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公开(公告)号：US10202867B2
公开(公告)日：2019-02-12
申请号：US14777331
申请日：2014-03-14
Applicant: General Electric Company
Inventor： John Joseph Rahaim , Daniel John Fusinato , Scott David Hunter , Joel Francis Kirk , Michael Robert Melzak , Curtis Walton Stover
Abstract: A flow transfer apparatus for transferring cooling flow from a primary gas flowpath to a turbine rotor. The apparatus includes a first supply plenum communicating with the primary gas flowpath and first inducers, the first inducers configured to accelerate a first fluid flow from the first supply plenum and discharge it toward the rotor with a tangential velocity; a second supply plenum communicating with the primary gas flowpath and second inducers, the second inducers configured to accelerate a second fluid flow from the second supply plenum towards the rotor with a tangential velocity; and a cooling modulation valve operable to selectively permit or block the second fluid flow from the primary gas flowpath to the second supply plenum. The valve includes a flow control structure disposed in the primary gas flowpath and an actuation structure extending to a location radially outside of a casing defining the primary gas flowpath.
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公开(公告)号：US20240369072A1
公开(公告)日：2024-11-07
申请号：US18142745
申请日：2023-05-03
Applicant: General Electric Company
Inventor： Vaishnav Raghuvaran , Bhaskar Nanda Mondal , Thomas Ory Moniz , Atanu Saha , Vaibhav Deshmukh , Curtis Walton Stover , Andrew Mark Del Donno
Abstract: Structures for reducing forward loads in compressors are described. compressor includes inner and outer circumferential support structures positioned concentrically around a central axis, and an aft-most stage including a vane extending radially inward from the outer circumferential support structure. An axial length of the aft-most stage is defined by a spacer arm of the inner circumferential support structure. The vane includes a root, a tip, and a trailing edge extending between the root and the tip. A ratio of a first radial distance between a first point located at an intersection of the tip of the vane and the trailing edge to a radially inner wall of the spacer arm of the inner circumferential support structure to a second radial distance between the first point and a second point located at an intersection of the root of the vane and the trailing edge is between 0.95 and 4.5.
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公开(公告)号：US10690055B2
公开(公告)日：2020-06-23
申请号：US15314490
申请日：2015-05-27
Applicant: General Electric Company
Inventor： 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
Abstract: 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.
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公开(公告)号：US20180038243A1
公开(公告)日：2018-02-08
申请号：US15229466
申请日：2016-08-05
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Jeffrey Douglas Rambo , Andrew Martin , Curtis Walton Stover , Jared Matthew Wolfe , Mohammed El Hacin Sennoun
CPC classification number: F01D25/14 , F01D17/105 , F01D17/145 , F01D17/162 , F01D25/12 , F02C6/08 , F02C7/14 , F02C7/18 , F02K3/06 , F02K3/115 , F04D19/002 , F04D29/542 , F05D2220/32 , F05D2260/213 , F05D2260/601 , F05D2260/98 , Y02T50/676
Abstract: A heat exchanger assembly for a gas turbine engine that includes an outer engine case. The heat exchanger assembly includes at least one cooling channel, the at least one cooling channel is configured to receive a flow of fluid to be cooled. At least one first coolant flow duct that is configured to receive a flow of a first coolant, wherein the at least one cooling channel is disposed between a first inlet and a first outlet. The heat exchanger assembly further include at least one second coolant flow duct that is configured to receive a flow of a second coolant, wherein the at least one cooling channel is disposed between a second inlet and a second outlet.
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公开(公告)号：US11280215B2
公开(公告)日：2022-03-22
申请号：US15522854
申请日：2015-10-28
Applicant: General Electric Company
Inventor： Robert Frederick Bergholz , Jason Randolph Allen , Robert David Briggs , Kevin Robert Feldmann , Curtis Walton Stover , Zachary Daniel Webster , Fernando Reiter
IPC: F01D25/12 , F23R3/00 , F01D5/18 , F23R3/06 , F01D9/04 , F01D11/08 , F02C3/04 , F02C7/18 , F23R3/04
Abstract: An engine component assembly includes a first engine component having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface with at least one cavity. A second engine component is spaced from the cooling surface, and includes at least one cooling aperture. The cooling aperture is arranged such that cooling fluid impinges on the cooling surface at an angle.
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Patent Agency Ranking
公开(公告)号：US10364684B2
公开(公告)日：2019-07-30
申请号：US14712287
申请日：2015-05-14
Applicant: General Electric Company
Inventor： Jason Randolph Allen , Robert David Briggs , Gulcharan Singh Brainch , Curtis Walton Stover
Abstract: 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.
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公开(公告)号：US20170107852A1
公开(公告)日：2017-04-20
申请号：US14884152
申请日：2015-10-15
Applicant: General Electric Company
CPC classification number: F01D25/14 , F01D9/04 , F01D11/24 , F01D25/12 , F01D25/28 , F01D25/32 , F02C7/12 , F05D2240/11 , F05D2260/607 , Y02T50/675
Abstract: A shroud assembly for a gas turbine engine includes a shroud, hanger, and a hanger support mounted adjacent to a plurality of blades. The hanger can have an interior chamber defining a cooling circuit with a particle separator located within the interior chamber. The particle separator can have an inlet for accepting a flow of cooling fluid, such that a the flow of cooling fluid separates into a major flow and a minor flow carrying particles or particulate matter along the minor flow into a particle collector comprising at least a portion of the particle separator. Particles become constrained to the minor flow and pass into the particle collector, while the major flow is separated into the remaining area of the interior chamber to remove the particles from the flow of cooling fluid passing into the interior chamber.
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公开(公告)号：US20150345305A1
公开(公告)日：2015-12-03
申请号：US14712287
申请日：2015-05-14
Applicant: General Electric Company
Inventor： Jason Randolph Allen , Robert David Briggs , Gulcharan Singh Brainch , Curtis Walton Stover
CPC classification number: F01D5/188 , F01D5/187 , F05D2250/14 , F05D2250/16 , F05D2250/23 , F05D2250/231 , F05D2250/292 , F05D2260/2212 , F23R2900/03045 , F28F1/40 , F28F3/022 , F28F13/02 , F28F13/12 , Y02T50/676
Abstract: 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 inclining section that tapers in height, taken parallel to the Y-axis, in a direction parallel to the Z-axis.
Abstract translation: 一种用于破坏流体流动的结构，所述结构包括：（a）第一侧壁和第二侧壁，所述第一侧壁和第二侧壁彼此间隔开，但由地板和天花板连接; 以及（b）在平行于X轴的方向上在第一侧壁和第二侧壁之间不完全延伸的激素针，所述vorticor针同时上升并且从地板延伸到高度，平行于 以提供在所述vorticor针和天花板之间的间隙，所述vorticor针包括：（i）在所述第一侧壁和所述第二侧壁之间不完全延伸的前表面，所述前表面延伸到所述底板之上， 具有相对于垂直于X轴和Y轴的Z轴横向的弓形部分，以及（ii）在第一侧壁和第二侧壁之间延伸的后表面，后部 所述表面在所述前表面和所述地板之间延伸，所述后表面具有与所述Z轴平行的方向平行于所述Y轴的高度渐缩的倾斜部。
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公开(公告)号：US12247580B2
公开(公告)日：2025-03-11
申请号：US18142745
申请日：2023-05-03
Applicant: General Electric Company
Inventor： Vaishnav Raghuvaran , Bhaskar Nanda Mondal , Thomas Ory Moniz , Atanu Saha , Vaibhav Deshmukh , Curtis Walton Stover , Andrew Mark Del Donno
Abstract: Structures for reducing forward loads in compressors are described. A compressor includes inner and outer circumferential support structures positioned concentrically around a central axis, and an aft-most stage including a vane extending radially inward from the outer circumferential support structure. An axial length of the aft-most stage is defined by a spacer arm of the inner circumferential support structure. The vane includes a root, a tip, and a trailing edge extending between the root and the tip. A ratio of a first radial distance between a first point located at an intersection of the tip of the vane and the trailing edge to a radially inner wall of the spacer arm of the inner circumferential support structure to a second radial distance between the first point and a second point located at an intersection of the root of the vane and the trailing edge is between 0.95 and 4.5.
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公开(公告)号：US20220170383A1
公开(公告)日：2022-06-02
申请号：US17673426
申请日：2022-02-16
Applicant: GENERAL ELECTRIC COMPANY
Inventor： Robert Frederick Bergholz , Jason Randolph Allen , Robert David Briggs , Kevin Robert Feldmann , Curtis Walton Stover , Zachary Daniel Webster , Fernando Reiter
IPC: F01D25/12 , F23R3/00 , F01D5/18 , F23R3/06 , F01D9/04 , F01D11/08 , F02C3/04 , F02C7/18 , F23R3/04
Abstract: An engine component assembly with a first substrate having a hot surface in thermal communication with a hot combustion gas flow and a cooling surface, with the cooling surface being different than the hot surface, a second substrate having a first surface in fluid communication with a cooling fluid supply and a second surface, different from the first surface, facing and spaced from the cooling surface to define at least one interior cavity. At least one cavity is provided within the first substrate defining a cavity surface where at least a portion of the cavity surface is directly opposite the second surface. At least one cooling aperture extending through the second substrate from the first surface to the second surface, and defining a streamline along which a cooling fluid passes from the cooling fluid supply to the at least one interior cavity.
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