Patents by Inventor Kevin Leon Bruce
Kevin Leon Bruce 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).
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Patent number: 11092039Abstract: Embodiments of the present disclosure can provide an apparatus for circumferentially separating turbine blades. An apparatus according to the present disclosure may include: a length-adjustable elongate member having opposing first and second ends; a first clasp coupled to the first end of the length-adjustable elongate member, the first clasp shaped to at least partially engage an airfoil profile of a first turbine blade positioned circumferentially adjacent to a dovetail slot, relative to a centerline axis of the turbomachine; and a second clasp coupled to the second end of the length-adjustable elongate member, the second clasp shaped to at least partially engage an airfoil profile of a second turbine blade circumferentially positioned adjacent to the dovetail slot, the first and second turbine blades being circumferentially adjacent to the dovetail slot at opposing circumferential ends thereof.Type: GrantFiled: October 3, 2017Date of Patent: August 17, 2021Assignee: General Electric CompanyInventors: Sandra Beverly Kolvick, Kevin Leon Bruce, Antoine Mastroianni, Danielle Werner, Hubert Karol Wojtowicz
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Patent number: 10760434Abstract: A fixture for transferring turbine blades may include: a first body having an arcuate radially inward surface shaped to contact a rotor of a turbomachine, and a radially outward surface including a plurality of dovetail slots therein shaped to engage the dovetails of the plurality of turbine blades; and a first alignment aperture extending axially through the first body relative to a centerline axis, and positioned for alignment with a portion of the rotor wheel such that the plurality of dovetail slots of the first body are substantially axially aligned with the plurality of dovetail slots of the rotor wheel for at least partial transfer of the turbine blade thereto from the fixture, wherein the dovetails of the plurality of turbine blades are slidably removable from the plurality of dovetail slots of the first body for guided insertion into the plurality of dovetail slots of the rotor wheel.Type: GrantFiled: November 3, 2017Date of Patent: September 1, 2020Assignee: General Electric CompanyInventors: Sandra Beverly Kolvick, Kevin Leon Bruce, Antoine Mastroianni
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Publication number: 20200191003Abstract: Embodiments of the present disclosure can provide an apparatus for circumferentially separating turbine blades. An apparatus according to the present disclosure may include: a length-adjustable elongate member having opposing first and second ends; a first clasp coupled to the first end of the length-adjustable elongate member, the first clasp shaped to at least partially engage an airfoil profile of a first turbine blade positioned circumferentially adjacent to a dovetail slot, relative to a centerline axis of the turbomachine; and a second clasp coupled to the second end of the length-adjustable elongate member, the second clasp shaped to at least partially engage an airfoil profile of a second turbine blade circumferentially positioned adjacent to the dovetail slot, the first and second turbine blades being circumferentially adjacent to the dovetail slot at opposing circumferential ends thereof.Type: ApplicationFiled: October 3, 2017Publication date: June 18, 2020Inventors: Sandra Beverly Kolvick, Kevin Leon Bruce, Antoine Mastroianni, Danielle Werner, Hubert Karol Wojtowicz
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Patent number: 10519783Abstract: A method for modifying an airfoil shroud located at a tip of an airfoil is provided. A locating step locates a reference location in a first end edge. The reference location includes a portion of a fillet. A seal rail extends circumferentially along a radially outer surface of the airfoil shroud. The fillet extends along the radially outer surface and is positioned directly adjacent to the seal rail. A forming step forms a compound relief cut in the fillet without performing a weld process on the airfoil shroud to remove the reference location. The compound relief cut has a first cut having a first radius extending from the seal rail towards the first end edge, and a second cut having a second radius extending from an end of the first cut to the first end edge. Modifying the airfoil shroud is complete following forming the compound relief cut.Type: GrantFiled: December 22, 2016Date of Patent: December 31, 2019Assignee: GENERAL ELECTRIC COMPANYInventors: Richard Gordon Rollings, Kevin Leon Bruce, William Scott Zemitis
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Publication number: 20190101012Abstract: Embodiments of the present disclosure can provide an apparatus for circumferentially separating turbine blades. An apparatus according to the present disclosure may include: a length-adjustable elongate member having opposing first and second ends; a first clasp coupled to the first end of the length-adjustable elongate member, the first clasp shaped to at least partially engage an airfoil profile of a first turbine blade positioned circumferentially adjacent to a dovetail slot, relative to a centerline axis of the turbomachine; and a second clasp coupled to the second end of the length-adjustable elongate member, the second clasp shaped to at least partially engage an airfoil profile of a second turbine blade circumferentially positioned adjacent to the dovetail slot, the first and second turbine blades being circumferentially adjacent to the dovetail slot at opposing circumferential ends thereof.Type: ApplicationFiled: October 3, 2017Publication date: April 4, 2019Inventors: Sandra Beverly Kolvick, Kevin Leon Bruce, Antoine Mastroianni, Danielle Werner, Hubert Karol Wojtowicz
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Patent number: 10125635Abstract: A fixture and method for installing turbine buckets is disclosed. The fixture is adapted for mounting a plurality of turbine buckets with dovetails to a rotor wheel of a turbomachine that is separated from an adjacent rotor wheel by a spacer wheel, the rotor wheel and the spacer wheel each having a plurality of circumferentially aligned dovetail slots, the fixture includes: a turbine bucket holder having a dovetail that is configured to engage with one of the dovetail slots of the spacer wheel. The profile of a bucket holder dovetail slot substantially aligns the dovetail of the turbine bucket with a dovetail slot of the rotor wheel for at least partial transfer of a turbine bucket thereto.Type: GrantFiled: January 12, 2015Date of Patent: November 13, 2018Assignee: General Electric CompanyInventors: Sandra Beverly Kolvick, Kevin Leon Bruce, Matthew Ryan Ferslew, Stuart Craig Hanson, Thomas Michael Merlau, Joshua Michael Oden, Christopher Michael Penny
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Publication number: 20180230817Abstract: A method for modifying an airfoil shroud located at a tip of an airfoil is provided. A locating step locates a reference location in a first end edge. The reference location includes a portion of a fillet. A seal rail extends circumferentially along a radially outer surface of the airfoil shroud. The fillet extends along the radially outer surface and is positioned directly adjacent to the seal rail. A forming step forms a compound relief cut in the fillet without performing a weld process on the airfoil shroud to remove the reference location. The compound relief cut has a first cut having a first radius extending from the seal rail towards the first end edge, and a second cut having a second radius extending from an end of the first cut to the first end edge. Modifying the airfoil shroud is complete following forming the compound relief cut.Type: ApplicationFiled: December 22, 2016Publication date: August 16, 2018Applicant: General Electric CompanyInventors: Richard Gordon Rollings, Kevin Leon Bruce, William Scott Zemitis
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Publication number: 20180163549Abstract: A fixture for transferring turbine blades may include: a first body having an arcuate radially inward surface shaped to contact a rotor of a turbomachine, and a radially outward surface including a plurality of dovetail slots therein shaped to engage the dovetails of the plurality of turbine blades; and a first alignment aperture extending axially through the first body relative to a centerline axis, and positioned for alignment with a portion of the rotor wheel such that the plurality of dovetail slots of the first body are substantially axially aligned with the plurality of dovetail slots of the rotor wheel for at least partial transfer of the turbine blade thereto from the fixture, wherein the dovetails of the plurality of turbine blades are slidably removable from the plurality of dovetail slots of the first body for guided insertion into the plurality of dovetail slots of the rotor wheel.Type: ApplicationFiled: November 3, 2017Publication date: June 14, 2018Inventors: Sandra Beverly KOLVICK, Kevin Leon BRUCE, Antoine MASTROIANNI
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Patent number: 9574450Abstract: A mid-span shroud assembly for a turbine blade airfoil includes a pressure side shroud body which is associated with a pressure side wall of the airfoil and a suction side shroud body which is associated with a suction side wall of the airfoil. At least one of the pressure side shroud body and the suction side shroud body defines a coupling spar which is formed to extend at least partially through a bore hole defined within the airfoil of the turbine blade.Type: GrantFiled: August 7, 2014Date of Patent: February 21, 2017Assignee: GENERAL ELECTRIC COMPANYInventors: David Randolph Spracher, Kevin Leon Bruce, John Wesley Harris, Jr., Daryl R. Collins, William Scott Zemitis
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Publication number: 20160201556Abstract: A fixture and method for installing turbine buckets is disclosed. The fixture is adapted for mounting a plurality of turbine buckets with dovetails to a rotor wheel of a turbomachine that is separated from an adjacent rotor wheel by a spacer wheel, the rotor wheel and the spacer wheel each having a plurality of circumferentially aligned dovetail slots, the fixture includes: a turbine bucket holder having a dovetail that is configured to engage with one of the dovetail slots of the spacer wheel. The profile of a bucket holder dovetail slot substantially aligns the dovetail of the turbine bucket with a dovetail slot of the rotor wheel for at least partial transfer of a turbine bucket thereto.Type: ApplicationFiled: January 12, 2015Publication date: July 14, 2016Inventors: Sandra Beverly Kolvick, Kevin Leon Bruce, Matthew Ryan Ferslew, Stuart Craig Hanson, Thomas Michael Merlau, Joshua Michael Oden, Christopher Michael Penny
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Publication number: 20160040537Abstract: A mid-span shroud assembly for a turbine blade includes a pressure side shroud body defining a spar pocket and a fastener hole and a suction side shroud body defining a spar pocket and a fastener hole. The mid-span shroud assembly further includes a spar having a first end portion which extends within the spar pocket of the pressure side shroud body and a second end portion which extends within the spar pocket of the suction side shroud body. The spar is formed to extend through a bore hole of the turbine blade. A fastener is formed to extend through the fastener hole of the pressure side shroud body, a fastener orifice of the turbine blade and the fastener hole of the suction side shroud body to provide a clamping force to hold the pressure side and suction side shroud bodies against the airfoil.Type: ApplicationFiled: August 7, 2014Publication date: February 11, 2016Inventors: David Randolph Spracher, Kevin Leon Bruce, John Wesley Harris, JR., Brian Denver Potter, William Scott Zemitis
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Publication number: 20160040535Abstract: A mid-span shroud assembly for a turbine blade airfoil includes a pressure side shroud body which is associated with a pressure side wall of the airfoil and a suction side shroud body which is associated with a suction side wall of the airfoil. At least one of the pressure side shroud body and the suction side shroud body defines a coupling spar which is formed to extend at least partially through a bore hole defined within the airfoil of the turbine blade.Type: ApplicationFiled: August 7, 2014Publication date: February 11, 2016Inventors: David Randolph Spracher, Kevin Leon Bruce, John Wesley Harris, JR., Daryl R. Collins, William Scott Zemitis
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Patent number: 9175573Abstract: A dovetail attachment seal for a turbomachine includes an outer seal member having a first end that extends to a second end through an intermediate portion, and at least one articulating element encapsulated, at least in part, by the outer seal member at one of the first and second ends. The at least one articulating element is slidingly disposed within the outer seal member.Type: GrantFiled: November 28, 2012Date of Patent: November 3, 2015Assignee: General Electric CompanyInventors: Ronald Ralph Cairo, Kevin Leon Bruce
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Patent number: 8967957Abstract: A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing.Type: GrantFiled: November 3, 2011Date of Patent: March 3, 2015Assignee: General Electric CompanyInventors: Gary Michael Itzel, Christopher Michael Penny, Aaron Ezekiel Smith, Kevin Leon Bruce
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Patent number: 8905717Abstract: A retention system for a plurality of turbine buckets located in respective mating slots in a turbine rotor wheel includes a plurality of first circumferentially-oriented retention slots formed in outer peripheral portions of the turbine wheel; a plurality of second circumferentially-oriented retention slots formed in wheel mounting portions of said buckets, the first and second circumferentially-oriented retention slots aligned to form an annular lockwire retention slot; and a lockwire located within the annular lockwire retention slot. A first surface feature on one or both of the turbine rotor wheel and one or more of said plurality of turbine buckets is adapted to engage a second surface feature on the lockwire for preventing rotation of the lockwire beyond predetermined limits.Type: GrantFiled: October 6, 2010Date of Patent: December 9, 2014Assignee: General Electric CompanyInventors: Felipe Roman-Morales, Ariel Caesar Prepena Jacala, Liming Xu, Melbourne James Myers, Kevin Leon Bruce, Luke John Ammann
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Patent number: 8900424Abstract: An electrode for an electrochemical machining process is provided. The electrode includes an electrically conductive member defining at least one passage and an insulating coating partially covering a side surface of the electrically conductive member. The insulating coating does not cover at least one of first and second exposed sections of the electrically conductive member, where the first and second exposed sections are separated by approximately 180 degrees and extend substantially along a longitudinal axis of the electrically conductive member. The insulating coating also does not cover an exposed front end of the electrically conductive member. An electrochemical machining method is also provided, for forming a non-circular hole in a workpiece using the electrode.Type: GrantFiled: June 8, 2012Date of Patent: December 2, 2014Assignee: General Electric CompanyInventors: Bin Wei, Kevin Leon Bruce
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Publication number: 20140144157Abstract: A dovetail attachment seal for a turbomachine includes an outer seal member having a first end that extends to a second end through an intermediate portion, and at least one articulating element encapsulated, at least in part, by the outer seal member at one of the first and second ends. The at least one articulating element is slidingly disposed within the outer seal member.Type: ApplicationFiled: November 28, 2012Publication date: May 29, 2014Applicant: General Electric CompanyInventors: Ronald Ralph Cairo, Kevin Leon Bruce
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Patent number: 8727724Abstract: A turbine bucket is provided and includes a shank interconnectable with a rotor and formed to accommodate coolant therein and an airfoil blade coupled to a radially outward portion of the shank and including a body formed to define a substantially radially extending cooling hole therein, which is disposed to be solely receptive of the coolant accommodated within the shank for removing heat from the body, the cooling hole being further defined as having a substantially non-circular cross-sectional shape at a predefined radial position of the body.Type: GrantFiled: April 12, 2010Date of Patent: May 20, 2014Assignee: General Electric CompanyInventors: Kevin Leon Bruce, Matthew Robert Piersall
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Publication number: 20130202439Abstract: A rotating assembly for a turbine assembly includes an airfoil extending radially outward from, and rotatable about, an axial centerline. Also included is a tip shroud integrally connected proximate a radially outer tip of the airfoil. Further included is a substrate operably coupled to the tip shroud. Yet further included is at least one hard face interface member secured to the substrate.Type: ApplicationFiled: February 8, 2012Publication date: August 8, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Kevin Leon Bruce, Ronald Ralph Cairo, Matthew Robert Piersall, Richard Gordon Rollings
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Publication number: 20130115096Abstract: A rotating airfoil component equipped with one or more angel wings that inhibit the ingress of a hot working fluid into interior regions of a turbomachine in which the component is installed. The component includes an airfoil and a feature for mounting the component to enable rotation of the component within the turbomachine. An angel wing projects from the component to have a first surface facing the airfoil, an oppositely-disposed second surface facing the mounting feature, and at least one lateral surface therebetween. A thermal-insulating coating system is present on the first surface to inhibit heat transfer from the working fluid to the angel wing but not on the second or lateral surfaces so as not to inhibit heat transfer from the second and lateral surfaces of the angel wing.Type: ApplicationFiled: November 3, 2011Publication date: May 9, 2013Applicant: General Electric CompanyInventors: Gary Michael Itzel, Christopher Michael Penny, Aaron Ezekiel Smith, Kevin Leon Bruce