To develop and find the effect of combination of four cycle design variables that minimizes the specific fuel consumption (sfc) of a turbofan engine.
After choosing the four variables, namely bypass ratio (B), fan pressure ratio, overall pressure ratio, and turbine inlet temperature (T04), first the sfc was minimized without a minimum thrust constraint. Then, a minimum specific thrust constraint was introduced.
The unconstrained‐specific thrust is a two‐dimensional optimization problem, whereas the specific thrust constrained problem was found to be a three‐dimensional one.
The variables B and ï are limiting factors to further improvement, as set by their maximum practical values, whereas the other two variables are to be optimized.
A very useful work, in which numerical optimization program was developed, for a turbofan cycle and could be extended to other cycles.
This paper offers a great help to those intending to optimize certain cycles with a number of variables.
