Propulsion System Flow Stability Program (Dynamic). Part X. Explicit Stall Prediction Model - Theory and Comparison of Computed and Experimental Results.
Abstract
In a jet engine, surge is in general initiated by disturbances generated by such mechanisms as unsteady inlet flow conditions, combustion instabilities, and rotating stall in the compressor. In this study the phenomenon of rotating stall was analyzed with the emphasis on the development of a prediction method, and the results show that in the absence of combustion instabilities and unsteady inlet flow conditions, a successful link between the occurrences of rotating stall and surge can be established. The problem of predicting the occurrence of rotating stall in a multistage compressor is subsequently treated theoretically. The theoretically derived equations are then used to predict the surge conditions in a number of single and multistage compressors for which test data are available. The agreement between the predicted and measured operating conditions at which rotating stall occurs is very good for single rotor cases. For the multistage compressors it was not only found that the correlation between the calculated occurrence of rotating stall and the measured surge condition is good, but also that the locations at which rotating stall is first calculated to occur correspond closely to those found by experiments. The analysis has been expanded to include the effects of inlet flow distortions. However, no comparisons with experimental results have been made to validate the results. Suggestions for future studies have been indicated. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1968
- Accession Number
- AD0851905
Entities
People
- G. E. Smith
- W. Jansen