High Stability Engine Control (HISTEC)

TITLE AND SUBTITLE:
High Stability Engine Control (HISTEC)

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

REPORT DATE:
June 1996

FUNDING NUMBERS:
WU-505-62-50

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

PERFORMING ORGANIZATION REPORT NUMBER:
E-10339

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

REPORT TYPE AND DATES COVERED:
Technical Memorandum

SPONSORING/MONITORING AGENCY REPORT NUMBER:
NASA TM-107272
AIAA-96-2586

SUPPLEMENTARY NOTES:
Prepared for the 32nd Joint Propulsion Conference cosponsored by AIAA, ASME, SAE, and ASEE, Lake Buena Vista, Florida, July 1-3, 1996. 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. Responsible person, John C. DeLaat, organization code 2530, (216) 433-3744.

ABSTRACT:
Future aircraft turbine engines, both commercial and military, must be able to successfully accommodate expected increased levels of steady-state and dynamic engine-face distortion. The current approach of incorporating a sufficient component 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 flight demonstrate an advanced, high-stability, integrated engine control system that uses measurement-based, real-time 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, consisting of a Distortion Estimation System and a Stability Management Control, has been designed and developed. The Distortion Estimation System uses a small number of high-response pressure sensors at the engine face to calculate indicators of the type and extent of distortion in real time. The Stability Management Control, through direct control of the fan and compressor pressure ratio, accommodates the distortion by transiently increasing the amount of stall margin available based on information from the Distortion Estimation System. Simulation studies have shown the HISTEC distortion tolerant control is able to successfully estimate and accommodate time-varying distortion. Currently, hardware and software systems necessary for flight demonstration of the HISTEC concept are being designed and developed. The HISTEC concept will be flight tested in early 1997.

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

NUMBER OF PAGES:
13

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1996/TM-107272.pdf
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