A numerical study was carried out for a cascade thrust reverser of a turbofan engine with bypass ratio of 8

in order to investigate the influences of the thrust reverser deployment with different movement controls on the back pressure of the fan and the force of the blocker door. Results showed that the fluctuation of the fan back pressure increased and the aerodynamic force acted on the blocker door reduced with the delay of the initial rotating time of the blocker door when the total opening time for the thrust reverser was constant. Therefore

for the blocker door

there was a compromise design time for blocker rotation which started at the moment of the transcowl moved 1/3 of the length overall. The total moving time of the thrust reverser from the close point to the deployment had little effect on the pressure at the fan exit and the aerodynamic force on the blocker door. When the deployment of the thrust reverser took place at the emergency cancel of taking off

the fluctuation of the back pressure for the fan was about 20%. It exceeded the allowable values of pressure fluctuation. The maximum force on the blocker door at the emergency cancel of taking off reached 4500N

equaled to four times the normal state.