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公开(公告)号：US20210348514A1
公开(公告)日：2021-11-11
申请号：US16868165
申请日：2020-05-06
Applicant: General Electric Company
Inventor： Zachary John Snider , Matthew Troy Hafner , Jeffrey Clarence Jones
Abstract: Aspects of the embodiments set forth a sacrificial plug system including a component having a surface and at least one cooling hole in the surface; a sacrificial plug integrally formed with the component and integrally formed in the at least one cooling hole, where the sacrificial plug includes a top portion; a cover portion; and a bottom portion, the bottom portion integrally formed, engaged to, and connected to at least one cooling hole. The sacrificial plug system also includes at least one connective member integrally formed with the bottom portion of the sacrificial plug and integral with an inner wall of each respective at least one cooling hole; each at least one connective member being severable from the respective inner wall when a force is applied to the top portion, thus permitting the sacrificial plug to be removed from the at least one respective cooling hole.
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公开(公告)号：US10815786B2
公开(公告)日：2020-10-27
申请号：US16235079
申请日：2018-12-28
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , James Zhang , Jeffrey Clarence Jones , Peter de Diego
Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil is defined between a pressure face and a laterally opposed suction face, the pressure face and the suction face extending axially between opposite leading and trailing edges and radially between an outboard tip and a connection with a root of the rotor blade. The airfoil may include non-integral portions in which: a base portion of the airfoil is made from a first material; and a top portion of the airfoil is made from a second material. The airfoil may include a dovetail joint connecting the top portion to the base portion. The dovetail joint may include a dovetail extending from the top portion being received within a complementary dovetail groove formed in the base portion.
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公开(公告)号：US20200208526A1
公开(公告)日：2020-07-02
申请号：US16235079
申请日：2018-12-28
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , John McConnell Delvaux , James Zhang , Jeffrey Clarence Jones , Peter de Diego
IPC: F01D5/14
Abstract: A gas turbine that includes a rotor blade that includes an airfoil. The airfoil is defined between a pressure face and a laterally opposed suction face, the pressure face and the suction face extending axially between opposite leading and trailing edges and radially between an outboard tip and a connection with a root of the rotor blade. The airfoil may include non-integral portions in which: a base portion of the airfoil is made from a first material; and a top portion of the airfoil is made from a second material. The airfoil may include a dovetail joint connecting the top portion to the base portion. The dovetail joint may include a dovetail extending from the top portion being received within a complementary dovetail groove formed in the base portion.
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公开(公告)号：US10450868B2
公开(公告)日：2019-10-22
申请号：US15217053
申请日：2016-07-22
Applicant: General Electric Company
Inventor： Jeffrey Clarence Jones , Adam John Fredmonski
Abstract: A turbine rotor blade includes an airfoil body having a leading edge, a trailing edge and a smooth outer surface. A cutout is included within at least one of the leading edge and the trailing edge, the cutout removing a predetermined area of the airfoil body. A coupon is coupled in the cutout to replace the predetermined area of the airfoil body. The coupon includes a first corrugated surface on at least a portion of an outer surface thereof. The coupon allows for the addition of advantageous wake mixing and cooling efficiencies to preexisting blades.
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公开(公告)号：US10443399B2
公开(公告)日：2019-10-15
申请号：US15217062
申请日：2016-07-22
Applicant: General Electric Company
Inventor： Jeffrey Clarence Jones , Adam John Fredmonski
Abstract: A turbine vane includes an airfoil body having a leading edge, a trailing edge and a smooth outer surface. A cutout is included within at least one of the leading edge and the trailing edge, the cutout removing a predetermined area of the airfoil body. A coupon is coupled in the cutout to replace the predetermined area of the airfoil body. The coupon includes a first corrugated surface on at least a portion of an outer surface thereof. The coupon allows for the addition of advantageous wake mixing and cooling efficiencies to preexisting vanes.
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Patent Agency Ranking
公开(公告)号：US11660673B2
公开(公告)日：2023-05-30
申请号：US17073565
申请日：2020-10-19
Applicant: General Electric Company
Inventor： Matthew Troy Hafner , Christopher Donald Porter , Zachary John Snider , Jeffrey Clarence Jones
IPC: B33Y80/00 , B05B12/26 , B22F10/00 , B22F3/10 , B22F3/24 , B22F10/28 , B33Y10/00 , B33Y40/20 , B22F10/47 , F01D5/28
CPC classification number: B22F10/00 , B05B12/26 , B22F3/1007 , B22F3/24 , B22F10/28 , B33Y80/00 , B22F10/47 , B22F2003/1046 , B22F2003/242 , B22F2201/03 , B22F2201/10 , B23P2700/06 , B33Y10/00 , B33Y40/20 , F01D5/288
Abstract: An additively manufactured (AM) object may include a body including an opening in an exterior surface thereof, the opening having a shape and a first area at the exterior surface of the body. A mask may be positioned over the opening. The mask has the shape of the opening and a second area that is larger than the first area so as to overhang the exterior surface of the body about the opening. A plurality of support ligaments couple to the mask and the exterior surface of the body at a location adjacent to the opening to support a portion of the mask. A coating can be applied to the object, and the mask removed. The final AM object includes a plurality of ligament elements extending from the exterior surface of the body and through the coating adjacent the opening, each ligament element at least partially surrounded by the coating.
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27.发明申请公开(公告)号：US20210394413A1
公开(公告)日：2021-12-23
申请号：US17465930
申请日：2021-09-03
Applicant: General Electric Company
Inventor： Jose Troitino Lopez , Eric Lee Bell , Jeffrey Clarence Jones
Abstract: A mold system and method for forming a casting article for investment casting is disclosed. The mold system includes a mold for receiving therein a selected core chosen from a plurality of varied cores. The mold includes a plurality of separable mold portions that are coupleable together to create the mold and configured to form a sacrificial material from a sacrificial material fluid about the selected core. At least one selected separable mold portion of the plurality of separable mold portions includes a set of varied interchangeable versions of the at least one selected separable mold portion. Each varied interchangeable version of the selected separable mold portion is configured to accommodate a different core of the plurality of varied cores. A number of systems for controlling a temperature of the mold are also disclosed.
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公开(公告)号：US20210348513A1
公开(公告)日：2021-11-11
申请号：US16870234
申请日：2020-05-08
Applicant: General Electric Company
Inventor： Jeffrey Clarence Jones , Zachary John Snider , Christopher Donald Porter , Brad Wilson VanTassel
Abstract: A conforming coating mask is used with a turbine component having a plurality of cooling holes. The conforming coating mask includes at least two anchors; a plurality of radial mask strips integrally formed with and extending between each of the at least two anchors; and at least one coating mask securing insert. Each at least one coating mask securing insert integrally formed with a respective at least one radial mask strip; wherein the plurality of radial mask strips align with and cover the plurality of cooling holes.
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公开(公告)号：US20210222565A1
公开(公告)日：2021-07-22
申请号：US16749143
申请日：2020-01-22
Applicant: General Electric Company
Inventor： Zachary John Snider , Brad Wilson VanTassel , Jeffrey Clarence Jones
IPC: F01D5/18
Abstract: A turbine rotor blade is additively manufactured and includes an airfoil body with a radially extending chamber for receiving a coolant flow, a tip end at a radial outer end of the airfoil body, and a shank at a radial inner end of the airfoil body. The radially extending chamber extends at least partially into the shank to define a shank inner surface. An integral impingement cooling structure is within the radially extending chamber. The integral impingement cooling structure allows an exterior surface of a hollow body thereof to be uniformly spaced from the airfoil inner surface despite the curvature of the chamber. The turbine rotor blade has impingement cooling throughout the blade.
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公开(公告)号：US10774656B2
公开(公告)日：2020-09-15
申请号：US15948207
申请日：2018-04-09
Applicant: General Electric Company
Inventor： Gary Michael Itzel , Jeffrey Clarence Jones , James William Vehr
Abstract: An airport having an exterior wall including a plurality of spaced layers for improved cooling and lifetime is disclosed. The airfoil and exterior wall are made by additive manufacturing. The exterior wall includes an exterior layer, an intermediate layer, and an interior layer each separated from adjacent layers by a plurality of standoff members; a plurality of first cooling chambers between the exterior and intermediate layers, the chambers partitioned by a first partitioning wall; a plurality of second cooling chambers between in the intermediate and interior layers, the chambers partitioned by a second partitioning wall; a thermal barrier coating on the exterior layer; a plurality of impingement openings in the intermediate layer and a second plurality of impingement openings in the interior layer; and a plurality of cooling passages in the exterior layer. The exterior layer may also include plateaus on an exterior face through which the cooling passages extend.
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