NASA Technical Reports Server (NTRS) 19740025659: Digital Integrated Control Of A Mach 2.5 Mixed-compression Supersonic Inlet And An Augmented Mixed-flow Turbofan Engine - Info and Reading Options
By NASA Technical Reports Server (NTRS)
"NASA Technical Reports Server (NTRS) 19740025659: Digital Integrated Control Of A Mach 2.5 Mixed-compression Supersonic Inlet And An Augmented Mixed-flow Turbofan Engine" and the language of the book is English.
“NASA Technical Reports Server (NTRS) 19740025659: Digital Integrated Control Of A Mach 2.5 Mixed-compression Supersonic Inlet And An Augmented Mixed-flow Turbofan Engine” Metadata:
- Title: ➤ NASA Technical Reports Server (NTRS) 19740025659: Digital Integrated Control Of A Mach 2.5 Mixed-compression Supersonic Inlet And An Augmented Mixed-flow Turbofan Engine
- Author: ➤ NASA Technical Reports Server (NTRS)
- Language: English
Edition Identifiers:
- Internet Archive ID: NASA_NTRS_Archive_19740025659
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"NASA Technical Reports Server (NTRS) 19740025659: Digital Integrated Control Of A Mach 2.5 Mixed-compression Supersonic Inlet And An Augmented Mixed-flow Turbofan Engine" Description:
The Internet Archive:
A digitally implemented integrated inlet-engine control system was designed and tested on a mixed-compression, axisymmetric, Mach 2.5, supersonic inlet with 45 percent internal supersonic area contraction and a TF30-P-3 augmented turbofan engine. The control matched engine airflow to available inlet airflow. By monitoring inlet terminal shock position and over-board bypass door command, the control adjusted engine speed so that in steady state, the shock would be at the desired location and the overboard bypass doors would be closed. During engine-induced transients, such as augmentor light-off and cutoff, the inlet operating point was momentarily changed to a more supercritical point to minimize unstarts. The digital control also provided automatic inlet restart. A variable inlet throat bleed control, based on throat Mach number, provided additional inlet stability margin.
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