Control Mode Studies for Advanced Variable-Geometry Turbine Engines.
Abstract
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.
Document Details
- Document Type
- Technical Report
- Publication Date
- Nov 01, 1974
- Accession Number
- ADA009169
Entities
People
- Edward C. Beattie
Organizations
- Pratt & Whitney