| 摘要 |
A self-powered and self-contained portable testing apparatus for monitoring critical operating parameters of an aircraft reciprocating engine. The portable testing apparatus is typically used for the running-in of aircraft engines after overhaul, before returning the engines to service. The portable testing apparatus includes a plurality of sensors for sensing and generating analog signals corresponding to temperature at various locations inside and outside the engine. A multiposition selector switch electrically connects to each of the sensors. The switch is designed to select one of the analog temperature signals and to transmit the selected signal to a computer having a display. The computer converts the selected signal into a digital temperature signal and indicates the digital signal in corresponding numerical representation on its display. Also included is a tachometer for measuring and displaying the operating speed of the engine. The tachometer has a memory, and can calculate and store in its memory the average operating speed of the engine and the maximum operating speed achieved during the run-in of the engine. A manifold pressure gauge senses and displays intake manifold pressure and an oil pressure gauge senses and displays engine oil pressure. A run time monitor electrically connects to an oil pressure switch which, in turn, connects to the oil pressure circuit. The oil pressure switch closes when the engine is turned on and develops oil pressure. The monitor is supplied with electrical power upon oil pressure switch closure and commences to monitor engine run time.
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