Digital twin test device and control method for gas turbine radial intake complex distortion

Abstract

The invention discloses a digital twin test device and a control method for radial air intake complex distortion of a gas turbine. The outlet of the radial air inlet chamber of the device is connected to the inlet of the compressor through a connecting pipe, the connecting pipe is fixedly connected coaxially with the outlet pipe, the outlet pipe is connected to the electric valve, and the axial flow compressor is fixedly installed in the outlet pipe through the interface flange. The connecting pipeline is equipped with a lubricating oil mist generating device, and the performance sensors are respectively installed on the radial air intake chamber, the connecting pipeline, the outlet pipeline and the axial flow compressor. The performance sensors are all connected to the data acquisition and storage system, and the intake distortion digital twin control center Connect with other modules. The control method obtains the actual digital twin performance model, and uses the driving mechanism to control the flow field of the radial air intake system of the gas turbine. The invention carries out the high-precision design and optimization of the air intake distortion of the radial air intake chamber of the gas turbine, reduces the control oscillation, and ensures the low-delay control and high reliability and safe operation of the stall surge characteristics.

Description

technical field [0001] The invention relates to a gas turbine intake complex distortion digital twin test device in the field of gas turbine flow field distortion digital twins, in particular to a gas turbine radial intake complex distortion digital twin test device and a control method. Background technique [0002] Compressor surge is one of the main problems that affect the safe operation of gas turbines and aero-engines. Because the compressors of gas turbines and aero-engines are in the working environment of reverse pressure gradient, the flow field on the surface of the blade is prone to separation, which leads to compressor Stall, if the intake flow rate drops further and the intake conditions are uneven, it will cause a certain degree of intake distortion, which will cause the unit to enter a surge state. If the surge state is not exited in time, the duration exceeds 0.5s, and it is easy to cause blade breakage , Rotor bending, bearing damage, resulting in serious a...

AI Technical Summary

Problems solved by technology

[0004] The existing axial flow compressor stall surge design under the condition of radial intake distortion mostly adopts experience-based design and CFD flow field simulation design, the test data of intake distortion characteristics is scarce, and the accuracy of flow field simulation needs to be further improved. The running test data and the flow field simulation data cannot establish a mapping relationship in real time, and cannot accurately evaluate the complex intake distortion characteristics caused by intake filter failure, raindrop intrusion, and bearing lubricating oil and gas leakage, and the axial flow under the influence of complex nonlinear intake distortion Accuracy assessment and stability control of compressor surge characteristics need to be further improved

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