Patents by Inventor Benjamin E. Toby

Benjamin E. Toby 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).

  • Multi-stage multi-plane combustion method for a gas turbine engine
    Publication number: 20040144098
    Abstract: A low emissions combustion method wherein, in an embodiment, a plurality of tangential fuel injectors introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.
    Type: Application
    Filed: December 12, 2003
    Publication date: July 29, 2004
    Inventors: Jeffrey W. Willis, Guillermo Pont, Benjamin E. Toby, Robert D. McKeirnan
  • Gas turbine engine having a multi-stage multi-plane combustion system
    Patent number: 6684642
    Abstract: A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.
    Type: Grant
    Filed: June 17, 2002
    Date of Patent: February 3, 2004
    Assignee: Capstone Turbine Corporation
    Inventors: Jeffrey W. Willis, Guillermo Pont, Benjamin E. Toby, Robert D. McKeirnan, Jr.
  • Gas turbine engine having a multi-stage multi-plane combustion system
    Publication number: 20020148232
    Abstract: A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.
    Type: Application
    Filed: June 17, 2002
    Publication date: October 17, 2002
    Inventors: Jeffrey W. Willis, Guillermo Pont, Benjamin E. Toby, Robert D. McKeirnan
  • Multi-stage multi-plane combustion method for a gas turbine engine
    Publication number: 20020148231
    Abstract: A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.
    Type: Application
    Filed: June 17, 2002
    Publication date: October 17, 2002
    Inventors: Jeffrey W. Willis, Guillermo Pont, Benjamin E. Toby, Robert D. McKeirnan
  • Multi-stage multi-plane combustion system for a gas turbine engine
    Patent number: 6453658
    Abstract: A low emissions combustion system with a plurality of tangential fuel injectors to introduce a fuel/air mixture at the combustor dome end of an annular combustion chamber in two spaced injector planes. Each of the spaced injector planes includes multiple tangential fuel injectors delivering premixed fuel and air into the annular combustor. A generally skirt-shaped flow control baffle extends from the tapered inner liner into the annular combustion chamber downstream of the fuel injector planes. A plurality of air dilution holes in the tapered inner liner underneath the flow control baffle introduce dilution air into the annular combustion chamber while another plurality of air dilution holes in the cylindrical outer liner introduces more dilution air downstream from the flow control baffle.
    Type: Grant
    Filed: February 24, 2000
    Date of Patent: September 24, 2002
    Assignee: Capstone Turbine Corporation
    Inventors: Jeffery W. Willis, Guillermo Pont, Benjamin E. Toby, Robert D. McKeirnan, Jr.