The Design of a New Rotary Flow Control Valve with a Pressure Compensator for a Turbojet Engine

This paper presents a new rotary flow control valve with cam-nozzle structure that consists of a pressure compensator valve with an electronic actuator. This configuration installed in a turbojet engine fuel control system. This valve actuation is accomplished directly with a rotary servomotor. The purpose of this new design is to modify and optimize of a single speed turbojet engine performance for new missions. The rotary actuator selection, rotary metering valve design with high travel, direct drive rotary metering valve design and the special metering flow area are the innovations in the presented design. Because of rotary direct drive metering section, versus usual methods, number of parts(15-20%) and cost and hence weight of system are decreased. The fuel metering area is the lateral area of a cylinder with variable height. The mathematical model and simulation of the system is performed to obtain optimized design parameters. After manufacturing the prototypes, they are tested on a special stand for evaluation of system performance and adjusting the fuel system. The test results compared with the simulation results. Maximum (5%) deviation between model and test results shows that the model is accurate for prediction of system function.