Patents by Inventor Li Xing Pan

Li Xing Pan 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).

  • Full-span forward swept airfoils for gas turbine engines
    Patent number: 10605260
    Abstract: Rotor of a gas turbine engines having a rotor hub and a plurality of blades extending from the rotor hub, wherein each blade has a full-span forward sweep along a leading edge of the blade that starts at an airfoil root of the blade at the hub and extends to a blade tip, wherein a sweep of a blade is a percentage of a root axial chord length of the respective blade.
    Type: Grant
    Filed: September 9, 2016
    Date of Patent: March 31, 2020
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Li Xing Pan, Yuan Dong, Simon W. Evans, Robert W. Fessenden, Sue-Li Kingsley Chuang, Sean Nolan
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20190390688
    Abstract: A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be 2.5 percent or less. A mass flow rate of the compressor may be 3.0 pounds-mass per second or less.
    Type: Application
    Filed: August 5, 2019
    Publication date: December 26, 2019
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Robert W. FESSENDEN, Abhir A. ADHATE, Yuan DONG, Sean NOLAN, Li Xing PAN
  • Gas turbine engine airfoil
    Patent number: 10415591
    Abstract: A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be between 1.5 to 2.5 percent.
    Type: Grant
    Filed: September 21, 2016
    Date of Patent: September 17, 2019
    Assignee: UNITED TECHNOLOGIES CORPORATION
    Inventors: Robert W Fessenden, Abhir A Adhate, Yuan Dong, Sean Nolan, Li Xing Pan
  • GAS TURBINE ENGINE AIRFOIL
    Publication number: 20180080472
    Abstract: A compressor may include an airfoil configured to rotate about an axis. The airfoil may have a span measured radially from a root of the airfoil to a tip of the airfoil. A compressor case may be radially adjacent to the airfoil. The airfoil and the compressor case may define a clearance between the tip of the airfoil and a radially inner surface of the compressor case. A ratio of the clearance to the span may be between 1.5 to 2.5 percent.
    Type: Application
    Filed: September 21, 2016
    Publication date: March 22, 2018
    Applicant: United Technologies Corporation
    Inventors: Robert W. Fessenden, Abhir A. Adhate, Yuan Dong, Sean Nolan, Li Xing Pan
  • FULL-SPAN FORWARD SWEPT AIRFOILS FOR GAS TURBINE ENGINES
    Publication number: 20180073517
    Abstract: Rotor of a gas turbine engines having a rotor hub and a plurality of blades extending from the rotor hub, wherein each blade has a full-span forward sweep along a leading edge of the blade that starts at an airfoil root of the blade at the hub and extends to a blade tip, wherein a sweep of a blade is a percentage of a root axial chord length of the respective blade.
    Type: Application
    Filed: September 9, 2016
    Publication date: March 15, 2018
    Inventors: Li Xing Pan, Yuan Dong, Simon W. Evans, Robert W. Fessenden, Sue-Li Kingsley Chuang, Sean Nolan