DIGITAL ELECTRONIC CONTROL SYSTEM WITH BUILT-IN COMPLETE THERMO- AND GAS-DYNAMIC MATHEMATICAL MODEL OF GAS TURBINE ENGINE, AND AIRCRAFT GAS TURBINE ENGINE Russian patent published in 2015 - IPC G05B17/00 

FIELD: engines and pumps.

SUBSTANCE: group of inventions relates to aircraft gas turbine engines (GTE). Improvement of quality and reliable control of GTE under actual operating conditions due to "virtual engine" software built in GTE control system and providing online calculation of non-measured GTE parameters in steady-state and transient modes of its operation in full range of their change by means of GTE thermo- and gas-dynamic mathematical model contained in it, engine control as per these design parameters, self-identification of the engine model, as well as replacement of engine parameters used for control of measured values at failure of the corresponding sensors with their design values determined by means of the thermo- and gas-dynamic mathematical model. For that purpose, a digital electronic control system of an aircraft gas turbine engine is proposed, which includes a built-in complete thermo- and gas-dynamic mathematical model of a gas turbine engine, consisting of "virtual engine" software for on-line calculation of values of internal parameters of the operating process and performance characteristics of the engine, which are not accessible for measurement, such as: engine thrust R, temperature T*_G of gas in a combustion chamber, margins of gas-dynamic stability of compressor ΔKs, excess air coefficient in the main combustion chamber α_OCC and afterburner α_A, temperature Ti, pressure Pi and air (gas) flow rate Gi in the main cross sections (i - cross section index) of the engine.

EFFECT: improvement of quality and reliable control of GTE under real operating conditions.

6 cl, 9 dwg