| Abstract | This note describes the extension of an existing computer programme which enables the design-point performance parameters for non-regenerative turbojet and turbofan engines to be calculated quickly and accurately. The programme has been rewritten so that the design point performance of regenerative engines also can be assessed. The source deck has been prepared in Fortran IV for an IBM 360 computer. A series of regenerative turbofan cycles has then been examined using the programme and the design-point performance parameters evaluated. It was found that for a compressor pressure ratio of 10, heat exchanger effectiveness of 0.8 and Bypass Ratio of 5, the optimum S.F.C. was 0.308 1b/hr.-1b., compared with 0.415 1b/hr. - 1b. for a non-regenerative cycle. This and similar comparisons have been made assuming the same basic gas generators for regenerative and nonregenerative cycles. The effect on performance of changing heat exchanger parameters, including leakage from hot to cold streams, was examined as’ was also the effect of tailpipe mixing. |
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