CONTROL METHOD OF TURBOJET TWO-CIRCUIT ENGINE Russian patent published in 2019 - IPC F02C9/28 F02C9/00 

FIELD: engines and pumps.

SUBSTANCE: invention relates to aircraft engine building, particularly, to adjustment of in-flight turbojet engine with mixing of flows. Method is characterized by that in stationary and transient modes of operation of the engine external operating parameters are measured, from which internal parameters of the engine working process not available for measurement are calculated and the engine operating characteristics are defined as actual thrust values and fan gas-dynamic stability margin. Values of obtained operational characteristics are compared with values of thrust and value of gas-dynamic stability margin, previously determined by results of engine tests. Based on results of operating characteristics comparison, standard values of control factors effect are determined and, depending on them, control signal is generated. In addition, real values of engine operating characteristics are determined with allowance for level of non-uniformity of full pressure behind fan and reference values of thrust and value of gas-dynamic stability margin. Control signal is generated depending on the sum of standard value of action of control factors and correction to it.

EFFECT: invention allows improving reliability and efficiency of engine operation due to optimization of control action formed with account of degree of non-uniformity of total air pressure at the engine inlet.

1 cl, 3 dwg