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Robert Coign Phones & Addresses

  • 53 Viola Dr, East Hampton, CT 06424
  • 175 Kingsland Way, Piedmont, SC 29673
  • 1115 Highway 51, Madison, MS 39110
  • 243 Highway 51, Madison, MS 39110
  • Greenville, SC
  • Jupiter, FL
  • Palm City, FL

Publications

Us Patents

Airfoil Shape For A Turbine Bucket

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US Patent:
6739838, May 25, 2004
Filed:
Mar 17, 2003
Appl. No.:
10/388476
Inventors:
Craig Allen Bielek - Simpsonville SC
Robert Alan Brittingham - Piedmont SC
Jeff Brian Thompson - Jackson TN
Benjamin Arnette Lagrange - Simpsonville SC
Robert Walter Coign - Piedmont SC
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 514
US Classification:
416223A, 416243, 416DIG 5
Abstract:
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.

Internal Core Profile For A Turbine Nozzle Airfoil

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US Patent:
6994520, Feb 7, 2006
Filed:
May 26, 2004
Appl. No.:
10/853240
Inventors:
David John Humanchuk - Simpsonville SC,
Curtis John Jacks - Greenville SC,
Robert W. Coign - Piedmont SC,
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 9/06
US Classification:
415191, 4152082, 4152101, 415115
Abstract:
First stage nozzle airfoils have internal core profiles substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in Table I wherein X, Y and Z values are in inches. The X and Y values are distances which, when connected by smooth continuing arcs, define internal core profile sections at each radial distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete internal core profile. 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 internal core profile. The nominal internal core profile given by the X, Y and Z distances lies within an envelope of ±0. 030 inches in directions normal to any internal core surface location.

System For Sealing An Inner Retainer Segment And Support Ring In A Gas Turbine And Methods Therefor

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US Patent:
7094026, Aug 22, 2006
Filed:
Apr 29, 2004
Appl. No.:
10/834116
Inventors:
Robert Walter Coign - Piedmont SC,
David John Humanchuk - Simpsonville SC,
Gregory Thomas Foster - Greer SC,
Kevin Lee Worley - Easley SC,
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 9/04
US Classification:
415189, 4152092, 4152093
Abstract:
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.

Turbine Nozzle Trailing Edge Cooling Configuration

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US Patent:
7121787, Oct 17, 2006
Filed:
Apr 29, 2004
Appl. No.:
10/834055
Inventors:
Curtis John Jacks - Greenville SC,
Robert Walter Coign - Piedmont SC,
Randall Douglas Gill - Greenville SC,
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 9/02
F01D 5/18
US Classification:
415115, 416 97 R
Abstract:
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.

Mechanical Solution For Rail Retention Of Turbine Nozzles

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US Patent:
7160078, Jan 9, 2007
Filed:
Sep 23, 2004
Appl. No.:
10/947450
Inventors:
Robert Walter Coign - Piedmont SC,
David John Humanchuk - Simpsonville SC,
Leslie Tucker - Tequesta FL,
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 21/00
F01D 9/04
US Classification:
415 9, 415138, 415139, 415189, 4152092, 4152094, 2988922
Abstract:
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.

Ceramic Matrix Composite Shroud Attachment System

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US Patent:
8647055, Feb 11, 2014
Filed:
Apr 18, 2011
Appl. No.:
13/064815
Inventors:
Gregory Thomas Foster - Greer SC,
Robert Coign - Piedmont SC,
Kevin McGovern - Simpsonville SC,
David Weber - Simpsonville SC,
Assignee:
General Electric Company - Schenectady NY
International Classification:
F01D 25/28
US Classification:
415139, 4151731
Abstract:
Shroud assembly for use in a turbine, having an outer shroud having a side proximate to flow of operative fluid of the turbine, the side having a boss and an outer shroud aperture extending through the boss. An inner shroud is located between the side of the outer shroud proximate to the flow of operative fluid and the operative fluid flow of the turbine, the inner shroud having an inner shroud aperture which is dimensioned to fit over the boss.

Variable Turbine Nozzle System

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US Patent:
2012009, Apr 19, 2012
Filed:
Oct 15, 2010
Appl. No.:
12/905569
Inventors:
Andres Jose Garcia Crespo - Greenville SC,
Robert Walter Coign - Piedmont SC,
David Richard Johns - Simpsonville SC,
Gary Charles Liotta - Greenville SC,
Assignee:
GENERAL ELECTRIC COMPANY - Schenectady NY
International Classification:
F03B 1/04
US Classification:
415151
Abstract:
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.

Turbomachine Vane And Method Of Cooling A Turbomachine Vane

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US Patent:
2012012, May 17, 2012
Filed:
Nov 17, 2010
Appl. No.:
12/948361
Inventors:
Robert Alan Brittingham - Piedmont SC,
Robert Walter Coign - Piedmont SC,
Assignee:
GENERAL ELECTRIC COMPANY - Schenectady NY
International Classification:
F01D 5/08
US Classification:
416 95
Abstract:
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.
Robert W Coign from East Hampton, CT, age ~55 Get Report