Numerical Calculations Of A Turbine With Partial Admission Nozzles In A Turbopump Of Liquid Rocket Engine Using The Frozen Rotor Method
- Paper number
IAC-07-C4.3.02
- Author
Dr. Eun Seok Lee, Korea Aerospace Research Institute, Korea
- Year
2007
- Abstract
Turbbopump research of liquid rocket engine development has been carried out for several years at Korea Aerospace Research Institute. In this paper, a numerical flow analysis has been performed on the partial admission turbine of the turbopump. The flow-field in a partial admission turbine is essentially three dimensional and unsteady because of a tip clearance and a finite number of nozzles. Therefore the mixing plane method is generally not appropriate. To avoid heavy computational load due to an unsteady three dimensional calculation, a frozen rotor method was implemented in steady calculation. The results were compared with a mixing plane method. The frozen rotor method can detect the variation of flow-field dependent upon the blade’s circumferential position relative to the nozzle. It gives an idea of wake loss mechanism starting from the lip of a nozzle. This wake loss was assumed to be one of the most difficult issues in turbine designers. Thus, the frozen rotor approach has proven to be an efficient and robust tool in design of a partial admission turbine. In this paper, it gives an idea of partial admission turbine at design level.
- Abstract document