The High Stability Engine Control (HISTEC) Program: Flight Demonstration Phase

TITLE AND SUBTITLE:
The High Stability Engine Control (HISTEC) Program: Flight Demonstration Phase

AUTHOR(S):
John C. DeLaat, Robert D. Southwick, George W. Gallops, and John S. Orme

REPORT DATE:
July 1998

FUNDING NUMBERS:
WU-523-53-13-00

PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Lewis Research Center
Cleveland, Ohio 44135-3191

PERFORMING ORGANIZATION REPORT NUMBER:
E-11257

SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES):
National Aeronautics and Space Administration
Washington, DC 20546-0001

REPORT TYPE AND DATES COVERED:
Technical Memorandum

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA TM-1998-208482
AIAA-98-3756

SUPPLEMENTARY NOTES:
Prepared for the 34th Joint Propulsion Conference cosponsored by AIAA, ASME, SAE, and ASEE, Cleveland, Ohio,
July 12-15, 1998. John C. DeLaat, NASA Lewis Research Center; Robert D. Southwick and George W. Gallops, United Technologies Corporation, Pratt & Whitney, P.O. Box 109600, West Palm Beach, Florida 33410; John S. Orme, NASA Dryden Flight Research Center, Edwards, California 93523. Responsible person, J.C. DeLaat, organization code 5530, (216) 433-3744.

ABSTRACT:
Future aircraft turbine engines, both commercial and military, must be able to accommodate expected increased levels of steadystate and dynamic engine-face distortion. The current approach of incorporating sufficient design stall margin to tolerate these increased levels of distortion would significantly reduce performance. The objective of the High Stability Engine Control (HISTEC) program is to design, develop, and flightdemonstrate an advanced, integrated engine control system that uses measurementbased estimates of distortion to enhance engine stability. The resulting distortion tolerant control reduces the required design stall margin, with a corresponding increase in performance and decrease in fuel burn. The HISTEC concept has been developed and was successfully flight demonstrated on the F-l 5 ACTIVE aircraft during the summer of 1997. The flight demonstration was planned and carried out in two phases, the first to show distortion estimation, and the second to show distortion accommodation. Post-flight analysis shows that the HISTEC technologies are able to successfully estimate and accommodate distortion, transiently setting the stall margin requirement online and in realtime. This allows the design stall margin requirement to be reduced, which in turn can be traded for significantly increased performance and/or decreased weight. Flight demonstration of the HISTEC technologies has significantly reduced the risk of transitioning the technology to tactical and commercial engines.

SUBJECT TERMS:
Aircraft engines; Engine control; Flow distortion; Stability augmentation

NUMBER OF PAGES:
17

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1998/TM-1998-208482.pdf
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