1
Craig Allen
Craig Allen Bielek, Robert Alan Brittingham, Jeff Brian Thompson, Benjamin Arnette Lagrange, Robert Walter Coign: Airfoil shape for a turbine bucket. General Electric Company, Nixon & Vanderhye, May 25, 2004: US06739838 (37 worldwide citation)

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 ...


2
Craig Allen
Curtis John Jacks, Craig Allen Bielek, Robert Walter Coign, Randall Gill: First stage turbine nozzle airfoil. General Electric Company, Sutherland Asbill & Brennan, May 18, 2004: US06736599 (37 worldwide citation)

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 dista ...


3
Robert Walter Coign, David John Humanchuk, Gregory Thomas Foster, Kevin Lee Worley: System for sealing an inner retainer segment and support ring in a gas turbine and methods therefor. General Electric Company, Nixon & Vanderhye P C, August 22, 2006: US07094026 (30 worldwide citation)

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 ...


4
Curtis John Jacks, Robert Walter Coign, Randall Douglas Gill: Turbine nozzle trailing edge cooling configuration. General Electric Company, Nixon & Vanderhye P C, October 17, 2006: US07121787 (10 worldwide citation)

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 ...


5
Robert Walter Coign, David John Humanchuk, Leslie Tucker: Mechanical solution for rail retention of turbine nozzles. General Electric Company, Nixon & Vanderhye P C, January 9, 2007: US07160078 (3 worldwide citation)

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 an ...


6
Robert Walter Coign, Gregory Thomas Foster, Ravichandran Meenakshisundaram, Glen Arthur MacMillan, Aaron Gregory Winn: Turbine nozzle compartmentalized cooling system. General Electric Company, Sutherland Asbill & Brennan, April 21, 2015: US09011079 (2 worldwide citation)

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 ...


7
Robert Alan Brittingham, Robert Walter Coign: Turbomachine vane and method of cooling a turbomachine vane. General Electric Company, Cantor Colburn, October 7, 2014: US08851845 (1 worldwide citation)

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 ...


8
Thomas James Brunt, Robert Walter Coign, Gregory Thomas Foster: Gas turbine nozzle attachment scheme and removal/installation method. General Electric Company, Nixon & Vanderhye P C, April 1, 2014: US08684683 (1 worldwide citation)

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 ...


9
Aaron Gregory Winn, Robert Walter Coign: Turbine vane seal carrier with slots for cooling and assembly. General Electric Company, Sutherland Asbill & Brennan, April 21, 2015: US09011078

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 ...


10
Robert Walter Coign, Aaron Gregory Winn: Turbine nozzle assembly methods. General Electric Company, Sutherland Asbill & Brennan, October 21, 2014: US08864445

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, posi ...