| 摘要 |
FIELD: engines and pumps.SUBSTANCE: invention relates to methods of controlling operating modes of engine upon its operation at aircraft at instrument flight speed depending on maximum axial load acting on rotor thrust bearing of aircraft gas turbine engine. Axial load limit Ris specified for each engine operating mode, which corresponds to specific value of flight bending and altitude at nand based onrelationshipis determined, then by universal relationship ofaxial load Ris determined and compared with R, using successive approximations determine limit Mach number M, where R= R, determine relevant limit instrument speed based onrelationship, during flight aircraft gas turbine engine operating modes are adjusted so that the indicated airspeed V<V.EFFECT: invention allows to reduce time of engine development at the stage of engine flight tests and increase efficiency of adjustment stage, whereupon increase service life of engine and its reliability through limiting value of axial load acting on rotor of aircraft gas turbine engine.1 cl, 2 dwg |
