| 摘要 |
Continuous engine monitoring with regard to gas turbine engines is difficult particularly when the engine is utilized for propulsion of an aircraft. Nevertheless, by use of transfer passages 4 to an arrangement located within the tail cone 9 of an engine, it is possible through a transparent test cell 6 and appropriate heating to generate sufficient infra red radiation as well as incandescent visible light for detectors 11, 16 to determine various constituent parts of the gas flow. Thus a photo detector 11 can provide through electrical signals, the proportion of soot/smoke particles in the gas flow through their incandescence, whilst use of filters 17 for particular spectral lines in an infra red radiation spectrum will allow detectors 16 to provide an indication through an electrical signal the proportion and presence of other constituents such as NO, CO and unburnt hydrocarbons in an exhaust gas flow.
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