Development of a CuNiCrAl Bond Coat for Thermal Barrier Coatings in Rocket Combustion Chambers
Development of a CuNiCrAl Bond Coat for Thermal Barrier Coatings in Rocket Combustion Chambers
复制标题
火箭燃烧室热障涂层 CuNiCrAl 粘结涂层的开发
DOI：
10.1007/s11666-015-0325-0
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发表时间：
2015
影响因子：
3.1
通讯作者：
M. Bäker
中科院分区：
文献类型：
--
作者：
T. Fiedler;J. Rösler;M. Bäker
采用热障涂层可以提高火箭发动机燃烧室的使用寿命。通常用于燃气涡轮机或航空发动机的标准涂层系统将在粘结涂层/基底界面处失效，这是由于铜衬里和所施加的NiCrAlY粘结涂层之间的化学差异以及不同的热膨胀。以前设计了一种用于火箭发动机应用的新型粘结涂层合金，其化学成分和热膨胀系数与铜基体更相似。由于之前没有通过热喷涂应用类似材料，因此必须进行涂层测试。采用超音速火焰喷涂技术制备了Ni-30%Cu-6%Al-5%Cr新型粘结层合金。在第一步中，研究不同涂层参数对例如，研究了孔隙率、未熔化颗粒的量和涂层粗糙度，并选择了用于进一步研究的合适参数组。在第二步中，用所选参数涂覆铜基板以测试该工艺的可行性。通过激光循环实验测试了涂层的高温性能和附着力。新涂层表现出良好的附着力，即使在温度超过最高测试温度的NiCrAlY粘结涂层在以前的研究。
The lifetime of rocket combustion chambers can be increased by applying thermal barrier coatings. The standard coating systems usually used in gas turbines or aero engines will fail at the bond coat/substrate interface due to the chemical difference as well as the different thermal expansion between the copper liner and the applied NiCrAlY bond coat. A new bond coat alloy for rocket engine applications was designed previously with a chemical composition and coefficient of thermal expansion more similar to the copper substrate. Since a comparable material has not been applied by thermal spraying before, coating tests have to be carried out. In this work, the new Ni-30%Cu-6%Al-5%Cr bond coat alloy is applied via high velocity oxygen fuel spraying. In a first step, the influence of different coating parameters on, e.g., porosity, amount of unmolten particles, and coating roughness is investigated and a suitable parameter set for further studies is chosen. In a second step, copper substrates are coated with the chosen parameters to test the feasibility of the process. The high-temperature behavior and adhesion is tested with laser cycling experiments. The new coatings showed good adhesion even at temperatures beyond the maximum test temperatures of the NiCrAlY bond coat in previous studies.