosion, so that the composite coating of ZrO₂-MgO and Mo wear good erosion performance.

• Periodical: Advanced Materials Research (Volume 852)
• Pages: 23-26
• DOI: https://doi.org/10.4028/www.scientific.net/AMR.852.23
• Online since: January 2014
• Authors: Jia Hui Qu, Yan Jun Wei
• Keywords: Ablation, Mo, Nozzle, Plasma Spray, ZrO₂-MgO Coating

References

[1] Sun Jufang. Application of Finite-element Method to Calculating Stress Field In Nozzle Insert of Solid Rocket Motor．Joumal of Aero Spaee Power．1989，4 (03): 245-249.

[2] Song Jiaming, Zhou Yu. Solid Rocket Motor Throat Lining Material．Journal of Solid Rocket Technology. 1984，(3)：7-18.

[3] Zhang Dexiong, Li Hongjun. A Review of the Recent Advancements of So1id Rocket Propulsion Technology. Journal of Solid Rocket Technology. 1997，20(2)：1-6.

[4] Katzman HA. Polyarylene-matrix Composites for Solid Rocket Motor Components.J. Advances Material. 1995，(4)：21-27.

[5] Fang Dingyou, Xia Zhixun, Jiang Chunlin. Engineering Calculation of C/C Throat Insert Ablation．Journal of Solid Rocket Technology. 2000，23(02)：24-27.

[6] Su Junming, Chen Linquan, Wang Shuxian. The Microscopic Structure and Thermal Shock Resistance of Copper-impregnated Graphite Throat Insert Material . Journal of Solid Rocket Technology. 2003，26(03)：58-61.

[7] Chen Linquan, Wang Shuxian, Zhang Shengyong. Study on the Erosion Mechanism of Copper-infiltrated Graphite Throat Insert. Journal of Solid Rocket Technology. 2004，27(01): 57-59.

[8] Pan Yusong, Zhang Litong. Ablation Properties Analysis of 2D C/SiC Composites. Ordnance Material Science and Engineeging．2006，29 (01)：17-20.

[9] Pan Yusong, Zhang Litong. Analysis of the Ablation Properties of C/SiC Diversion Tube Used in Solid Rocket Motor. Journal of Astronautics．2006，26 (06)：789-792.

[10] Pan Yusong, Zhang Litong. Ablation and Thermal Shock Resistance Properties of C／SiC jet vane．The Chinese Journal of Nonferrous Metal. 2006，16 (06): 976-980.

[11] Zhang Qingjun, Mo Wenling, Wang Zhanle. Analysis on the Microstructure of Zirconia Coating Deposited by Plasma Spraying Technique．Bulletin of the Chinese Ceramic Society. 2006, (6): 64-67.

[12] Miller R A, Garlick R G, Smialek J L. Phase Distribution in Plasma Sprayed Zirconia Yttria. Ceram Bull，1983， 62( 2) : 1355-1358.

[13] Miller R A. Current Status of Thermal Barrier Coating an Overview. Surface and Coating Technology, 1987，（30）：1- 11.

[14] Zhang Xiaolin, Hao Jianmin. Study on Process and Properties of Plasma Sprayed Molybdenum Coating. Hot Working Technology．2009，38（04）：59-62.