Research of rotor attacking angle for liquid rocket reaction turbine

According to the characteristics of the astronautical reaction turbine used in a high performance liquid rocket engine with staged closed circulation combustion, the designed rotor cascade and the blade to blade flow in the cascade were investigated. For the existed rotor cascade, the effects of positive or negative attacking angle for the reaction turbine on the energy loss and the blade to blade flow also were studied by means of two-dimensional cascade experiments in the subsonic tunnel. The results indicate that: in order to obtain the continuous contraction of the geometrical cascade and less energy loss the positive attacking angle showld be adopted for the rotor design. For the existed contracting rotor cascade, the negative attacking angle condition will result in the lessen the energy loss.