| 摘要 |
FIELD: engines and pumps. ^ SUBSTANCE: invention is intended for protecting aircraft gas turbine engines against compressor surges. Proposed device comprises pickup of air pressure P2 behind compressor, compressor inlet air pressure P1 pickup, pickup of compressor inlet air temperature T1, first divider, first threshold device additionally incorporating multiplier and second divider connected in series with the latter. It comprises also second integrator, second threshold device and logical device OR, its second input being connected with first threshold device output. It incorporates also first integrator with its output connected with input of first threshold device and its input connected with output of first divider. Input of the latter is connected with output of pickup of air pressure P2 behind compressor. Second output of the latter pickup is connected with second input of multiplier. Second input of the latter is connected with compressor inlet air pressure P1 pickup output. Note that output of pickup of compressor inlet air temperature T1 is connected with second input of second divider. Note also that signals K2 describing type of critical conditions are connected to inputs first and second dividers. ^ EFFECT: higher validity and accuracy of surge detection. ^ 1 dwg |
