Patents by Inventor Jason David Liles

Jason David Liles 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).

  • Publication number: 20210102474
    Abstract: A replaceable rotor blade tip clearance measurement device for a gas turbine engine, includes a threaded section along an axis and an integral abradable tip with an internal lattice geometry that extends from the threaded section along the axis.
    Type: Application
    Filed: October 3, 2019
    Publication date: April 8, 2021
    Applicant: United Technologies Corporation
    Inventors: Jose R. Paulino, Veronika Reynolds, Jason David Liles
  • Patent number: 10330011
    Abstract: A fairing sub-assembly 88 for a turbine frame comprises an inner ring 50, an outer ring 48 and a plurality of strut-shells. The inner ring is formed of a plurality of inner segments 82. The outer ring is formed of a plurality of outer segments 80. The plurality of strut-shells 84, 86 connecting the inner ring 48 and the outer ring 50. In another embodiment, the fairing sub-assembly comprises an inner band 45 joining the plurality of inner segments 82 and the plurality of strut-shells 86 to form outer slots, and an outer band 44 joining the plurality of outer segments 80 and the plurality of strut-shells 86 to form inner slots. A method of assembling a fairing 46 comprises inserting the aforementioned fairing sub-assembly 38 into an aft end of a turbine frame 42, inserting a plurality of forward strut-shells 84 into the outer and inner slots at a forward end of the turbine frame 42, and joining the forward strut-shells 84 to the fairing sub-assembly 88.
    Type: Grant
    Filed: March 11, 2014
    Date of Patent: June 25, 2019
    Assignee: United Technologies Corporation
    Inventors: Conway Chuong, Jason David Liles, Jonathan Ariel Scott
  • Publication number: 20170145827
    Abstract: A rotor blade for a gas turbine engine is provided. The rotor blade having: an attachment; an airfoil extending from the attachment to a tip; and a squealer pocket located in a surface of the tip, wherein the squealer pocket is at least partially surrounded by a first surface of a wall located between the squealer pocket and a pressure side of the airfoil, wherein the first surface of the wall has a convex configuration with respect to the pressure side of the airfoil as it extends from a leading edge to a trailing edge of the airfoil.
    Type: Application
    Filed: February 8, 2016
    Publication date: May 25, 2017
    Inventors: Scott D. Lewis, Kyle C. Lana, Jason David Liles
  • Patent number: 9631517
    Abstract: A gas turbine engine component comprises a frame and a fairing. The frame comprises a monolithic ring-strut-ring structure. The fairing comprises a multi-segment ring-strut-ring structure that is assembled around the frame. A method of assembling the frame and fairing comprises positioning a plurality of shroud segments within a frame and joining the plurality of shroud segments to each other so that the fairing is trapped within the frame. In one embodiment, the fairing comprises a plurality of outer diameter shroud segments, a plurality of inner diameter shroud segments, a plurality of strut segments, and stiffening features connected to the plurality of strut segments to strengthen the fairing.
    Type: Grant
    Filed: December 29, 2012
    Date of Patent: April 25, 2017
    Assignee: United Technologies Corporation
    Inventors: Jason David Liles, Charles T. Ruby
  • Publication number: 20160017807
    Abstract: A fairing sub-assembly 88 for a turbine frame comprises an inner ring 50, an outer ring 48 and a plurality of strut-shells. The inner ring is formed of a plurality of inner segments 82. The outer ring is formed of a plurality of outer segments 80. The plurality of strut-shells 84, 86 connecting the inner ring 48 and the outer ring 50. In another embodiment, the fairing sub-assembly comprises an inner band 45 joining the plurality of inner segments 82 and the plurality of strut-shells 86 to form outer slots, and an outer band 44 joining the plurality of outer segments 80 and the plurality of strut-shells 86 to form inner slots. A method of assembling a fairing 46 comprises inserting the aforementioned fairing sub-assembly 38 into an aft end of a turbine frame 42, inserting a plurality of forward strut-shells 84 into the outer and inner slots at a forward end of the turbine frame 42, and joining the forward strut-shells 84 to the fairing sub-assembly 88.
    Type: Application
    Filed: March 11, 2014
    Publication date: January 21, 2016
    Inventors: Conway Chuong, Jason David Liles, Jonathan Ariel Scott
  • Publication number: 20140186167
    Abstract: A gas turbine engine component comprises a frame and a fairing. The frame comprises a monolithic ring-strut-ring structure. The fairing comprises a multi-segment ring-strut-ring structure that is assembled around the frame. A method of assembling the frame and fairing comprises positioning a plurality of shroud segments within a frame and joining the plurality of shroud segments to each other so that the fairing is trapped within the frame. In one embodiment, the fairing comprises a plurality of outer diameter shroud segments, a plurality of inner diameter shroud segments, a plurality of strut segments, and stiffening features connected to the plurality of strut segments to strengthen the fairing.
    Type: Application
    Filed: December 29, 2012
    Publication date: July 3, 2014
    Applicant: UNITED TECHNOLOGIES CORPORATION
    Inventors: Jason David Liles, Charles T. Ruby