Aero-engine Test Key Parameters Of Testing And Condition Monitoring Systems Are Developed

The paper is systematic to have elaborated realization and design of the crucial parameters testing and states monitoring system in aerial engine test. The system included 2 rotational speed measurement channels, oil flow measurement channels, 8 pressure measurement channels, which are based on PCI bus in a industrial computer. The system software realized functions of which parameters are measured and states are monitored. It has been adequately considered expansibility of measurement channels and has been implemented automatic expanded.Measured for rotational speed and oil flow is based in principle of zero-dead-time period measurement, which implement consecutive period measurement and give 2 dimensions between rotational speed (or oil flow) and timetable. It can automatically match rotational speed generator, electromagnetic rotational speed sensor and electromagnetic turbine flowmeter. Moreover it can adapted measured signal that is 1V~300V voltage and 1Hz~2500Hz frequency. The design can adapt to application range correspondingly and measured parameter with period relatively. One board has been 2 channels. The paper has described designing and implementing method of rotational speed / oil flow measurement board in detail.Measured for pressure is based in zero dead time parallel acquisition technology. One board has been 4 channels. One channel has been 100KSPS sampling rate and ±20mV～±10V input signal range(7 scopes selectable). The paper has described principle of the pressure acquisition board.It has adequately been considered that user demanded in functions of crucial parameters testing and states monitoring in aerial engine test in the software design in the paper.In the paper has been described that crucial technologies have PCI interface, automatic gain control, CPLD implementing of digital logic and so on.