CONTROL METHOD OF TURBO-COMPRESSOR UNIT Russian patent published in 2019 - IPC F02C9/00 

FIELD: control systems.

SUBSTANCE: invention relates to methods of controlling operation of turbo-compressor units and can be used to control process of occurrence of critical nonstationary self-oscillations of injector compressor, which arise when testing mainly aircraft gas turbine engines (GTE) and gas turbine engines (GTE) for stationary stations. In the known method of controlling a turbo-compressor unit, which includes measurement of air temperature and pressure at the inlet of the compressor, temperature of gases behind the low-pressure turbine, rotation speed of the low pressure rotor and air pressure behind the high pressure compressor, measurement of fuel consumption and installation angles of input and guiding devices of low-pressure compressor and formation of low-pressure rotor according to measured parameters of rotation and formation of control actions during adjustment of low-pressure rotor rotation speed by error value between mathematically programmed and measured parameters values, according to the invention prior to occurrence of critical non-stationary self-oscillations of low-pressure rotor rotation speed, additional static pressure at the compressor inlet, total pressure behind the low pressure compressor and total pressure in at least two points in radial section to the high pressure compressor axis is measured, by statistically significant relative to mathematically programmed values of measured values based on static pressure, temperature, averaged full pressure at inlet of high pressure compressor and total pressure behind low pressure compressor, determining air flow corresponding to working frequency of low pressure rotor, and generation of control actions is performed based on the value of mismatch between mathematically programmed values of air flow rate and air flow, determined from values of measured values in interval of stability of compressor, at that, control action is performed by swirling gate installed on turbo-compressor unit.

EFFECT: use of invention prevents occurrence of critical non-stationary self-oscillations of rotor speed of compressor-injector, allows to provide control of turbo-compressor unit and its operation in narrow working zone at maximum values of efficiency and preset reserves of its gas-dynamic stability of compressor, provides preset uniform pressure and temperature field to work places, reduces fuel consumption and excludes unjustified stops of turbo-compressor unit.

1 cl, 1 dwg, 3 tbl