Patents by Inventor Andrew Paul Giametta

Andrew Paul Giametta 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: 10907491
    Abstract: A sealing system for a rotary machine is provided. The sealing system includes a pair of circumferentially-adjacent rotary components and an axial seal. Each of the rotary components includes a platform including a first side channel and an opposite second side channel, a shank extending radially inwardly from the platform, and a dovetail region extending radially inwardly from the shank. The axial seal is sized and shaped to be received in the first side channel of a first of the rotary components and the second side channel of a second of the rotary components, such that the axial seal sealingly interfaces with the first and second channels.
    Type: Grant
    Filed: June 1, 2018
    Date of Patent: February 2, 2021
    Assignee: General Electric Company
    Inventors: Jagdish Prasad Tyagi, Sendilkumaran Soundiramourty, Amit Grover, Sunil Rajagopal, Rajesh Mavuri, Andrew Paul Giametta
  • Publication number: 20190162073
    Abstract: A sealing system for a rotary machine is provided. The sealing system includes a pair of circumferentially-adjacent rotary components and an axial seal. Each of the rotary components includes a platform including a first side channel and an opposite second side channel, a shank extending radially inwardly from the platform, and a dovetail region extending radially inwardly from the shank. The axial seal is sized and shaped to be received in the first side channel of a first of the rotary components and the second side channel of a second of the rotary components, such that the axial seal sealingly interfaces with the first and second channels.
    Type: Application
    Filed: June 1, 2018
    Publication date: May 30, 2019
    Inventors: Jagdish Prasad Tyagi, Sendilkumaran Soundiramourty, Amit Grover, Sunil Rajagopal, Rajesh Mavuri, Andrew Paul Giametta
  • Patent number: 9938835
    Abstract: A system for providing cooling of a turbine rotor wheel includes a rotor wheel including a plurality of dovetail slots spaced circumferentially about a peripheral surface of the rotor wheel. Each of the dovetail slots includes a pair of opposite upper slot tangs and a pair of opposite lower slot tangs. The system also includes at least one turbine blade. The turbine blade includes an airfoil, a platform, and a dovetail. The dovetail includes a pair of opposite upper dovetail tangs and a pair of opposite lower dovetail tangs. The dovetail further includes at least one inlet aperture extending longitudinally therethrough. The pair of upper dovetail tangs include a first cooling hole extending therethrough and coupled in flow communication with the at least one inlet aperture.
    Type: Grant
    Filed: October 31, 2013
    Date of Patent: April 10, 2018
    Assignee: General Electric Company
    Inventors: Andrew Paul Giametta, David Richard Johns
  • Patent number: 9890653
    Abstract: The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a shank assembly may include a component shank with a platform including a first slash face. The shank assembly may include a seal pin slot extending into the first slash face, the seal pin slot having a slot length and a depth, and a seal pin disposed in the seal pin slot, the seal pin having a rounded end positioned adjacent to an end of the seal pin slot.
    Type: Grant
    Filed: April 7, 2015
    Date of Patent: February 13, 2018
    Assignee: GENERAL ELECTRIC COMPANY
    Inventors: Omprakash Samudrala, David Richard Johns, Andrew Paul Giametta, Anthony Christopher Marin
  • Patent number: 9845690
    Abstract: This disclosure provides systems and methods for sealing flow path components, such as turbomachine airfoils, with a front-leaded seal. A seal channel is defined between a portion of the suction side surface of a first flow path component and a portion of the pressure side of a second flow path component. A seal is retained within the seal channel formed by the pressure side portion and the suction side portion and the seal channel defines a forward opening through which the seal is inserted during installation.
    Type: Grant
    Filed: June 3, 2016
    Date of Patent: December 19, 2017
    Assignee: General Electric Company
    Inventors: Andrew Paul Giametta, James Tyson Balkcum, III, David Richard Johns, Stephen Paul Wassynger
  • Publication number: 20170350263
    Abstract: This disclosure provides systems and methods for sealing flow path components, such as turbomachine airfoils, with a front-leaded seal. A seal channel is defined between a portion of the suction side surface of a first flow path component and a portion of the pressure side of a second flow path component. A seal is retained within the seal channel formed by the pressure side portion and the suction side portion and the seal channel defines a forward opening through which the seal is inserted during installation.
    Type: Application
    Filed: June 3, 2016
    Publication date: December 7, 2017
    Inventors: Andrew Paul Giametta, James Tyson Balkcum, III, David Richard Johns, Stephen Paul Wassynger
  • Patent number: 9771820
    Abstract: A turbine in a gas turbine engine that includes a stator blade and a rotor blade having a seal formed in a trench cavity. The trench cavity may include an axial gap defined between opposing inboard faces of the stator blade and rotor blade. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an outboard edge and an inboard edge and, defined therebetween, an overhang face; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; and a first axial projection extending from the rotor outboard face toward the stator blade. The stator overhang and the first axial projection of the rotor blade may be configured so to axially overlap.
    Type: Grant
    Filed: December 30, 2014
    Date of Patent: September 26, 2017
    Assignee: General Electric Company
    Inventors: Richard William Johnson, Kevin Richard Kirtley, David Richard Johns, James William Vehr, Andrew Paul Giametta
  • Patent number: 9765699
    Abstract: A gas turbine engine having a turbine that includes a stator blade and a rotor blade having a seal formed in a trench cavity defined therebetween. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an overhang topside, and, opposite the overhang topside, an overhang underside; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; an axial projection extending from the rotor outboard face toward the stator blade so to axially overlap with the stator overhang; and an interior cooling channel extending through the stator overhang to a port formed through the overhang underside. The port may be configured to direct a coolant expelled therefrom toward the axial projection.
    Type: Grant
    Filed: December 30, 2014
    Date of Patent: September 19, 2017
    Assignee: General Electric Company
    Inventors: Kevin Richard Kirtley, David Richard Johns, Andrew Paul Giametta, Richard William Johnson
  • Publication number: 20160298478
    Abstract: The present application and the resultant patent provide improved gas turbine component sealing. In one example embodiment, a shank assembly may include a component shank with a platform including a first slash face. The shank assembly may include a seal pin slot extending into the first slash face, the seal pin slot having a slot length and a depth, and a seal pin disposed in the seal pin slot, the seal pin having a rounded end positioned adjacent to an end of the seal pin slot.
    Type: Application
    Filed: April 7, 2015
    Publication date: October 13, 2016
    Inventors: Omprakash Samudrala, David Richard Johns, Andrew Paul Giametta, Anthony Christopher Marin
  • Publication number: 20160186665
    Abstract: A turbine in a gas turbine engine that includes a stator blade and a rotor blade having a seal formed in a trench cavity. The trench cavity may include an axial gap defined between opposing inboard faces of the stator blade and rotor blade. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an outboard edge and an inboard edge and, defined therebetween, an overhang face; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; and a first axial projection extending from the rotor outboard face toward the stator blade. The stator overhang and the first axial projection of the rotor blade may be configured so to axially overlap.
    Type: Application
    Filed: December 30, 2014
    Publication date: June 30, 2016
    Inventors: Richard William Johnson, Kevin Richard Kirtley, David Richard Johns, James William Vehr, Andrew Paul Giametta
  • Publication number: 20160186664
    Abstract: A gas turbine engine having a turbine that includes a stator blade and a rotor blade having a seal formed in a trench cavity defined therebetween. The seal may include: a stator overhang extending from the stator blade toward the rotor blade so to include an overhang topside, and, opposite the overhang topside, an overhang underside; a rotor outboard face extending radially inboard from a platform edge, the rotor outboard face opposing at least a portion of the overhang face across the axial gap of the trench cavity; an axial projection extending from the rotor outboard face toward the stator blade so to axially overlap with the stator overhang; and an interior cooling channel extending through the stator overhang to a port formed through the overhang underside. The port may be configured to direct a coolant expelled therefrom toward the axial projection.
    Type: Application
    Filed: December 30, 2014
    Publication date: June 30, 2016
    Inventors: Kevin Richard Kirtley, David Richard Johns, Andrew Paul Giametta, Richard William Johnson
  • Patent number: 9359908
    Abstract: An aerodynamic seal assembly for a rotary machine includes multiple sealing segments disposed circumferentially intermediate to a stationary housing and a rotor. Each of the segments includes a shoe plate with a forward load-bearing section and an aft load-bearing section configured to generate an aerodynamic force between the shoe plate and the rotor. The shoe plate includes at least one labyrinth teeth facing the rotor and positioned between the forward load-bearing section and the aft load-bearing section. The sealing segment also includes at least one spring connected to a pedestal located about midway of an axial length of the shoe plate and to a stator interface element. Further, the sealing segment includes a rigid segmented secondary seal attached to the stator interface element at one first end and in contact with the pedestal of the shoe plate at one second end.
    Type: Grant
    Filed: July 8, 2014
    Date of Patent: June 7, 2016
    Assignee: General Electric Company
    Inventors: Rahul Anil Bidkar, Andrew Paul Giametta, Nathan Evan McCurdy Gibson, Nicolas Joseph Cleveland
  • Publication number: 20160146016
    Abstract: A system and method of cooling a radially outer surface of a rotor wheel post of a turbine wheel and a rotor wheel space between a turbine bucket and a rotor wheel post, including a turbine bucket having at least one cooling passage that extends between an inner cooling channel of the turbine bucket and an outer surface of a shank portion of the turbine bucket that directly faces a radially upper surface of the rotor wheel post, and using the cooling passage to direct cooling flow towards the radially upper surface of the rotor wheel post.
    Type: Application
    Filed: November 24, 2014
    Publication date: May 26, 2016
    Inventors: David Richard JOHNS, Michael James FEDOR, Andrew Paul GIAMETTA
  • Patent number: 9267513
    Abstract: According to one aspect of the invention, a method for temperature control of a turbine engine compressor includes directing a fluid from a first region proximate a main flow path in a downstream portion of a structure in a compressor to an upstream portion of the structure, wherein the fluid is cooled as the fluid flows through the upstream portion of the structure. The method further includes directing the fluid from the upstream portion of the structure downstream to a second region of the compressor to cool the second region, wherein the fluid is directed through passages in the upstream and downstream portions of the structure thereby substantially conserving an energy of the fluid within the structure and wherein a pressure of the second region is less than a pressure of the first region.
    Type: Grant
    Filed: June 6, 2012
    Date of Patent: February 23, 2016
    Assignee: General Electric Company
    Inventor: Andrew Paul Giametta
  • Publication number: 20160010480
    Abstract: An aerodynamic seal assembly for a rotary machine includes multiple sealing segments disposed circumferentially intermediate to a stationary housing and a rotor. Each of the segments includes a shoe plate with a forward load-bearing section and an aft load-bearing section configured to generate an aerodynamic force between the shoe plate and the rotor. The shoe plate includes at least one labyrinth teeth facing the rotor and positioned between the forward load-bearing section and the aft load-bearing section. The sealing segment also includes at least one spring connected to a pedestal located about midway of an axial length of the shoe plate and to a stator interface element. Further, the sealing segment includes a rigid segmented secondary seal attached to the stator interface element at one first end and in contact with the pedestal of the shoe plate at one second end.
    Type: Application
    Filed: July 8, 2014
    Publication date: January 14, 2016
    Inventors: Rahul Anil Bidkar, Andrew Paul Giametta, Nathan Evan McCurdy Gibson, Nicolas Joseph Cleveland
  • Patent number: 9121299
    Abstract: The present application provides an axially retractable seal system positioned within a seal slot of a stationary component and adjacent to a rotating component. The axially retractable seal system may include a seal with an upper flange positioned within the seal slot and one more bristles extending towards the rotating component and a spring positioned axially between the upper flange of seal and the seal slot such that the seal is forced into a retracted position.
    Type: Grant
    Filed: June 5, 2013
    Date of Patent: September 1, 2015
    Assignee: General Electric Company
    Inventor: Andrew Paul Giametta
  • Patent number: 9115810
    Abstract: A seal assembly for a rotary machine is provided. The seal assembly includes multiple sealing device segments disposed circumferentially intermediate to a stationary housing and a rotor. Each of the sealing device segments includes a stator interface element, a shoe plate having an extended portion having one or more labyrinth teeth facing the rotor and a load bearing portion, wherein the shoe plate is configured to generate an aerodynamic force between the shoe plate and the rotor. The sealing device segment further includes a secondary seal configured to be in contact with the stator interface element at a radially outer end and configured to be in contact with an elevated nose section of the extended portion of the shoe plate on a radially inner end; and multiple flexible elements attached to the shoe plate and to the stator interface element.
    Type: Grant
    Filed: October 3, 2013
    Date of Patent: August 25, 2015
    Assignee: General Electric Company
    Inventors: Rahul Anil Bidkar, Azam Mihir Thatte, Nathan Evan McCurdy Gibson, Andrew Paul Giametta
  • Publication number: 20150118045
    Abstract: A system for providing cooling of a turbine rotor wheel includes a rotor wheel including a plurality of dovetail slots spaced circumferentially about a peripheral surface of the rotor wheel. Each of the dovetail slots includes a pair of opposite upper slot tangs and a pair of opposite lower slot tangs. The system also includes at least one turbine blade. The turbine blade includes an airfoil, a platform, and a dovetail. The dovetail includes a pair of opposite upper dovetail tangs and a pair of opposite lower dovetail tangs. The dovetail further includes at least one inlet aperture extending longitudinally therethrough. The pair of upper dovetail tangs include a first cooling hole extending therethrough and coupled in flow communication with the at least one inlet aperture.
    Type: Application
    Filed: October 31, 2013
    Publication date: April 30, 2015
    Applicant: General Electric Company
    Inventors: Andrew Paul Giametta, David Richard Johns
  • Patent number: 8956120
    Abstract: An assembly is disclosed that includes a first rotating component and a second rotating component disposed adjacent to the first rotating component. An annular slot may be defined between the first and second rotating components and may include a sealing surface. Additionally, a seal may be disposed within the annular slot and may be configured to be engaged against the sealing surface when the first and second rotating components are rotated. Moreover, the seal may form a non-continuous ring within the annular slot when the seal is engaged against the sealing surface.
    Type: Grant
    Filed: September 8, 2011
    Date of Patent: February 17, 2015
    Assignee: General Electric Company
    Inventor: Andrew Paul Giametta
  • Publication number: 20140361489
    Abstract: The present application provides an axially retractable seal system positioned within a seal slot of a stationary component and adjacent to a rotating component. The axially retractable seal system may include a seal with an upper flange positioned within the seal slot and one more bristles extending towards the rotating component and a spring positioned axially between the upper flange of seal and the seal slot such that the seal is forced into a retracted position.
    Type: Application
    Filed: June 5, 2013
    Publication date: December 11, 2014
    Inventor: Andrew Paul Giametta