| 摘要 |
FIELD: aircraft instrumentation engineering; on-board monitoring of gas-turbine engines. ^ SUBSTANCE: proposed system employs information transmitted from aircraft parameter sensors to inputs of multiplexing unit and to on-board computer from output of this unit. Information received from sensors of very important parameters of engine is transmitted directly to command unit input. Present measured magnitudes are compared with limiting and dangerous magnitudes in on-board computer and in command unit on basis of algorithms introduced in their storage and received from sensors of very important parameters: turbine outlet temperature, consumption and pressure of fuel, pressure of gas after fan door and thrust. In case of deviation of these magnitudes from specified limits, limiting and dangerous commands are formed and are transmitted to on-board computer and to emergency information system for recording and warning the crew. Actual operating time and residual service life of aircraft engine with commands thus obtained taken into account are determined in on-board computer and are transmitted to on-board information system for indication and recording. ^ EFFECT: possibility of monitoring the aircraft engine in standard, off-standard and augmented power rating conditions. ^ 2 dwg |
