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:bl.uk/oai:ethos.bl.uk:357988 |
| Date | January 1974 |
| Creators | MacMillan, W. L. |
| Contributors | Palmer, J. R. |
| Publisher | Cranfield University |
| Source Sets | Ethos UK |
| Detected Language | English |
| Type | Electronic Thesis or Dissertation |
| Source | http://dspace.lib.cranfield.ac.uk/handle/1826/7401 |
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