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Hybrid combustor assembly and method of operation

  • US 10,641,169 B2
  • Filed: 06/09/2017
  • Issued: 05/05/2020
  • Est. Priority Date: 06/09/2017
  • Status: Active Grant
First Claim
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1. A combustion system for a propulsion system, the combustion system comprising:

  • a rotating detonation combustion (RDC) system comprising a RDC chamber and a RDC inlet, the RDC system further comprising a nozzle configured to receive a flow of oxidizer, the nozzle configured to selectively receive a flow of fuel and provide the flow of fuel to the flow of oxidizer through the nozzle;

    a bulkhead wall coupling together an inner liner and an outer liner, wherein the inner liner, the outer liner, and the bulkhead wall together define a combustion chamber, and further wherein the RDC system and bulkhead wall together define a RDC outlet through the bulkhead wall and adjacent to the combustion chamber;

    a fuel manifold assembly extended at least partially through the bulkhead wall, wherein the fuel manifold assembly defines a fuel manifold assembly exit positioned adjacent to the combustion chamber; and

    a deflagrative combustion system formed at least by the inner liner, the outer liner, the bulkhead wall, and the fuel manifold assembly.

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