Patents by Inventor Hisham Salman Alkabie

Hisham Salman Alkabie 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).

  • Combustion chamber for a gas turbine engine
    Patent number: 6546731
    Abstract: In a twin wall combustion chamber for a gas turbine engine, the outer wall has impingement holes so that compressed air surrounding the chamber can pass through the holes to impinge on the inner wall, and the inner wall has effusion holes whereby air can effuse into the combustion chamber. The number of effusion holes is greater than the number of impingement holes, the effusion-holes preferably being arranged in groups of seven, comprising six holes equi-spaced around a central seventh hole, each group having an impingement hole in a fixed positional relationship to the central hole, preferably downstream of it.
    Type: Grant
    Filed: November 29, 2000
    Date of Patent: April 15, 2003
    Assignee: ABB Alstom Power UK Ltd.
    Inventors: Hisham Salman Alkabie, Robin Thomas David McMillan
  • Gas turbine fuel/air mixing arrangement with outer and inner radial inflow swirlers
    Patent number: 6311496
    Abstract: A fuel/air mixing arrangement for a combustion apparatus such as a gas turbine comprises a first swirler in which air and fuel are mixed to form a fuel/air mixture, a first conduit to supply a first proportion of the mixture to the combustion apparatus, a second swirler arranged to receive a second proportion of the mixture, and a second conduit to supply the second proportion from the second swirler to the combustion apparatus.
    Type: Grant
    Filed: December 17, 1998
    Date of Patent: November 6, 2001
    Assignee: Alstom Gas Turbines Limited
    Inventor: Hisham Salman Alkabie
  • Combustion chamber for a gas turbine engine
    Publication number: 20010004835
    Abstract: In a twin wall combustion chamber for a gas turbine engine, the outer wall has impingement holes so that compressed air surrounding the chamber can pass through the holes to impinge on the inner wall, and the inner wall has effusion holes whereby air can effuse into the combustion chamber. The number of effusion holes is greater than the number of impingement holes, the effusion holes preferably being arranged in groups of seven, comprising six holes equi-spaced around a central seventh hole, each group having an impingement hole in a fixed positional relationship to the central hole, preferably downstream of it.
    Type: Application
    Filed: November 29, 2000
    Publication date: June 28, 2001
    Inventors: Hisham Salman Alkabie, Robin Thomas David McMillan
  • Combuster and operating method for gas-or liquid-fuelled turbine arrangement
    Patent number: 5784876
    Abstract: In a combustor for a gas turbine, combustor 1 utilizes at least 50% of the air supplied thereto by a compressor to mix with the fuel to form a lean mixture, the remainder of the air is utilized for impingement cooling and the spent impingement cooling air is injected as radial jets into a post-primary combustion zone 17 through perforations 6.
    Type: Grant
    Filed: February 21, 1996
    Date of Patent: July 28, 1998
    Assignee: European Gas Turbines Limited
    Inventor: Hisham Salman Alkabie