Patents by Inventor Gulcharan Singh Brainch
Gulcharan Singh Brainch 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: 11313235Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a metering section defining a metering diameter and a diffusing section that defines a hooded length.Type: GrantFiled: March 17, 2015Date of Patent: April 26, 2022Inventors: Ronald Scott Bunker, Frederick Alan Buck, Robert David Briggs, Gulcharan Singh Brainch, Kevin Robert Feldmann
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Patent number: 10690055Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.Type: GrantFiled: May 27, 2015Date of Patent: June 23, 2020Assignee: General Electric CompanyInventors: Curtis Walton Stover, Jonathan Michael Rausch, Satoshi Atsuchi, Gulcharan Singh Brainch, Robert David Briggs, Ronald Scott Bunker, Ambarish Jayant Kulkarni, Michael Alan Meade, Byron Andrew Pritchard, Robert Proctor
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Patent number: 10443407Abstract: An apparatus for a gas turbine engine can include an airfoil having an interior. The interior can be separated into one or more cooling air channels extending in a span-wise direction. An accelerator insert can be placed in one or more cooling air channels to define a reduced cross-sectional area within the cooling air channel to accelerate an airflow passing through the cooling air channel.Type: GrantFiled: February 15, 2016Date of Patent: October 15, 2019Assignee: General Electric CompanyInventors: Robert David Briggs, Shawn Michael Pearson, Andrew David Kemp, Gulcharan Singh Brainch
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Patent number: 10364684Abstract: A structure for disrupting the flow of a fluid comprises and a second lateral wall spaced apart from one another, yet joined, by a floor and a ceiling; and, (b) a vorticor pin extending in a direction parallel to an X-axis, the vorticor pin concurrently rising above and extending away from the floor to a height, in a direction parallel to a Y-axis, the vorticor pin comprising: (i) a front surface extending incompletely between the first lateral wall and the second lateral wall, the front surface extending above the floor and having an arcuate portion that is transverse with respect to a Z-axis, which is perpendicular to the X-axis and the Y-axis, and (ii) a rear surface extending between the first lateral wall and the second lateral wall, the rear surface extending between the front surface and the floor, the rear surface having an inclining section that tapers in height, taken parallel to the Y-axis, in a direction parallel to the Z-axis.Type: GrantFiled: May 14, 2015Date of Patent: July 30, 2019Assignee: General Electric CompanyInventors: Jason Randolph Allen, Robert David Briggs, Gulcharan Singh Brainch, Curtis Walton Stover
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Patent number: 10280785Abstract: A shroud assembly for a turbine section of a turbine engine includes a shroud plate in thermal communication with a hot combustion gas flow and a baffle overlying the shroud plate to define a region. One or more shaped cooling features are located along the region such that a cooling fluid flow passing through the region encounters the shaped cooling features to increase the turbulence of the cooling fluid flow.Type: GrantFiled: October 9, 2015Date of Patent: May 7, 2019Assignee: General Electric CompanyInventors: Robert David Briggs, Gulcharan Singh Brainch, Curtis Walton Stover
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Publication number: 20170234145Abstract: An apparatus for a gas turbine engine can include an airfoil having an interior. The interior can be separated into one or more cooling air channels extending in a span-wise direction. An accelerator insert can be placed in one or more cooling air channels to define a reduced cross-sectional area within the cooling air channel to accelerate an airflow passing through the cooling air channel.Type: ApplicationFiled: February 15, 2016Publication date: August 17, 2017Inventors: Robert David Briggs, Shawn Michael Pearson, Andrew David Kemp, Gulcharan Singh Brainch
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Publication number: 20170101932Abstract: Gas turbine engine components are provided which utilize an insert to provide cooling air along a cooled surface of an engine component. The insert provides cooling holes or apertures which face the cool side surface of the engine component and direct cooling air onto that cool side surface. The apertures may be formed in arrays and directed at an oblique or a non-orthogonal angle to the surface of the insert and may be at an angle to the surface of the engine component being cooled. An engine component assembly is provided with counterflow impingement cooling, comprising an engine component cooling surface having a cooling fluid flow path on one side and a second component adjacent to the first component. The second component may have a plurality of openings forming an array wherein the openings extend through the second component at a non-orthogonal angle to the surface of the second component.Type: ApplicationFiled: May 27, 2015Publication date: April 13, 2017Applicant: General Electric CompanyInventors: Curtis Walton STOVER, Jonathan Michael RAUSCH, Satoshi ATSUCHI, Gulcharan Singh BRAINCH, Robert David BRIGGS, Ronald Scott BUNKER, Ambarish Jayant KULKARNI, Michael Alan MEADE, Byron Andrew PRITCHARD, Robert PROCTOR
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Publication number: 20160273363Abstract: An engine component for a gas turbine engine includes a film-cooled substrate having a hot surface facing hot combustion gas and a cooling surface facing a cooling fluid flow. The substrate includes one or more film holes that have a metering section defining a metering diameter and a diffusing section that defines a hooded length.Type: ApplicationFiled: March 17, 2015Publication date: September 22, 2016Inventors: Ronald Scott BUNKER, Frederick Alan BUCK, Robert David BRIGGS, Gulcharan Singh BRAINCH, Kevin Robert FELDMANN
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Publication number: 20160186605Abstract: A shroud assembly for a turbine section of a turbine engine includes a shroud plate in thermal communication with a hot combustion gas flow and a baffle overlying the shroud plate to define a region. One or more shaped cooling features are located along the region such that a cooling fluid flow passing through the region encounters the shaped cooling features to increase the turbulence of the cooling fluid flow.Type: ApplicationFiled: October 9, 2015Publication date: June 30, 2016Inventors: Robert David BRIGGS, Gulcharan Singh BRAINCH, Curtis Walton STOVER
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Publication number: 20150345305Abstract: A structure for disrupting the flow of a fluid, the structure comprising: (a) a first lateral wall and a second lateral wall spaced apart from one another, yet joined, by a floor and a ceiling; and, (b) a vorticor pin extending incompletely between the first lateral wall and the second lateral wall in a direction parallel to an X-axis, the vorticor pin concurrently rising above and extending away from the floor to a height, in a direction parallel to a Y-axis, to provide a gap between the vorticor pin and the ceiling, the vorticor pin comprising: (i) a front surface extending incompletely between the first lateral wall and the second lateral wall, the front surface extending above the floor and having an arcuate portion that is transverse with respect to a Z-axis, which is perpendicular to the X-axis and the Y-axis, and (ii) a rear surface extending between the first lateral wall and the second lateral wall, the rear surface extending between the front surface and the floor, the rear surface having an incliniType: ApplicationFiled: May 14, 2015Publication date: December 3, 2015Inventors: Jason Randolph Allen, Robert David Briggs, Gulcharan Singh Brainch, Curtis Walton Stover
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Patent number: 6923616Abstract: A method facilitates fabricating a rotor assembly for a gas turbine engine. The method comprises providing a plurality of rotor blades that each include an airfoil, a dovetail, a shank, and a platform, wherein the platform extends between the shank and the airfoil, and wherein the dovetail extends outwardly from the shank, and forming a cooling circuit within a portion of the shank to supply cooling air to the rotor blade for supplying cooling air to the rotor blade for impingement cooling a portion of the rotor blade and for supplying cooling air to the rotor blade for purging a cavity defined downstream from the rotor blade.Type: GrantFiled: September 2, 2003Date of Patent: August 2, 2005Assignee: General Electric CompanyInventors: Ronald Eugene McRae, Jr., Sean Robert Keith, Gulcharan Singh Brainch
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Patent number: 6514037Abstract: A cooled turbine element including an airfoil and a flowpath boundary member extending laterally from either an inboard end or an outboard end of the airfoil. The member has a flowpath face and an outside face which is cooler than said flowpath face creating a tendency for the member to deflect in a direction away from the flowpath face and causing a thermally induced tensile radial stress in a region of the trailing edge of the airfoil. The element has an interior cooling passage and at least one cooling hole extending from the interior cooling passage to an opening located in an area upstream from the stressed region of the trailing edge to cool the area so the airfoil thermally deflects to a shape corresponding to that of the boundary member thereby lowering the thermally induced tensile radial stress in the airfoil at the trailing edge thereof.Type: GrantFiled: September 26, 2001Date of Patent: February 4, 2003Assignee: General Electric CompanyInventors: Michael Joseph Danowski, Gulcharan Singh Brainch