Gas turbine radial air inlet complex distortion digital twinning test device and control method

Abstract

The invention discloses a gas turbine radial air inlet complex distortion digital twinning test device and a control method. An outlet of a radial air inlet chamber of the device is connected with an inlet of an air compressor through a connecting pipeline, the connecting pipeline is coaxially and fixedly connected with an outlet pipeline, the outlet pipeline is connected with an electric valve, an axial flow air compressor is fixedly installed in the outlet pipeline through a connector flange, and a lubricating oil mist generating device is installed on the connecting pipeline. The performance sensors are installed on the radial air inlet chamber, the connecting pipeline, the outlet pipeline and the axial flow air compressor respectively, the performance sensors are all connected with the data collecting and storing system, and the air inlet distortion digital twinborn control middle table is connected with the other modules. According to the control method, an actual digital twinning performance model is obtained, and a driving mechanism is used for controlling a flow field of a radial air inlet system of the gas turbine. According to the method, high-precision design and optimization of air inlet distortion of the radial air inlet chamber of the gas turbine are carried out, control oscillation is reduced, and low-delay control and high-reliability safe operation of stall surge characteristics are guaranteed.

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

Images