Patents by Inventor Zhenhua Xiao

Zhenhua Xiao 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: 10308705
    Abstract: The invention relates to synthetic liver-specific promoters and expression constructs for producing polypeptides and functional nucleic acids in the liver of a subject. The invention further relates to Factor VIII proteins containing modifications in the amino acid sequence of the Factor VIII protein, as well as nucleic acid constructs encoding the Factor VIII proteins and methods of using these compositions to treat a bleeding disorder.
    Type: Grant
    Filed: February 5, 2016
    Date of Patent: June 4, 2019
    Assignee: The University of North Carolina at Chapel Hill
    Inventors: Xiao Xiao, Juan Li, Zhenhua Yuan
  • Patent number: 8504276
    Abstract: Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.
    Type: Grant
    Filed: February 28, 2008
    Date of Patent: August 6, 2013
    Assignee: Power Systems Mfg., LLC
    Inventors: Vincent C. Martling, Peter So, Zhenhua Xiao, Plazi Ricklin
  • Patent number: 7685823
    Abstract: An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between the flow sleeve and a combustion liner. The plurality of vanes serve to direct a flow of air entering the region between the flow sleeve and combustion liner in a substantially axial direction, such that components of tangential velocity are removed thereby providing a more uniform flow of air the combustion chamber and reducing the amount of pressure lost due attempting to straighten the airflow by pressure drop alone.
    Type: Grant
    Filed: October 28, 2005
    Date of Patent: March 30, 2010
    Assignee: Power Systems Mfg., LLC
    Inventors: Vincent C. Martling, Zhenhua Xiao
  • Publication number: 20090222187
    Abstract: Embodiments for controlling a gas turbine engine to minimize combustion dynamics and emissions are disclosed. Methods and an apparatus are provided for controlling the gas turbine engine where a compressor inlet temperature is measured and a turbine reference temperature is calculated in real-time and utilized to determine the most-efficient fuel splits and operating conditions for each of the fuel circuits. The fuel flow for the fuel circuits are then adjusted according to the identified fuel split.
    Type: Application
    Filed: February 28, 2008
    Publication date: September 3, 2009
    Applicant: POWER SYSTEMS MFG., LLC
    Inventors: VINCENT C. MARTLING, Peter SO, ZHENHUA XIAO, PLAZI RICKLIN
  • Publication number: 20090139238
    Abstract: An apparatus and method of providing a gas turbine combustor having increased combustion stability and reducing pressure drop across a gas turbine combustor is disclosed. A plurality of vanes is fixed to a flow sleeve radially between the flow sleeve and a combustion liner. The plurality of vanes serve to direct a flow of air entering the region between the flow sleeve and combustion liner in a substantially axial direction, such that components of tangential velocity are removed thereby providing a more uniform flow of air the combustion chamber and reducing the amount of pressure lost due attempting to straighten the airflow by pressure drop alone.
    Type: Application
    Filed: October 28, 2005
    Publication date: June 4, 2009
    Inventors: Vincent C. Martling, Zhenhua Xiao
  • Patent number: 7269957
    Abstract: A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness along the aft end of the combustion liner is improved, resulting in extended component life, while utilizing a simpler combustion liner geometry. The region of the combustion liner proximate its second end comprises a plurality of spring seals that seal against a transition duct while admitting a cooling fluid to pass into a passage, formed between the combustion liner and spring seals, that feeds a plurality of cooling holes located in the combustion liner proximate the liner second end. Depending on the cooling requirements, the cooling holes can be angled both axially and circumferentially to maximize the cooling effectiveness.
    Type: Grant
    Filed: May 28, 2004
    Date of Patent: September 18, 2007
    Inventors: Vincent C. Martling, Zhenhua Xiao
  • Patent number: 7137241
    Abstract: A gas turbine transition duct having a reduced pressure loss is disclosed. The transition duct of the preferred embodiment comprises a panel assembly having a first panel fixed to a second panel and a mounting assembly for securing the transition duct to a turbine inlet. The first panel includes a means for augmenting the heat transfer from the first panel while the second panel includes a plurality of first cooling holes for directing cooling air through the second panel. Specific details are provided regarding the first cooling holes and multiple embodiments are disclosed for the heat transfer augmentation of the transition duct first panel.
    Type: Grant
    Filed: April 30, 2004
    Date of Patent: November 21, 2006
    Assignee: Power Systems Mfg, LLC
    Inventors: Vincent C. Martling, Zhenhua Xiao
  • Patent number: 7096668
    Abstract: An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are lowered. An aft end of a combustion liner is telescopically received within the transition duct such that a combustion liner seal is in contact with an inner wall of the transition duct inlet ring. Increasing the dedicated cooling air supply to the combustion liner aft end, coupled with a modified combustion liner aft end geometry, significantly reduces turbulence and flow re-circulation, thereby resulting in lower metal temperatures and increased component life. Multiple embodiments of the interface region are disclosed depending on the amount of cooling required.
    Type: Grant
    Filed: December 22, 2003
    Date of Patent: August 29, 2006
    Inventors: Vincent C. Martling, Zhenhua Xiao
  • Patent number: 7047723
    Abstract: The present invention provides an apparatus and method for reducing the pressure loss of air prior to entering a combustion system, such that, for a known combustion system having a predetermined pressure loss, the resulting fluid entering the turbine has a higher supply pressure that will result in more efficient turbine and increased engine output. Significant enhancements include the addition of a plurality of deflector assemblies to direct the air from a compressor outlet towards an exposed single-wall transition duct to provide direct cooling to a first panel of the transition duct.
    Type: Grant
    Filed: April 30, 2004
    Date of Patent: May 23, 2006
    Inventors: Vincent C. Martling, Zhenhua Xiao
  • Publication number: 20050262845
    Abstract: A gas turbine combustion liner is disclosed having an alternate interface region between it and a transition duct where the cooling effectiveness along the aft end of the combustion liner is improved, resulting in extended component life, while utilizing a simpler combustion liner geometry. The region of the combustion liner proximate its second end comprises a plurality of spring seals that seal against a transition duct while admitting a cooling fluid to pass into a passage, formed between the combustion liner and spring seals, that feeds a plurality of cooling holes located in the combustion liner proximate the liner second end. Depending on the cooling requirements, the cooling holes can be angled both axially and circumferentially to maximize the cooling effectiveness.
    Type: Application
    Filed: May 28, 2004
    Publication date: December 1, 2005
    Inventors: Vincent Martling, Zhenhua Xiao
  • Publication number: 20050241317
    Abstract: The present invention provides an apparatus and method for reducing the pressure loss of air prior to entering a combustion system, such that, for a known combustion system having a predetermined pressure loss, the resulting fluid entering the turbine has a higher supply pressure that will result in more efficient turbine and increased engine output. Significant enhancements include the addition of a plurality of deflector assemblies to direct the air from a compressor outlet towards an exposed single-wall transition duct to provide direct cooling to a first panel of the transition duct.
    Type: Application
    Filed: April 30, 2004
    Publication date: November 3, 2005
    Inventors: Vincent Martling, Zhenhua Xiao
  • Publication number: 20050241321
    Abstract: A gas turbine transition duct having a reduced pressure loss is disclosed. The transition duct of the preferred embodiment comprises a panel assembly having a first panel fixed to a second panel and a mounting assembly for securing the transition duct to a turbine inlet. The first panel includes a means for augmenting the heat transfer from the first panel while the second panel includes a plurality of first cooling holes for directing cooling air through the second panel. Specific details are provided regarding the first cooling holes and multiple embodiments are disclosed for the heat transfer augmentation of the transition duct first panel.
    Type: Application
    Filed: April 30, 2004
    Publication date: November 3, 2005
    Inventors: Vincent Martling, Zhenhua Xiao
  • Publication number: 20050132708
    Abstract: An interface region between a combustion liner and a transition duct of a gas turbine combustor is disclosed having improved cooling such that component life is increased and metal temperatures are lowered. An aft end of a combustion liner is telescopically received within the transition duct such that a combustion liner seal is in contact with an inner wall of the transition duct inlet ring. Increasing the dedicated cooling air supply to the combustion liner aft end, coupled with a modified combustion liner aft end geometry, significantly reduces turbulence and flow re-circulation, thereby resulting in lower metal temperatures and increased component life. Multiple embodiments of the interface region are disclosed depending on the amount of cooling required.
    Type: Application
    Filed: December 22, 2003
    Publication date: June 23, 2005
    Inventors: Vincent Martling, Zhenhua Xiao
  • Patent number: 6832482
    Abstract: A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said cooling air under pressure enters the combustion chamber/venturi near the aft portion of the combustion chamber, passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The method prevents any channel/passage cooling air from being received into the combustion chamber, and at the same time, introduces the outlet of the cooling air, after the air has passed over the combustion chamber of the venturi and has been heated, back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process.
    Type: Grant
    Filed: November 22, 2002
    Date of Patent: December 21, 2004
    Assignee: Power Systems Mfg, LLC
    Inventors: Vincent C. Martling, Zhenhua Xiao
  • Patent number: 6772595
    Abstract: A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said cooling air under pressure enters the combustion chamber/venturi near the aft portion of the combustion chamber, passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The method prevents any channel/passage cooling air from being received into the combustion chamber, and at the same time, introduces the outlet of the cooling air, after the air has passed over the combustion chamber of the venturi and has been heated, back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process.
    Type: Grant
    Filed: November 15, 2002
    Date of Patent: August 10, 2004
    Assignee: Power Systems Mfg., LLC
    Inventors: Vincent C. Martling, Zhenhua Xiao
  • Publication number: 20030233832
    Abstract: A method for providing cooling air to the venturi and the combustion chamber in a low NOx emission combustor as used in a gas turbine engine that includes the steps of providing an annular air passage surrounding said combustion chamber and venturi where said cooling air under pressure enters the combustion chamber/venturi near the aft portion of the combustion chamber, passing the air along the combustion chamber, past the venturi where the air exits near the front portion of the convergent area of the venturi. The method prevents any channel/passage cooling air from being received into the combustion chamber, and at the same time, introduces the outlet of the cooling air, after the air has passed over the combustion chamber of the venturi and has been heated, back into the premix chamber thereby improving the efficiency of the combustor while reducing and lowering NOx emission in the combustion process.
    Type: Application
    Filed: November 15, 2002
    Publication date: December 25, 2003
    Applicant: Power Systems Mfg, LLC
    Inventors: Vincent C. Martling, Zhenhua Xiao
  • Patent number: 6644032
    Abstract: A transition duct having a panel assembly with an inlet end of generally circular cross section and an outlet end having a generally rectangular arc-like cross section is disclosed. The panel assembly has an uncoated internal profile substantially in accordance with coordinate values X, Y, and Z as set forth in Table 1 carried only to three decimal places wherein the coordinates are taken at a sweep angle &thgr; wherein &thgr; is an angle measured from said inlet end and X, Y, and Z are coordinates defining the panel assembly profile at each angle &thgr; from the inlet end. An alternate embodiment is also disclosed defining an envelope for the uncoated internal profile of the panel assembly.
    Type: Grant
    Filed: October 22, 2002
    Date of Patent: November 11, 2003
    Assignee: Power Systems MFG, LLC
    Inventors: Stephen W. Jorgensen, John C. Resos, Zhenhua Xiao, Heather Johnston
  • Patent number: 6558114
    Abstract: The subcavity between a stator seal assembly and the upstream rotor disc in the interstage disc cavity of a gas turbine is divided into a radially inward region and a radially outward region by an annular baffle that extends from the seal assembly partially across the subcavity toward the rotor disc. The volume of cooling air injected into the interstage disc cavity can be reduced to increase turbine efficiency because the baffle interrupts recirculation in the subcavity to confine ingress of the hot main gas flow to the radially outward region away from the rotor seals.
    Type: Grant
    Filed: September 29, 2000
    Date of Patent: May 6, 2003
    Assignee: Siemens Westinghouse Power Corporation
    Inventors: Joseph Theodore Tapley, John Y. Xia, Zhenhua Xiao