Thrust Augmentation System for Low-Cost-Expendable Turbojet Engine
Final rept. 26 Jun 1992-31 Mar 1993
M-DOT INC PHOENIX AZ
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During the performance period, a dump-combustor afterburner and watermethanol injection system were designed, fabricated and tested on a Sundstrand TJ-90 expendable-turbojet engine. Maximum thrust measured was 150 lbs. yielding an augmentation ratio of 1.57. Also evaluated were silicone based and alumina based lining materials for the afterburner combustion tube and coated-graphite and alumina based materials for the exit nozzle. Watermethanol injection was tested at four engine stations 8 inches upstream of the compressor face, directly upstream of the compressor deswirl vanes, directly into the combustor dilution region and downstream of the turbine exit. Maximum predicted watermethanol flow rates could not be achieved due to combustor flame out. Performance was measured dry, with watermethanol only, with afterburner only and with afterburner and watermethanol injection.... Afterburner, Thrust Augmentation, Expendable Turbojet, Water-Methanol Injection.
- Jet and Gas Turbine Engines
- Solid Propellant Rocket Engines