Investigation on the Strength and Vibration Safety of a Liquid Rocket Turbopump
- Paper number
IAC-05-C2.1.A.01
- Author
Dr. Seong Min Jeon, Korea Aerospace Research Institute, Korea
- Coauthor
Dr. Jinhan Kim, Korea Aerospace Research Institute, Korea
- Year
2005
- Abstract
Structural and dynamic analyses of an oxidizer pump and a turbine are performed to investigate the static and dynamic characteristics and to determine the safety margin with respect to the design requirements. External forces acting on the turbopump considered for the analyses include centrifugal load, hydrodynamic pressure load and thermal load. A three-dimensional finite element method is used for linear and nonlinear structural analyses of the oxidizer pump and for cyclic symmetry structural analyses of the turbine. From the results of the numerical analyses, the effects of various external loads on structural stresses and dynamic characteristics are carefully examined. A static analysis is performed to evaluate static characteristics of the inducer, impeller and turbine. The results show that the equivalent stresses of the inducer and the impeller are not a linear sum of each stress due to centrifugal and pressure loads because of the geometric curvature of their blades. As for the turbine, the total stress due to centrifugal and thermal loads simultaneously exerted is smaller than the thermal stress alone due to the circumferential stresses acting in the opposite direction. On the other hand, the radial displacement of the turbine is approximately a linear sum of each displacement due to each load as radial stresses act in the same direction. Dynamic characteristics at every inter-blade phase shift are slightly affected by centrifugal stiffening because of structural rigidity. A comparison between the rotating natural frequencies and external force harmonics shows a sufficient margin from resonance.
- Abstract document
- Manuscript document
IAC-05-C2.1.A.01.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.