http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-6644015-B2

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filingDate 2001-10-29-04:00^^<http://www.w3.org/2001/XMLSchema#date>
grantDate 2003-11-11-04:00^^<http://www.w3.org/2001/XMLSchema#date>
inventor http://rdf.ncbi.nlm.nih.gov/pubchem/patentinventor/MD5_834a827640addeb60d0a2761f4d26307
publicationDate 2003-11-11-04:00^^<http://www.w3.org/2001/XMLSchema#date>
publicationNumber US-6644015-B2
titleOfInvention Turbojet with precompressor injected oxidizer
abstract A turbojet engine with improved thrust and high-altitude capabilities. Arrangements are provided for injecting liquid oxygen or other oxidizer into the turbojet engine before the compressor section. Cooling the incoming air by the liquid oxygen reduces the air volume, which allows a fixed inlet to be matched to varying flow conditions, allowing a greater mass of air to be ingested by the compressor section and results in a lower compressor outlet temperature. Increased mass flow, combined with more fuel results in higher exhaust gas temperatures and greater thrust. The addition of oxygen to the inlet air flow allows the engine to operate at higher altitudes by preventing flameout due to rarefied air.
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http://rdf.ncbi.nlm.nih.gov/pubchem/patent/US-9810153-B2
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