Control Mode Studies for Advanced Variable-Geometry Turbine Engines.
Final rept. 1 Jul 73-30 Sep 74,
PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN
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This program addressed the definition and refinement of control modes for a variable cycle, non-mixed exhaust, turbofan engine incorporation fan and compressor vanes, variable high and low-pressure turbine nozzle areas, Under a previous Air Force contract, a control mode for a nonaugmented version of this engine was developed utilizing a dynamic computer simulation of the engine, and operation was demonstrated over a range of flight conditions. Under the program reported herein, this control mode was updated and refined to enable satisfactory transient response over a typical military flight envelope to meet MIL-E-5007C requirements. An implementable control scheduling approach was also developed to provide compliance with steady-state engine rating requirements.
- Jet and Gas Turbine Engines