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The design tables represent performance requirements from the end-item customer (airframer and/or government). The customer specifies a specific maximum and minimum thrust levels to be achieved at various flight conditions, which is termed the flight envelope. The engine manufacturer (PW in this case) must design an engine concept and cycle that satisfies these requirements. An engine simulation of the powerplant cycle is created that results in predictions of burn flow requirements, exhaust nozzle area, variable vane position, rotor speeds, gas path pressures and temperatures, etc. A partial listing ofthis engine simulation deck output is shown in Figure 5-6. The number of flight conditions and throttle settings has been greatly reduced to fit within Solver's capabilities. This listing represents only a single temperature "day" condition known as "standard day", which is defined as 59 degrees F at sea level. "Cold day", "tropical day", and "hot day" conditions have also been defined based on worldwide environmental extremes. Ambient temperatures and pressures for each type of day at various altitude conditions have also been defined. In totality, the entire fuel system must be evaluated against literally thousands of individual conditions observing both internally and externally imposed constraints. This is far beyond the capability of Excel Solver; therefore, an "industrial strength" optimization program such as AMPL would be required. A significant benefit of optimization modeling is the ability to have the model identify the design points (i.e. the conditions that determine the sizing of variables), then very quickly performing a sensitivity analysis at those conditions to determine the benefit of incrementally reducing requirements. For example, if the pump sizing condition is determined to be a low altitude, high Mach number condition, but at an idle (i.e. low thrust request) throttle condition, this would represent a condition where the thrust produced by the engine is much less than the drag induced by the aircraft, therefore the Mach number would decrease very quickly causing the 112PDF Image | Improving Gas Turbine Engine Control System
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