螺旋槽端面密封是液体火箭发动机涡轮泵用轴端密封的首选；考虑粘温、流体泄漏及热传导,建立了适合于内外双槽中间密封坝结构端面密封的理论分析模型,发展了螺旋槽密封膜厚控制方程和合适的边界条件；以此研究了密封特性参数(端面开启力、液膜刚度、摩擦力矩等)受不同运行参数(工作转速、压差等)和结构参数(槽深等)的影响规律.以水为密封介质,试验研究了处在不同压差和转速条件两类不同槽深的双螺旋槽端面密封的性能.理论和试验研究表明密封端面温升和摩擦力矩随转速和密封压差的增加而增加,槽深对温升和端面摩擦力矩影响不大；试验研究结果很好地验证了理论模型的正确性,为液体火箭发动机涡轮泵轴端密封的设计提供了理论和试验基础.%The spiral grooved seal is a prime candidate for application to liquid-oxygen (LOX) turbopumps. The introduction of the full paper reviews a number of papers in the open literature and then proposes the study mentioned in the title. The influences of operating parameters (rotational speed, supply pressure) and configuration parameters ( depth of spiral groove) on the basic static characteristics (opening force, leakage, friction torque, temperature rise and power loss) are discussed. Sections 1 and 2 explain how to obtain the above-mentioned influences. Section 1 briefs what is readily found in the open literature but eq. (2 ) and the particular boundary conditions to be used are contributed by us. Section 2 briefs our experimental setup. In section 3, comparisons are presented between the measurements and predictions for an average 100 mm diameter, high speed, and narrow spiral grooved face seal using water as a test fluid; the theoretical and experimental results, given in Figs. 4 through 9, and their discussion show preliminarily that both the temperature rise of face seal and the friction torque increase with increasing speed and supply pressure but change slightly with increasing depth of spiral groove; these findings appear to provide the theoretical and experimental basis for the design of reusable face seals applied to the LOX turbopumps.
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