Patents by Inventor Adam L. Hart

Adam L. Hart 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: 11248797
    Abstract: An apparatus and method for mounting a combustion liner within a flow sleeve of a gas turbine combustion system is disclosed. A mounting system comprises a plurality of low-profile mounting tabs secured to a combustion liner where each of the mounting tabs are placed within slots of flow sleeve pegs when the combustion liner is installed in a flow sleeve. A plurality of liner stop brackets are removably secured to a flange of the flow sleeve and have an arm extending to be adjacent to a top contact surface of the mounting tabs. The mounting system reduces blockage to the surrounding airflow.
    Type: Grant
    Filed: November 2, 2018
    Date of Patent: February 15, 2022
    Assignee: Chromalloy Gas Turbine LLC
    Inventors: Daniel L. Folkers, Zhenhua Xiao, Vincent C. Martling, Adam L. Hart
  • Patent number: 10982859
    Abstract: A system for retaining a cross fire tube in a multi-combustor gas turbine engine is disclosed. The system comprises a flow sleeve having a generally annular body, and a flange at a forward end thereof and having one or more recessed portions. A cross fire tube extends through one or more openings in the flow sleeve and is secured in place by a retention clip. The retention clip includes a plurality of fingers which engage the cross fire tube and a mounting plate engaging the one or more recessed portions of the flow sleeve flange so as to create a clip engagement having a lower profile than prior art configurations.
    Type: Grant
    Filed: November 2, 2018
    Date of Patent: April 20, 2021
    Assignee: Chromalloy Gas Turbine LLC
    Inventors: Daniel L. Folkers, Adam L. Hart
  • Publication number: 20200141585
    Abstract: An apparatus and method for mounting a combustion liner within a flow sleeve of a gas turbine combustion system is disclosed. A mounting system comprises a plurality of low-profile mounting tabs secured to a combustion liner where each of the mounting tabs are placed within slots of flow sleeve pegs when the combustion liner is installed in a flow sleeve. A plurality of liner stop brackets are removably secured to a flange of the flow sleeve and have an arm extending to be adjacent to a top contact surface of the mounting tabs. The mounting system reduces blockage to the surrounding airflow.
    Type: Application
    Filed: November 2, 2018
    Publication date: May 7, 2020
    Inventors: DANIEL L. FOLKERS, ZHENHUA XIAO, VINCENT C. MARTLING, ADAM L. HART
  • Publication number: 20200141584
    Abstract: A system for retaining a cross fire tube in a multi-combustor gas turbine engine is disclosed. The system comprises a flow sleeve having a generally annular body, and a flange at a forward end thereof and having one or more recessed portions. A cross fire tube extends through one or more openings in the flow sleeve and is secured in place by a retention clip. The retention clip includes a plurality of fingers which engage the cross fire tube and a mounting plate engaging the one or more recessed portions of the flow sleeve flange so as to create a clip engagement having a lower profile than prior art configurations.
    Type: Application
    Filed: November 2, 2018
    Publication date: May 7, 2020
    Inventors: DANIEL L. FOLKERS, ADAM L. HART
  • Patent number: 9840931
    Abstract: A gas turbine engine component has an axial seal pin assembly for sealing between adjacent platform regions where the seal pin assembly design provides a seal pin damper slot extending to a forward axial stop in a forward buttress region. The forward axial stop includes a relief slot to interrupt the loadpath from the airfoil into the blade neck and attachment regions to reduce the stress concentrations in these regions.
    Type: Grant
    Filed: September 30, 2013
    Date of Patent: December 12, 2017
    Assignee: ANSALDO ENERGIA IP UK LIMITED
    Inventors: Gaurav K. Joshi, John Cuyler Hunt, Orestes J. Maurell, Adam L. Hart
  • Publication number: 20140270072
    Abstract: A system and method for inspecting a grain size of a cast alloy component while maintaining the structural integrity of the cast alloy component is disclosed. The method includes recording a radiographic image of the component, identifying areas of the component to be inspected, and locating one or more lines having a pre-determined length on the radiographic image at an area to be inspected. Then, a total number of intersections with the one or more lines are determined and an average grain size is calculated.
    Type: Application
    Filed: March 11, 2014
    Publication date: September 18, 2014
    Inventors: ROBERT L. MCCORMICK, JOSEPH YOUNG, ADAM L. HART
  • Publication number: 20140030100
    Abstract: A gas turbine engine component has an axial seal pin assembly for sealing between adjacent platform regions where the seal pin assembly design provides a seal pin damper slot extending to a forward axial stop in a forward buttress region. The forward axial stop includes a relief slot to interrupt the loadpath from the airfoil into the blade neck and attachment regions to reduce the stress concentrations in these regions.
    Type: Application
    Filed: September 30, 2013
    Publication date: January 30, 2014
    Inventors: GAURAV K. JOSHI, JOHN CUYLER HUNT, ORESTES J. MAURELL, ADAM L. HART
  • Patent number: 8511982
    Abstract: A compressor diaphragm for a gas turbine engine having improved wear capability, manufacturability, and assembly techniques is disclosed. The diaphragm includes a shiplap-type joint at an outer vane platform for connecting to adjacent vane assemblies and a clamshell-like assembly of a seal box secures and seals regions around the inner vane platform of the compressor diaphragm so as to reduce wear between the seal box and the vane assemblies. The inner platform of the diaphragm segments are fastened to each other through circumferentially-oriented fasteners at the inner diameter platform.
    Type: Grant
    Filed: November 23, 2009
    Date of Patent: August 20, 2013
    Assignee: Alstom Technology Ltd.
    Inventors: Adam L. Hart, Charles A. Ellis, Elliot I. Goodman, W. David Day, Gerald Raresheid, James Page Strohl
  • Publication number: 20100129211
    Abstract: A compressor diaphragm for a gas turbine engine having improved wear capability, manufacturability, and assembly techniques is disclosed. The diaphragm includes a shiplap-type joint at an outer vane platform for connecting to adjacent vane assemblies and a clamshell-like assembly of a seal box secures and seals regions around the inner vane platform of the compressor diaphragm so as to reduce wear between the seal box and the vane assemblies. The inner platform of the diaphragm segments are fastened to each other through circumferentially-oriented fasteners at the inner diameter platform.
    Type: Application
    Filed: November 23, 2009
    Publication date: May 27, 2010
    Applicant: ALSTOM TECHNOLOGIES LTD. LLC
    Inventors: Adam L. Hart, Charles A. Ellis, Elliot I. Goodman, W. David Day, Gerald Raresheid, James Page Strohl