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A turbine engine diagnostic system utilizing a general purpose computer was developed and tested on a TF30-P-408 engine at sea level conditions. Forty-eight parameters, including vibration, oil and performance parameters, were monitored every 80 milliseconds. Forty-seven diagnostic messages were programmed and were displayed on a cathode ray tube. The system has not been fully debugged. Thirty-four diagnostic messages were demonstrated. (Author).
Turbine engine diagnostic development was continued in a number of hardware and software areas. New development and/or evaluation work was done on a turbine inlet temperature sensor, Ferrograph iron-in-oil monitor, and vibrating cylinder pressure transducer. Software work included investigation of data smoothing techniques, study of multiple fault gas path analysis applied to TF30-P-408 engine data, development of an advanced variable geometry engine cycle deck, and sensitivity study of the TEDD program. (Author).
The Turbine Engine Diagnostic Checkout System Program represents the second phase of continuing Air Force Research and Development program aimed at the development of a system allowing automatic, diagnostic status determination of aircraft propulsion engines. The results of the first phase of the program sequence have been documented in Technical Report AFAPL-TR-68-136: 'Turbine Engine Lubrication and Moving Parts Checkout, ' published in January 1969. Diagnostic techniques addressing the dynamic, parametric and functional manifestations of the turbine engine were evaluated during the first phase of effort. An optimum spectrum of these techniques was integrated in the form of an exploratory model system in the second phase of effort. The results of this program demonstrated that it is feasible to automatically determine the mechanical condition and functional status of turbine engines using the present state-of-the-art data acquisition, interpretation, and processing hardware. The major portion of work in this program consisted of diagnostic experimentation and data analysis of abnormal component signatures which were established to represent varying levels of severity for the in-engine components important to operation. Since determination of the condition of complex mechanical systems by other than direct inspection has heretofore been relatively unexplored, a primary goal of this work was to assure that the system had sufficient compatibility and flexibility to utilize a maximum number of existing techniques as well as diagnostic possibilities likely to be developed. (Author).
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).