This thesis presents a computer program written
(in Fortran IV) to simulate the steady state off design point
performance of virtually any gas turbine configuration (dealing
primarily with aerospace applications). The performance is
calculated using component characteristic maps for compressors,
combustion chambers, turbines (both compressor turbines and
free turbines) and a map giving the velocity coefficient for
exhaust nozzles. The off design point performance is determined
by using a modified Newton-Raphson method. Cont/d.
| Identifer | oai:union.ndltd.org:CRANFIELD1/oai:dspace.lib.cranfield.ac.uk:1826/7401 |
| Date | 09 1900 |
| Creators | MacMillan, W. L. |
| Contributors | Palmer, J. R. |
| Publisher | Cranfield University |
| Source Sets | CRANFIELD1 |
| Language | English |
| Detected Language | English |
| Type | Thesis or dissertation, Doctoral, PhD |
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