Patents by Inventor Gregory John Kelsall

Gregory John Kelsall 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).

  • Methods of reducing emissions for a sequential combustion gas turbine and combustor for a gas turbine
    Patent number: 8511059
    Abstract: In an SEV combustor and a method for reducing emissions in an SEV combustor of a sequential combustion gas turbine, an air/fuel mixture is combusted in a first burner and the hot gases are subsequently introduced into the SEV combustor (1) for further combustion. The SEV combustor (1) includes a chamber having a chamber wall (5) defining a mixing portion (8), for mixing the hot gases with a fuel, and a combustion region (9), at least one inlet (2) for introducing the hot gases into the mixing region (8), at least one inlet (12) for introducing a fuel into the mixing region (8) and at least one inlet (10, 13) for introducing steam into the mixing region.
    Type: Grant
    Filed: September 30, 2008
    Date of Patent: August 20, 2013
    Assignee: ALSTOM Technology Ltd.
    Inventors: Madhavan Narasimhan Poyyapakkam, Adnan Eroglu, Richard Carroni, Gregory John Kelsall, Jian-Xin Chen
  • Fuel lance for a gas turbine engine including outer helical grooves
    Patent number: 8220271
    Abstract: A fuel lance (7) for introducing fuel into a gas flow in a combustor (1) of a gas turbine engine includes a region of the lance (7) through which the fuel is introduced into the gas flow having a generally helical formation (12).
    Type: Grant
    Filed: September 30, 2008
    Date of Patent: July 17, 2012
    Assignee: ALSTOM Technology Ltd.
    Inventors: Madhavan Narasimhan Poyyapakkam, Adnan Eroglu, Gregory John Kelsall
  • FUEL LANCE FOR A GAS TURBINE ENGINE
    Publication number: 20100077756
    Abstract: A fuel lance (7) for introducing fuel into a gas flow in a combustor (1) of a gas turbine engine includes a region of the lance (7) through which the fuel is introduced into the gas flow having a generally helical formation (12).
    Type: Application
    Filed: September 30, 2008
    Publication date: April 1, 2010
    Inventors: Madhavan Narasimhan Poyyapakkam, Adnan Eroglu, Gregory John Kelsall
  • METHODS OF REDUCING EMISSIONS FOR A SEQUENTIAL COMBUSTION GAS TURBINE AND COMBUSTOR FOR A GAS TURBINE
    Publication number: 20100077720
    Abstract: In an SEV combustor and a method for reducing emissions in an SEV combustor of a sequential combustion gas turbine, an air/fuel mixture is combusted in a first burner and the hot gases are subsequently introduced into the SEV combustor (1) for further combustion. The SEV combustor (1) includes a chamber having a chamber wall (5) defining a mixing portion (8), for mixing the hot gases with a fuel, and a combustion region (9), at least one inlet (2) for introducing the hot gases into the mixing region (8), at least one inlet (12) for introducing a fuel into the mixing region (8) and at least one inlet (10, 13) for introducing steam into the mixing region.
    Type: Application
    Filed: September 30, 2008
    Publication date: April 1, 2010
    Inventors: Madhavan Narasimhan Poyyapakkam, Adnan Eroglu, Richard Carroni, Gregory John Kelsall, Jian-Xin Chen