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航天飞机主发动机高压燃料涡轮泵存在转子动力不稳定问题,其特征是既大而又危险的次同步甩转振动。本文评述了高压燃料涡轮泵原来的设计(从转子动力观点)及其次同步甩转问题的发展。文中也评述了用于说明高压燃料涡轮泵不稳定性和改进其稳定性而建立的模型和分析,并对转子动力模型的要素作了详细的讨论,其中包括:a)密封的水动力;b)转子的内阻尼;c)轴承和壳体支承刚性不对称;d)壳体动力。对以下两种设计方案的稳定性和同步共振特性进行了比较:a)刚性的对称轴承支承设计;b)阻尼的不对称刚性设计。从理论上讲,采用适当的级间密封设计,上述两种设计与原设计相比,在稳定性和同步共振特性方面都有本质上的改进。不对称设计比起刚性支承设计来有更好的稳定性和同步共振特性。
Space shuttle main engine high-pressure fuel turbine pump rotor instability problems exist, which is characterized by both large and dangerous sub-synchronous thrown vibration. This paper reviews the development of the design of high-pressure fuel turbopumps (from the perspective of rotor power) and the subsequent synchronous throttling problems. The models and analyzes used to illustrate the instability and stability of high-pressure fuel turbopumps are also reviewed and the elements of the rotor dynamics model are discussed in detail. These include: a) Sealed hydrodynamic forces; b ) Internal damping of the rotor; c) Rigidity and asymmetry of bearing and housing support; d) Housing power. The stability and the synchronous resonance characteristics of the following two designs are compared: a) Rigid symmetrical bearing support design; b) Asymmetric rigid design of damping. Theoretically, with proper inter-stage seal design, both designs provide substantial improvements in both stability and synchronous resonance characteristics compared to the original design. Asymmetric design has better stability and synchronous resonance than rigid support design.