Accession Number:

ADA009169

Title:

Control Mode Studies for Advanced Variable-Geometry Turbine Engines.

Descriptive Note:

Final rept. 1 Jul 73-30 Sep 74,

Corporate Author:

PRATT AND WHITNEY AIRCRAFT EAST HARTFORD CONN

Personal Author(s):

Report Date:

1974-11-01

Pagination or Media Count:

89.0

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.

Subject Categories:

  • Jet and Gas Turbine Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE