Patents by Inventor Steven J. Hoeser

Steven J. Hoeser has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).

  • Patent number: 9989014
    Abstract: A liquid injector system for a combustion engine, having a single feed inlet configured to receive a premixed liquid propellant under pressure or a purge gas under pressure, and having a liquid injector assembly. The assembly has a liquid injector having a hollow dome and injector holes configured to receive and inject the premixed liquid propellant or the purge gas through the liquid injector and into a combustion chamber. The liquid injector system has a liquid-to-gas zone between an injector outlet side and a flame front. A pressure gradient decrease between the liquid injector and the combustion chamber causes the premixed liquid propellant to expand from liquid to gas phases, which causes a temperature decrease at the liquid-to-gas zone, wherein the pressure gradient decrease and the temperature decrease prevent or mitigate the flame front from propagating upstream of the combustion chamber, which achieves an anti-flashback quenching liquid injector design.
    Type: Grant
    Filed: March 28, 2014
    Date of Patent: June 5, 2018
    Assignee: The Boeing Company
    Inventors: Anthony D. Straw, Mark J. Holthaus, Steven J. Hoeser
  • Publication number: 20160160801
    Abstract: A liquid injector system for a combustion engine, having a single feed inlet configured to receive a premixed liquid propellant under pressure or a purge gas under pressure, and having a liquid injector assembly. The assembly has a liquid injector having a hollow dome and injector holes configured to receive and inject the premixed liquid propellant or the purge gas through the liquid injector and into a combustion chamber. The liquid injector system has a liquid-to-gas zone between an injector outlet side and a flame front. A pressure gradient decrease between the liquid injector and the combustion chamber causes the premixed liquid propellant to expand from liquid to gas phases, which causes a temperature decrease at the liquid-to-gas zone, wherein the pressure gradient decrease and the temperature decrease prevent or mitigate the flame front from propagating upstream of the combustion chamber, which achieves an anti-flashback quenching liquid injector design.
    Type: Application
    Filed: March 28, 2014
    Publication date: June 9, 2016
    Applicant: The Boeing Company
    Inventors: Anthony D. Straw, Mark J. Holthaus, Steven J. Hoeser