Patents by Inventor Paul Hadley Vitt

Paul Hadley Vitt 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: 11125089
    Abstract: A turbomachinery apparatus includes: a turbine, including: a turbine component defining an arcuate flowpath surface; an array of axial-flow turbine airfoils extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of fences extending from the flowpath surface, in the spaces between the turbine airfoils, each fence having opposed concave and convex sides extending between a leading edge and a trailing edge, wherein the fences have a nonzero camber and a constant thickness, are axially located near the leading edges of adjacent turbine airfoils, and wherein at least one of a chord dimension of the fences and a span dimension of the fences is less than the corresponding dimension of the turbine airfoils.
    Type: Grant
    Filed: August 7, 2019
    Date of Patent: September 21, 2021
    Assignees: General Electric Company, GE Avio S.r.l.
    Inventors: Francesco Bertini, Aspi Rustom Wadia, Lyle D. Dailey, Andrea Arnone, Filippo Rubechini, Matteo Giovannini, Paul Hadley Vitt, Jeffrey Donald Clements
  • Publication number: 20210270137
    Abstract: A turbine engine with at least a compressor section, combustor section, turbine section and a set of airfoils. The airfoils include geometric characteristics to create a high contraction ratio (CR), a low blade turning (BT) at a radially inward location the airfoil, a low solidity, or a low aspect ratio (AR).
    Type: Application
    Filed: January 14, 2021
    Publication date: September 2, 2021
    Inventors: Ernesto Sozio, Francesco Bertini, Jeffrey Donald Clements, Jonathan Ong, Lyle Douglas Dailey, Paul Hadley Vitt, Matteo Renato Usseglio
  • Publication number: 20210079799
    Abstract: An apparatus for a nozzle assembly for a turbine engine and a method of forming the nozzle assembly are described herein. The nozzle assembly can include a set of nozzles including an inner band and an outer band, with one or more airfoils extending between the inner and outer bands. The nozzles can be coupled to adjacent nozzles at the inner and outer bands to form the nozzle assembly. A throat can be defined at the minimum cross-sectional area between adjacent airfoils in the nozzle assembly. A formed portion can be formed on either of or both of the inner or outer band at the throat.
    Type: Application
    Filed: September 12, 2019
    Publication date: March 18, 2021
    Inventors: Paul Hadley Vitt, Wilson Frost, Mark Broomer
  • Patent number: 10934858
    Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
    Type: Grant
    Filed: March 26, 2019
    Date of Patent: March 2, 2021
    Assignee: General Electric Company
    Inventors: Eric Joseph Schroeder, Paul Hadley Vitt, Timothy John Swenson, Kirk Douglas Gallier, Aspi Rustom Wadia
  • Publication number: 20200362713
    Abstract: A turbomachinery apparatus includes: a turbine, including: a turbine component defining an arcuate flowpath surface; an array of axial-flow turbine airfoils extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of fences extending from the flowpath surface, in the spaces between the turbine airfoils, each fence having opposed concave and convex sides extending between a leading edge and a trailing edge, wherein the fences have a nonzero camber and a constant thickness, are axially located near the leading edges of adjacent turbine airfoils, and wherein at least one of a chord dimension of the fences and a span dimension of the fences is less than the corresponding dimension of the turbine airfoils.
    Type: Application
    Filed: August 7, 2019
    Publication date: November 19, 2020
    Inventors: Francesco Bertini, Aspi Rustom Wadia, Lyle D. Dailey, Andrea Arnone, Filippo Rubechinni, Matteo Giovanni, Paul Hadley Vitt, Jeffrey Donald Clements
  • Patent number: 10760426
    Abstract: An apparatus and method for controlling a flow of fluid through a nozzle assembly including a set of nozzles. The nozzles can have a set of airfoils defining a throat between the airfoils. One or more exhaust holes can be provided in the airfoils downstream of the throat. A fluid supply line can be fluidly coupled to the exhaust holes for selectively supplying a flow of fluid through the exhaust holes.
    Type: Grant
    Filed: June 13, 2017
    Date of Patent: September 1, 2020
    Assignee: General Electric Company
    Inventors: Paul Hadley Vitt, Brian David Keith
  • Publication number: 20200191009
    Abstract: A shroud assembly for a gas turbine engine includes: at least one shroud hanger; an annular array of shroud segments carried by the child hanger at least one and arrayed about an engine centerline axis, each of the shroud segments having a flowpath side defining a portion of a primary engine flowpath, and an opposed backside facing the at least one shroud hanger, wherein the shroud segment is mounted to the at least one shroud hanger such that it is movable in a radial direction between an inboard position and an outboard position, in response to a balance of gas pressures prevailing on the flowpath side and the backside; and biasing means which urge each of the shroud segments towards one of the positions.
    Type: Application
    Filed: December 13, 2018
    Publication date: June 18, 2020
    Inventors: Paul Hadley Vitt, Andrew Breeze-Stringfellow
  • Patent number: 10577955
    Abstract: A stage for a compressor or a turbine in a turbine engine can include an annular row of airfoils radially extending from corresponding platforms, where each platform can include a fore edge and aft edge and each airfoil can include a leading edge and trailing edge. At least one of the platforms can have a scalloped flow surface including a bulge and a trough.
    Type: Grant
    Filed: June 29, 2017
    Date of Patent: March 3, 2020
    Assignee: General Electric Company
    Inventors: Connor Marie Shirley, Harjit Singh Hura, Paul Hadley Vitt
  • Publication number: 20200049014
    Abstract: A turbomachinery apparatus (10) includes: a turbine (22), including: a turbine component (36) defining at least one arcuate flowpath surface (40); an array of axial-flow turbine airfoils (46) extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils (146) extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.
    Type: Application
    Filed: March 6, 2018
    Publication date: February 13, 2020
    Inventors: Jeffrey Donald Clements, Paul Hadley Vitt, Francesco Bertini, Aspi Rustom Wadia, Ganesh Seshadri, Mahendran Manoharan, Ravikanth Avancha
  • Publication number: 20190218918
    Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
    Type: Application
    Filed: March 26, 2019
    Publication date: July 18, 2019
    Inventors: Eric Joseph Schroeder, Paul Hadley Vitt, Timothy John Swenson, Kirk Douglas Gallier, Aspi Rustom Wadia
  • Patent number: 10344602
    Abstract: A transition duct includes fairings with transition duct flow passage and hollow fairing airfoils extending between outer and inner walls of fairings and means for smoothing pressure gradients along inner wall. One means is a contracting duct flow area of flow passage from leading edge of fairing airfoil to about 30% of fairing chord. Leading edges of fairing airfoil intersect outer walls aft of regions of high curvature of outer walls. Leading edges may curve axially aftwardly and radially into fairing airfoils and transition duct flow passage between radially outer and inner walls from radially outer and inner intersection points. Transition duct downstream second area/upstream first area may be greater than about 1.35. Turbine center frame may include outer ring coupled to central hub with struts extending through hollow airfoils.
    Type: Grant
    Filed: April 18, 2016
    Date of Patent: July 9, 2019
    Assignee: General Electric Company
    Inventors: Harjit Hura, Paul Hadley Vitt, Brian David Keith, Jonathan Ong
  • Patent number: 10253637
    Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
    Type: Grant
    Filed: December 11, 2015
    Date of Patent: April 9, 2019
    Assignee: General Electric Company
    Inventors: Eric Joseph Schroeder, Paul Hadley Vitt, Timothy John Swenson, Kirk Douglas Gallier, Aspi Rustom Wadia
  • Publication number: 20190003323
    Abstract: A stage for a compressor or a turbine in a turbine engine can include an annular row of airfoils radially extending from corresponding platforms, where each platform can include a fore edge and aft edge and each airfoil can include a leading edge and trailing edge. At least one of the platforms can have a scalloped flow surface including a bulge and a trough.
    Type: Application
    Filed: June 29, 2017
    Publication date: January 3, 2019
    Inventors: Connor Marie Shirley, Harjit Singh Hura, Paul Hadley Vitt
  • Publication number: 20180355738
    Abstract: An apparatus and method for controlling a flow of fluid through a nozzle assembly including a set of nozzles. The nozzles can have a set of airfoils defining a throat between the airfoils. One or more exhaust holes can be provided in the airfoils downstream of the throat. A fluid supply line can be fluidly coupled to the exhaust holes for selectively supplying a flow of fluid through the exhaust holes.
    Type: Application
    Filed: June 13, 2017
    Publication date: December 13, 2018
    Inventors: Paul Hadley Vitt, Brian David Keith
  • Publication number: 20170298747
    Abstract: A transition duct includes fairings with transition duct flow passage and hollow fairing airfoils extending between outer and inner walls of fairings and means for smoothing pressure gradients along inner wall. One means is a contracting duct flow area of flow passage from leading edge of fairing airfoil to about 50% of fairing chord. Leading edges of fairing airfoil intersect outer walls aft of regions of high curvature of outer walls. Leading edges may curve axially aftwardly and radially into fairing airfoils and transition duct flow passage between radially outer and inner walls from radially outer and inner intersection points. Transition duct downstream second area/upstream first area may be greater than about 1.35. Turbine center frame may include outer ring coupled to central hub with struts extending through hollow airfoils.
    Type: Application
    Filed: April 18, 2016
    Publication date: October 19, 2017
    Inventors: Harjit Hura, Paul Hadley Vitt, Brian David Keith, Jonathan Ong
  • Publication number: 20170167275
    Abstract: A turbine blade is described herein, the turbine blade including a blade root, a blade tip, and an airfoil extending between the blade root and the blade tip. The airfoil has opposite pressure and suction sides extending between a forward leading edge and an aft trailing edge of the airfoil, and a maximum thickness located between the leading edge and the trailing edge. The blade tip includes a winglet extending laterally outward from at least one of the pressure side and the suction side from a leading point between the leading edge and the maximum thickness aftward to a trailing point between the maximum thickness and the trailing edge.
    Type: Application
    Filed: December 11, 2015
    Publication date: June 15, 2017
    Inventors: Eric Joseph Schroeder, Paul Hadley Vitt, Timothy John Swenson, Kirk Douglas Gallier, Aspi Rustom Wadia
  • Patent number: 8632311
    Abstract: A turbine blade includes an airfoil terminating in a tip. The tip includes a first rib conforming with a concave pressure side of the airfoil, and a second rib conforming with a convex suction side of the airfoil. The second rib is flared outwardly from the suction side.
    Type: Grant
    Filed: August 21, 2006
    Date of Patent: January 21, 2014
    Assignee: General Electric Company
    Inventors: Kevin Samuel Klasing, Ching-Pang Lee, Paul Hadley Vitt, Brian David Keith
  • Patent number: 8512003
    Abstract: A turbine blade includes first and second tip ribs extending from a tip floor to define a tip cavity. An exit ramp bridges the ribs and rises in elevation aft from the floor.
    Type: Grant
    Filed: August 21, 2006
    Date of Patent: August 20, 2013
    Assignee: General Electric Company
    Inventors: Kevin Samuel Klasing, Ching-Pang Lee, Paul Hadley Vitt, Brian David Keith
  • Patent number: 8500396
    Abstract: A turbine blade includes an airfoil tip with first and second ribs extending along the opposite pressure and suction sides. The ribs extend outwardly from a tip floor and are joined together at opposite leading and trailing edges. A cascade tip baffle transversely bridges the two ribs above the tip floor forward of the maximum width of the tip to partition the tip chordally into corresponding tip pockets on opposite sides of the baffle.
    Type: Grant
    Filed: August 21, 2006
    Date of Patent: August 6, 2013
    Assignee: General Electric Company
    Inventors: Kevin Samuel Klasing, Ching-Pang Lee, Paul Hadley Vitt, Brian David Keith
  • Patent number: 8425183
    Abstract: A turbine blade includes an airfoil having first and second tip ribs extending along the opposite pressure and suction sides thereof. The tip ribs are spaced apart between the leading and trailing edges of the airfoil to include a trifurcate tip baffle defining a triforial tip cavity.
    Type: Grant
    Filed: November 20, 2006
    Date of Patent: April 23, 2013
    Assignee: General Electric Company
    Inventors: Ching-Pang Lee, Kevin Samuel Klasing, Paul Hadley Vitt, Brian David Keith