FIELD: physics.
SUBSTANCE: invention can be applied in processes and devices of thrust measurement for turbo-jet engines (TJE) and double-circuit turbo-jet engines (DCTJE). The process involves measurement of flight parameters and drag force by two linear probes with different aerodynamic drag rates, placed in nozzle gas flow. Then ratio parameter of thrust measured by the two probes is defined, and dynamic head of gas flow is calculated with the use of previously defined dependencies of the parameter on M coefficient and nozzle thrust. Then mass fuel consumption per second, rev number of engine compressor rotor and gas temperature at the nozzle section is measured, followed by definition of gas flow parameters at the jet nozzle section and, finally, input pulse and engine thrust.
EFFECT: possibility of defining engine thrust in all flight modes.
6 dwg
