Patents by Inventor Robert Walter Coign
Robert Walter Coign 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: 9581036Abstract: Systems and devices configured to seal interfaces/gaps between stationary components of turbines and manipulate a flow of coolant about portions of the turbine during turbine operation are disclosed. In one embodiment, a seal element includes: a first surface shaped to be oriented toward a pressurized cavity of the turbine; a second surface oriented substantially opposite the first surface and shaped to sealingly engage a contact surface of the static components; and a first set of angular features disposed in the second surface, the first set of angular features fluidly connecting the pressurized cavity and the flowpath of the turbine.Type: GrantFiled: May 14, 2013Date of Patent: February 28, 2017Assignee: General Electric CompanyInventors: Dipankar Pal, Robert Walter Coign, Gary Michael Itzel, Kevin Thomas McGovern, Christopher Donald Porter
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Patent number: 9011078Abstract: The present application provides a seal carrier for use about a number of flow orifices of a platform of a turbine nozzle. The seal carrier may include an inner surface facing the platform with the inner surface having a number of slots therein aligning with the flow orifices of the platform and an opposed outer surface with a seal positioned about the outer surface.Type: GrantFiled: January 9, 2012Date of Patent: April 21, 2015Assignee: General Electric CompanyInventors: Aaron Gregory Winn, Robert Walter Coign
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Patent number: 9011079Abstract: The present application provides a compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein. The compartmentalized cooling system may include a turbine nozzle and a cooling baffle. The turbine nozzle may include an airfoil insert and a nozzle outer sidewall. The cooling baffle may include a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit.Type: GrantFiled: January 9, 2012Date of Patent: April 21, 2015Assignee: General Electric CompanyInventors: Robert Walter Coign, Gregory Thomas Foster, Ravichandran Meenakshisundaram, Glen Arthur MacMillan, Aaron Gregory Winn
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Patent number: 8944751Abstract: The present application provides an inner nozzle platform. The inner nozzle platform may include a platform cavity, an impingement plenum positioned within the platform cavity, a retention plate positioned on a first side of the impingement plenum, and a compliant seal positioned on a second side of the impingement plenum.Type: GrantFiled: January 9, 2012Date of Patent: February 3, 2015Assignee: General Electric CompanyInventors: Aaron Gregory Winn, Robert Walter Coign, James Stewart Phillips, Thomas Robbins Tipton, Gregory Thomas Foster, Ravichandran Meenakshisundaram, Niranjan Gokuldas Pai
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Publication number: 20140341720Abstract: Systems and devices configured to seal interfaces/gaps between stationary components of turbines and manipulate a flow of coolant about portions of the turbine during turbine operation are disclosed. In one embodiment, a seal element includes: a first surface shaped to be oriented toward a pressurized cavity of the turbine; a second surface oriented substantially opposite the first surface and shaped to sealingly engage a contact surface of the static components; and a first set of angular features disposed in the second surface, the first set of angular features fluidly connecting the pressurized cavity and the flowpath of the turbine.Type: ApplicationFiled: May 14, 2013Publication date: November 20, 2014Applicant: GENERAL ELECTRIC COMPANYInventors: Dipankar Pal, Robert Walter Coign, Gary Michael Itzel, Kevin Thomas McGovern, Christopher Donald Porter
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Patent number: 8864445Abstract: The present application provides a method of installing an impingement cooling assembly in an inner platform of an airfoil of a turbine nozzle. The method may include the steps of positioning an insert within a cavity of the airfoil, positioning a core exit cover about an opening of the cavity, positioning an impingement plenum within a platform cavity, inserting an unfixed spoolie through an assembly port of the impingement plenum and into an airflow cavity of the insert, and closing the assembly port.Type: GrantFiled: January 9, 2012Date of Patent: October 21, 2014Assignee: General Electric CompanyInventors: Robert Walter Coign, Aaron Gregory Winn
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Patent number: 8851845Abstract: A turbomachine includes a housing, and at least one turbine vane arranged within the housing. The at least one turbine vane includes a platform portion operatively connected to the airfoil portion. A cooling cavity is formed in the platform portion. The cooling cavity includes a first wall, a second wall arranged opposite the first wall, a third wall linking the first and second walls, and a fourth wall linking the first and second walls and positioned opposite the third wall. An impingement cooling plate extends into the cooling cavity and defines an inner cavity portion and an outer cavity portion. The impingement cooling plate including at least one impingement cooling passage that is configured and disposed to guide an impingement cooling flow onto at least one of the first, second, third and fourth walls of the cooling cavity.Type: GrantFiled: November 17, 2010Date of Patent: October 7, 2014Assignee: General Electric CompanyInventors: Robert Alan Brittingham, Robert Walter Coign
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Patent number: 8684683Abstract: A turbine nozzle attachment assembly includes an outer turbine component (a shroud or a turbine shell) formed with a circumferential groove open in a forward-facing axial direction; a nozzle segment including a vane extending between inner and outer bands, the outer band provided with an upstanding annular hook formed with a hook element extending in an aft-facing axial direction and received in the circumferential groove. The upstanding annular hook and hook element are formed with a circumferentially-oriented slot. An anti-rotation block is located in the circumferentially-oriented slot, and an anti-tipping plate having a circumferential width greater than a corresponding circumferential width of the circumferentially-oriented slot substantially covers a forward face of the anti-rotation block. The anti-rotation block and the anti-tipping plate are fastened directly to the outer turbine component.Type: GrantFiled: November 30, 2010Date of Patent: April 1, 2014Assignee: General Electric CompanyInventors: Thomas James Brunt, Robert Walter Coign, Gregory Thomas Foster
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Patent number: 8668445Abstract: A nozzle is disclosed for use in a turbine or compressor. In an embodiment, each of a plurality of vanes is supported by an outer shroud including a plurality of outer shroud segments disposed adjacent to adjoining segments in end-to-end relationship. Each segment includes a hole therethrough, dimensioned to receive a vane extension sleeve. This system may be used in conjunction with a modulated cooling system and may allow for improved removal for overhaul.Type: GrantFiled: October 15, 2010Date of Patent: March 11, 2014Assignee: General Electric CompanyInventors: Andres Jose Garcia Crespo, Robert Walter Coign, David Richard Johns, Gary Charles Liotta
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Publication number: 20130177420Abstract: The present application provides a seal carrier for use about a number of flow orifices of a platform of a turbine nozzle. The seal carrier may include an inner surface facing the platform with the inner surface having a number of slots therein aligning with the flow orifices of the platform and an opposed outer surface with a seal positioned about the outer surface.Type: ApplicationFiled: January 9, 2012Publication date: July 11, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Aaron Gregory Winn, Robert Walter Coign
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Publication number: 20130177447Abstract: The present application provides a method of installing an impingement cooling assembly in an inner platform of an airfoil of a turbine nozzle. The method may include the steps of positioning an insert within a cavity of the airfoil, positioning a core exit cover about an opening of the cavity, positioning an impingement plenum within a platform cavity, inserting an unfixed spoolie through an assembly port of the impingement plenum and into an airflow cavity of the insert, and closing the assembly port.Type: ApplicationFiled: January 9, 2012Publication date: July 11, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Robert Walter Coign, Aaron Gregory Winn
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Publication number: 20130175357Abstract: The present application provides an inner nozzle platform. The inner nozzle platform may include a platform cavity, an impingement plenum positioned within the platform cavity, a retention plate positioned on a first side of the impingement plenum, and a compliant seal positioned on a second side of the impingement plenum.Type: ApplicationFiled: January 9, 2012Publication date: July 11, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Aaron Gregory Winn, Robert Walter Coign, James S. Phillips, Thomas Robbins Tipton, Gregory Thomas Foster, Ravichandran Meenakshisundaram, Niranjan Gokuldas Pai
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Publication number: 20130177384Abstract: The present application provides a compartmentalized cooling system for providing a cooling flow in a turbine with a flow of combustion gases therein. The compartmentalized cooling system may include a turbine nozzle and a cooling baffle. The turbine nozzle may include an airfoil insert and a nozzle outer sidewall. The cooling baffle may include a high pressure cooling passage in communication with the airfoil insert in a first circuit and an impingement plate positioned about the nozzle outer sidewall in a second circuit.Type: ApplicationFiled: January 9, 2012Publication date: July 11, 2013Applicant: GENERAL ELECTRIC COMPANYInventors: Robert Walter Coign, Gregory Thomas Foster, Ravichandran Meenakshisundaram, Glen Arthur MacMillan, Aaron Gregory Winn
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Publication number: 20120121415Abstract: A turbomachine includes a housing, and at least one turbine vane arranged within the housing. The at least one turbine vane includes a platform portion operatively connected to the airfoil portion. A cooling cavity is formed in the platform portion. The cooling cavity includes a first wall, a second wall arranged opposite the first wall, a third wall linking the first and second walls, and a fourth wall linking the first and second walls and positioned opposite the third wall. An impingement cooling plate extends into the cooling cavity and defines an inner cavity portion and an outer cavity portion. The impingement cooling plate including at least one impingement cooling passage that is configured and disposed to guide an impingement cooling flow onto at least one of the first, second, third and fourth walls of the cooling cavity.Type: ApplicationFiled: November 17, 2010Publication date: May 17, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Robert Alan Brittingham, Robert Walter Coign
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Publication number: 20120093632Abstract: A nozzle is disclosed for use in a turbine or compressor. In an embodiment, each of a plurality of vanes is supported by an outer shroud including a plurality of outer shroud segments disposed adjacent to adjoining segments in end-to-end relationship. Each segment includes a hole therethrough, dimensioned to receive a vane extension sleeve. This system may be used in conjunction with a modulated cooling system and may allow for improved removal for overhaul.Type: ApplicationFiled: October 15, 2010Publication date: April 19, 2012Applicant: GENERAL ELECTRIC COMPANYInventors: Andres Jose Garcia Crespo, Robert Walter Coign, David Richard Johns, Gary Charles Liotta
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Patent number: 7160078Abstract: A mechanical arrangement for protection against catastrophic nozzle failures includes a turbine nozzle segment including an inner platform rail, a turbine nozzle inner support ring in part in axial registration with the rail on one side, an inner retainer segment secured to the inner support ring and in part in axially spaced registration relative to the rail on an axial side of the rail opposite from the support ring, a first inclined conical surface on the inner retainer segment, and a second inclined conical surface on the inner platform rail of the turbine nozzle, the second inclined conical surface opposing the first inclined conical surface, so as to bind the inner platform rail to the turbine nozzle between the inner retainer segment and the inner support ring, resulting in a wedge lock that prevents the inner platform from being lost downstream into rotating hardware of the turbine.Type: GrantFiled: September 23, 2004Date of Patent: January 9, 2007Assignee: General Electric CompanyInventors: Robert Walter Coign, David John Humanchuk, Leslie Tucker
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Patent number: 7121787Abstract: The trailing edge region of a nozzle airfoil is provided with a cooling configuration wherein post-impingement cooling air flows between radially spaced ribs defining convective cooling channels into a generally radially extending plenum. Cooling air in the plenum is split between film cooling holes for film cooling the pressure side of the trailing edge region and for flow about downstream pins for pin cooling the downstream regions of the opposite sides of the airfoil. The cooling air exiting the pins is directed through convective channels defined by a second set of radially spaced ribs and through exit apertures on the pressure side of the trailing edge.Type: GrantFiled: April 29, 2004Date of Patent: October 17, 2006Assignee: General Electric CompanyInventors: Curtis John Jacks, Robert Walter Coign, Randall Douglas Gill
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Patent number: 7094026Abstract: Arcuate seal layers conforming with one another are disposed between inner retainer segments and inner rails of nozzle segments of a gas turbine. The layers are secured to the aft axial face of the segments and project radially outwardly to seal against the forward axial faces of the rails. The rear axial faces of the rails have chordal seals for sealing against the forward axial faces of the support rings. The seal layers have radial cuts misaligned with one another in an axial direction to preclude leakage flows through gaps formed by the cuts. Arcuate spacers are staggered circumferentially with the arcuate retainer segments whereby an intermediate pressure plenum is formed between the finger seals and chordal seals.Type: GrantFiled: April 29, 2004Date of Patent: August 22, 2006Assignee: General Electric CompanyInventors: Robert Walter Coign, David John Humanchuk, Gregory Thomas Foster, Kevin Lee Worley
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Patent number: 6739838Abstract: Third stage turbine buckets have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table I wherein X and Y values are in inches and the Z values are non-dimensional values from 0 to 1 convertible to Z distances in inches by multiplying the Z values by the height of the airfoil in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape. The X, Y and Z distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the bucket. The nominal airfoil given by the X, Y and Z distances lies within an envelop of ±0.060 inches in directions normal to the surface of the airfoil.Type: GrantFiled: March 17, 2003Date of Patent: May 25, 2004Assignee: General Electric CompanyInventors: Craig Allen Bielek, Robert Alan Brittingham, Jeff Brian Thompson, Benjamin Arnette Lagrange, Robert Walter Coign
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Patent number: 6736599Abstract: The first stage nozzles have airfoil profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth Table 1. The X and Y values are in inches and the Z value is non-dimensional along the nozzle-stacking axis coincident with a turbine radius and convertible to a Z distance in inches from the turbine axis by multiplying the Z value by the height of the airfoil and adding the root radius to the result. The X and Y distances may be scalable as a function of the same constant or number to provide a scaled up or scaled down airfoil section for the nozzle. The nominal airfoil given by the X, Y and Z distances lies within an envelope of ±0.160 inches.Type: GrantFiled: May 14, 2003Date of Patent: May 18, 2004Assignee: General Electric CompanyInventors: Curtis John Jacks, Craig Allen Bielek, Robert Walter Coign, Randall Gill