Patents by Inventor Aspi Rustom Wadia

Aspi Rustom Wadia 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: 11149552
    Abstract: A fan for a gas turbine engine is provided. The fan includes a rotor including at least one rotor stage having a rotatable disk defining a flowpath surface and an array of rotor airfoils extending outward from the flowpath surface; an array of splitter airfoils extending outward from the flowpath surface, wherein the splitter airfoils and the rotor airfoils are disposed in a sequential arrangement; and a shroud extending between the rotor airfoils and the splitter airfoils.
    Type: Grant
    Filed: December 13, 2019
    Date of Patent: October 19, 2021
    Assignee: General Electric Company
    Inventors: Anthony Louis DiPietro, Jr., Tyler James Alexander, Joseph Capozzi, Aspi Rustom Wadia, Andrew Breeze-Stringfellow
  • 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: 20210180458
    Abstract: A fan for a gas turbine engine is provided. The fan includes a rotor including at least one rotor stage having a rotatable disk defining a flowpath surface and an array of rotor airfoils extending outward from the flowpath surface; an array of splitter airfoils extending outward from the flowpath surface, wherein the splitter airfoils and the rotor airfoils are disposed in a sequential arrangement; and a shroud extending between the rotor airfoils and the splitter airfoils.
    Type: Application
    Filed: December 13, 2019
    Publication date: June 17, 2021
    Inventors: Anthony Louis DiPietro, JR., Tyler James Alexander, Joseph Capozzi, Aspi Rustom Wadia, Andrew Breeze-Stringfellow
  • Patent number: 11002141
    Abstract: An apparatus and method of managing negative incidence of an airfoil are provided. The apparatus includes a first row of stationary turbine main vanes and a second row of auxiliary vanes extending radially inwardly from a stationary casing of the turbine proximate the adjacent leading edge of the main vane. The apparatus also includes a flow channel defined between a pressure side of an auxiliary vane of the second row of auxiliary vanes and a suction side of an adjacent main vane of the row of stationary turbine main vanes.
    Type: Grant
    Filed: May 22, 2017
    Date of Patent: May 11, 2021
    Assignee: General Electric Company
    Inventors: David Paul Lurie, Sherif Alykadry Abdelfattah, Michael Julian Castillo, Anthony Louis DiPietro, Jr., Aspi Rustom Wadia, Gregory Burr Heitland
  • 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
  • Patent number: 10914318
    Abstract: A rotary component for a gas turbine engine defining a central axis extending along an axial direction, a radial direction extending perpendicular to the axial direction, and a circumferential direction perpendicular to both the central axis and the radial direction. The rotary component includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in the radial direction and defining an annular gap between a tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features on an interior surface of the outer casing. A first feature of the feature(s) defines a first casing thickness, and a second feature positioned at least partially circumferentially or axially from the first feature defines a second casing thickness different than the first casing thickness.
    Type: Grant
    Filed: January 10, 2019
    Date of Patent: February 9, 2021
    Assignee: General Electric Company
    Inventors: Joseph Capozzi, Aspi Rustom Wadia
  • Patent number: 10883515
    Abstract: An apparatus and method of managing negative incidence of an airfoil are provided. The apparatus includes a row of vane pairs including a first row of main vanes extending radially inwardly from a stationary casing member and spaced circumferentially about a first axial location of the stationary casing member. The apparatus also includes a second row of auxiliary vanes extending radially inwardly from the stationary casing member and spaced circumferentially about a second axial location of the stationary casing member. The apparatus also includes a flow channel defined between a pressure side of each auxiliary vane and a suction side of an adjacent main vane proximate a leading edge of the adjacent main vane.
    Type: Grant
    Filed: May 22, 2017
    Date of Patent: January 5, 2021
    Assignee: General Electric Company
    Inventors: David Paul Lurie, Sherif Alykadry Abdelfattah, Michael Julian Castillo, Anthony Louis DiPietro, Jr., Aspi Rustom Wadia, Eric Andrew Falk, William Joseph Solomon, Andrew Breeze-Stringfellow
  • 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
  • Publication number: 20200224675
    Abstract: A rotary component for a gas turbine engine defining a central axis extending along an axial direction, a radial direction extending perpendicular to the axial direction, and a circumferential direction perpendicular to both the central axis and the radial direction. The rotary component includes a plurality of rotor blades operably coupled to a rotating shaft extending along the central axis and an outer casing arranged exterior to the plurality of rotor blades in the radial direction and defining an annular gap between a tip of each of the plurality of rotor blades and the outer casing. The outer casing includes a plurality of features on an interior surface of the outer casing. A first feature of the feature(s) defines a first casing thickness, and a second feature positioned at least partially circumferentially or axially from the first feature defines a second casing thickness different than the first casing thickness.
    Type: Application
    Filed: January 10, 2019
    Publication date: July 16, 2020
    Inventors: Joseph Capozzi, Aspi Rustom Wadia
  • Patent number: 10670037
    Abstract: A turbofan engine includes a compressor rotor, a plurality of main blades circumferentially mounted on the compressor rotor, and a plurality of spinner blades circumferentially mounted on the compressor rotor. Each of the spinner blades is located forward of a leading edge of a corresponding one of the main blades. Each of the spinner blades is circumferentially offset to the corresponding one of the main blades.
    Type: Grant
    Filed: November 21, 2017
    Date of Patent: June 2, 2020
    Assignee: General Electric Company
    Inventors: Aspi Rustom Wadia, Deepak Manohar Kamath, Daniel Waslo
  • 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
  • Patent number: 10385871
    Abstract: An apparatus and method of managing negative incidence in a compressor is provided. The apparatus includes a first row of stationary main vanes, and a second row of stationary auxiliary vanes extending radially inwardly from a stationary casing of the compressor proximate the leading edges of the main vanes. A flow channel is defined between a pressure side of an auxiliary vane of the second row of auxiliary vanes and a suction side of an adjacent main vane of the row of main vanes.
    Type: Grant
    Filed: May 22, 2017
    Date of Patent: August 20, 2019
    Assignee: General Electric Company
    Inventors: David Paul Lurie, Sherif Alykadry Abdelfattah, Michael Julian Castillo, Anthony Louis DiPietro, Jr., Aspi Rustom Wadia
  • 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
  • Publication number: 20190154055
    Abstract: A turbofan engine comprising a compressor rotor, a plurality of main blades, the main blades are circumferentially mounted on the compressor rotor; a plurality of spinner blades, the spinner blades are circumferentially mounted on the compressor rotor, the spinner blades are located forward to the leading edge of the main blades; each spinner blade is circumferentially offset to a corresponding main blade.
    Type: Application
    Filed: November 21, 2017
    Publication date: May 23, 2019
    Inventors: ASPI Rustom WADIA, Deepak Manohar Kamath, Daniel Waslo
  • 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: 20180335051
    Abstract: An apparatus and method of managing negative incidence of an airfoil are provided. The apparatus includes a row of vane pairs including a first row of main vanes extending radially inwardly from a stationary casing member and spaced circumferentially about a first axial location of the stationary casing member. The apparatus also includes a second row of auxiliary vanes extending radially inwardly from the stationary casing member and spaced circumferentially about a second axial location of the stationary casing member. The apparatus also includes a flow channel defined between a pressure side of each auxiliary vane and a suction side of an adjacent main vane proximate a leading edge of the adjacent main vane.
    Type: Application
    Filed: May 22, 2017
    Publication date: November 22, 2018
    Inventors: David Paul Lurie, Sherif Alykadry Abdelfattah, Michael Julian Castillo, Anthony Louis DiPietro, JR., Aspi Rustom Wadia, Eric Andrew Falk, William Joseph Solomon, Andrew Breeze-Stringfellow
  • Publication number: 20180335050
    Abstract: An apparatus and method of managing negative incidence in a compressor is provided. The apparatus includes a first row of stationary main vanes, and a second row of stationary auxiliary vanes extending radially inwardly from a stationary casing of the compressor proximate the leading edges of the main vanes. A flow channel is defined between a pressure side of an auxiliary vane of the second row of auxiliary vanes and a suction side of an adjacent main vane of the row of main vanes.
    Type: Application
    Filed: May 22, 2017
    Publication date: November 22, 2018
    Inventors: David Paul Lurie, Sherif Alykadry Abdelfattah, Michael Julian Castillo, Anthony Louis DiPietro, JR., Aspi Rustom Wadia
  • Publication number: 20180334916
    Abstract: An apparatus and method of managing negative incidence of an airfoil are provided. The apparatus includes a first row of stationary turbine main vanes and a second row of auxiliary vanes extending radially inwardly from a stationary casing of the turbine proximate the adjacent leading edge of the main vane. The apparatus also includes a flow channel defined between a pressure side of an auxiliary vane of the second row of auxiliary vanes and a suction side of an adjacent main vane of the row of stationary turbine main vanes.
    Type: Application
    Filed: May 22, 2017
    Publication date: November 22, 2018
    Inventors: David Paul Lurie, Sherif Alykadry Abdelfattah, Michael Julian Castillo, Anthony Louis DiPietro, JR., Aspi Rustom Wadia, Gregory Burr Heitland
  • Publication number: 20180156124
    Abstract: A frame apparatus for a turbine engine includes: a turbomachinery stage discharging into a downstream flowpath, the stage including a rotor carrying an array of axial-flow rotor airfoils; and a frame disposed downstream of the turbomachinery stage, the frame including: a support structure comprising at least one of a hub and an annular casing; an annular array of stationary struts carried by the support structure, each strut having an airfoil shape with spaced-apart pressure and suction sides extending between a leading edge and a trailing edge thereof, the stationary struts defining spaces therebetween; and the stationary struts defining spaces therebetween; and a plurality of splitters carried by the support structure, the splitters positioned in the spaces between the stationary struts, wherein at least one of a chord dimension of the splitters and a span dimension of the splitters is less than the corresponding dimension of the stationary struts.
    Type: Application
    Filed: December 1, 2016
    Publication date: June 7, 2018
    Inventors: Jeffrey Donald Clements, Ganesh Seshadri, Mahendran Manoharan, Ravikanth Avancha, Aspi Rustom Wadia
  • 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