Accession Number : ADA263727


Title :   Thrust Augmentation System for Low-Cost-Expendable Turbojet Engine


Descriptive Note : Final rept. 26 Jun 1992-31 Mar 1993


Corporate Author : M-DOT INC PHOENIX AZ


Personal Author(s) : Seegers, Bryan J ; Shreiner, David G


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a263727.pdf


Report Date : 31 Mar 1993


Pagination or Media Count : 66


Abstract : During the performance period, a dump-combustor afterburner and water/methanol 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. Water/methanol 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 water/methanol flow rates could not be achieved due to combustor flame out. Performance was measured dry, with water/methanol only, with afterburner only and with afterburner and water/methanol injection.... Afterburner, Thrust Augmentation, Expendable Turbojet, Water-Methanol Injection.


Descriptors :   *INTEGRATED SYSTEMS , *TURBOJET ENGINES , *THRUST AUGMENTATION , TEST AND EVALUATION , INJECTION , WATER , GRAPHITE , COMBUSTION , COMBUSTORS , FLOW RATE , METHANOLS , NOZZLES , TURBINES , FLAMES , COMPRESSORS , BOOSTER ROCKET ENGINES , SOLID PROPELLANT ROCKET ENGINES , EXHAUST SYSTEMS , TURBOJET INLETS , AFTERBURNERS


Subject Categories : Jet and Gas Turbine Engines
      Solid Propellant Rocket Engines


Distribution Statement : APPROVED FOR PUBLIC RELEASE