| In this paper, the research on control system simulation technology for gas turbine engine was studied in detail. The models of engine integrated control system and fuel system in gas turbine were established by simulation technology, which was analyzed subsequently. And the applications of control system simulation technology for gas turbine were investigated on the models, the details are as followed:A gas turbine's control system test platform used for turbine-fan engine was founded by semi-physical simulation. And then the control system simulation platform of aero-engine was designed, and the mathematical model of small deviation engine was set up, forming closed circle simulated control system, and the opened circle and closed circle simulations were carried out on this platform subsequently, verifying the platform which has comprehensive simulation capability preliminarily, which provided an effective guarantee on the development and verification of engine control system.Simulation model of fuel system of gas turbine was established by AMESim simulation software, and it can reduce design difficulty, shorten development period and improve research efficiency, favoring the design systematism and scientifism, having extensibility, and the founded fuel system scheme was reasonable and had better feasibility. And then the model of fuel and blade angle control system of turbine-fan engine was established, and the fuel feed and emergency control laws were stimulated, and results indicated that the fuel-feed characteristics meet the general requirements of gas turbine and control was reliable, and emergent flow characteristics can cut off the oil rapidly in emergency, ensuring gas turbine safety, hence, the plan of fuel and blade angle control system designed by simulation can satisfy the running up of trestle.On the basis of original self-starter structure, a high altitude compensator was added, founding a mathematical model and testing the improved self-starter. Ground start fuel supply flow was not affected by improved self-starter, which could adjust air-start fuel supply flow effectively in a height range, resolving the problem of air-start enrichment. The results of simulations and test showed that improved self-starter can conpensate the effects of flying height on fuel-feed characteristics and resolve the problem of airstart enrichment. Improving the temperature control system by the CSDY Jet pipe electro-hydraulic servo-valves can substitute the nozzle flapper electro-hydraulic servo-valves dealed with the defects of low control accuracy, without position feedback and the hysteresis and effects of dynamical friction. The test results indicated that the improved temperature control system had advantages in high control precision, low hysteresis, and high stabilization under low pressure, increasing the system performance significantly. The fuel metering device in FADEC system which kept ahead interiorly was designed, exploiting the dissimilar redundancy technology in hardware to enhance the reliability of FADEC system. And the properties of blade angle control and main fuel control of the designed real object of fuel metering device was tested, results suggested that the fuel metering device achieved the target generally, which could applied after consummating. |
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