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公开(公告)号：US11299993B2
公开(公告)日：2022-04-12
申请号：US16665964
申请日：2019-10-28
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Donald Mittendorf , Krista Amato , Nicole Conklin , Brent Ludwig , Mark Morris , Ryon Stanley , Donald Tilman , Heemann Yun
IPC: F01D5/28
Abstract: A turbomachine includes a shroud and a rotor, which includes first and second blades. A first blade tip and a second blade tip respectively include a base and a first layer. The second blade tip also includes an abrasive second layer layered over the respective first layer. The first layer has a lower material hardness than the shroud. The second layer has a lower thermal stability than the shroud and the first layer. The rotor performs a grind operation and, subsequently, a post-grind operation. The second layer, in the grind operation, contacts and removes material from the shroud, and wears away, thereby revealing the first layer of the second blade tip for the post-grind operation. The first layer of the first blade tip is spaced apart with at least some radial clearance from the shroud in the grind and post-grind operations.
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公开(公告)号：US20200040745A1
公开(公告)日：2020-02-06
申请号：US16051560
申请日：2018-08-01
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Brent Ludwig , Don Mittendorf , David R. Waldman , Malak Fouad Malak
Abstract: Cladding material is applied by laser to a net-shape. A method of cladding a host component includes installing the component in a fixture. A shroud component is located against the host component adjacent a select location for the cladding. Cladding is applied to the host component to the select location and adjacent to shroud component so that the shroud component defines an edge of the cladding as applied. The edge of the cladding as defined by the shroud component defines a desired cladding profile requiring no/approximately no post-cladding processing to remove over-cladded material.
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3.发明申请公开(公告)号：US20170138206A1
公开(公告)日：2017-05-18
申请号：US14939360
申请日：2015-11-12
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , David K. Jan , Don Mittendorf , Brent Ludwig , Amandine Miner , Deanna Pinar Chase
CPC classification number: F01D5/048 , B23K20/021 , B23K2101/001 , F01D5/28 , F01D5/3061 , F01D5/34 , F05D2230/42 , F05D2300/175 , F05D2300/607 , F05D2300/609
Abstract: Dual alloy bladed rotors are provided, as are methods for manufacturing dual alloy bladed rotors. In one embodiment, the method includes arranging bladed pieces in a ring formation such that contiguous bladed pieces contact along shank-to-shank bonding interfaces. The ring formation is positioned around a hub disk, which is contacted by the bladed pieces along a shank-to-hub bonding interface. A metallic sealing material is deposited between contiguous bladed pieces utilizing, for example, a laser welding process to produce an annular seal around the ring formation. A hermetic cavity is then formed, which is circumferentially bounded by the annular seal and which encloses the shank-to-shank and shank-to-hub bonding interface. Afterwards, a Hot Isostatic Pressing process is performed during which the ring formation and the hub disk are exposed to elevated pressures external to the hermetic cavity sufficient to diffusion bond the shank-to-shank and shank-to-hub bonding interface.
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Patent Agency Ranking
公开(公告)号：US20210123350A1
公开(公告)日：2021-04-29
申请号：US16665964
申请日：2019-10-28
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Donald Mittendorf , Krista Amato , Nicole Conklin , Brent Ludwig , Mark Morris , Ryon Stanley , Donald Tilman , Heemann Yun
IPC: F01D5/28
Abstract: A turbomachine includes a shroud and a rotor, which includes first and second blades. A first blade tip and a second blade tip respectively include a base and a first layer. The second blade tip also includes an abrasive second layer layered over the respective first layer. The first layer has a lower material hardness than the shroud. The second layer has a lower thermal stability than the shroud and the first layer. The rotor performs a grind operation and, subsequently, a post-grind operation. The second layer, in the grind operation, contacts and removes material from the shroud, and wears away, thereby revealing the first layer of the second blade tip for the post-grind operation. The first layer of the first blade tip is spaced apart with at least some radial clearance from the shroud in the grind and post-grind operations.
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公开(公告)号：US10900363B2
公开(公告)日：2021-01-26
申请号：US16051560
申请日：2018-08-01
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Brent Ludwig , Don Mittendorf , David R. Waldman , Malak Fouad Malak
Abstract: Cladding material is applied by laser to a net-shape. A method of cladding a host component includes installing the component in a fixture. A shroud component is located against the host component adjacent a select location for the cladding. Cladding is applied to the host component to the select location and adjacent to shroud component so that the shroud component defines an edge of the cladding as applied. The edge of the cladding as defined by the shroud component defines a desired cladding profile requiring no/approximately no post-cladding processing to remove over-cladded material.
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公开(公告)号：US10857596B1
公开(公告)日：2020-12-08
申请号：US16127383
申请日：2018-09-11
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Don Mittendorf , Jason Smoke , Brent Ludwig
Abstract: A method of producing an abrasive tip for a turbine blade includes producing or obtaining a metal powder that is mixed with an abrasive ceramic powder and producing or obtaining a metallic mold that is in the shape of an airfoil. The metallic mold includes a hollow interior portion. The method further includes sealing the metal and ceramic powder mixture within the hollow interior portion of the metallic mold under vacuum and subjecting the sealed mold to a hot isostatic pressing process. The hot isostatic pressing process compacts and binds the metal and ceramic powder mixture together into a solid article in the shape of the airfoil. Still further, the method includes slicing the solid article into a plurality of airfoil-shaped slices and bonding one slice of the plurality of airfoil-shaped slices to a tip portion of a turbine blade.
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公开(公告)号：US20200360998A1
公开(公告)日：2020-11-19
申请号：US16127383
申请日：2018-09-11
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Don Mittendorf , Jason Smoke , Brent Ludwig
Abstract: A method of producing an abrasive tip for a turbine blade includes producing or obtaining a metal powder that is mixed with an abrasive ceramic powder and producing or obtaining a metallic mold that is in the shape of an airfoil. The metallic mold includes a hollow interior portion. The method further includes sealing the metal and ceramic powder mixture within the hollow interior portion of the metallic mold under vacuum and subjecting the sealed mold to a hot isostatic pressing process. The hot isostatic pressing process compacts and binds the metal and ceramic powder mixture together into a solid article in the shape of the airfoil. Still further, the method includes slicing the solid article into a plurality of airfoil-shaped slices and bonding one slice of the plurality of airfoil-shaped slices to a tip portion of a turbine blade.
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公开(公告)号：US10036254B2
公开(公告)日：2018-07-31
申请号：US14939360
申请日：2015-11-12
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Jason Smoke , David K. Jan , Don Mittendorf , Brent Ludwig , Amandine Miner , Deanna Pinar Chase
CPC classification number: F01D5/048 , B23K20/021 , B23K2101/001 , B23P15/006 , F01D5/28 , F01D5/3061 , F01D5/34 , F05D2230/42 , F05D2300/175 , F05D2300/607 , F05D2300/609
Abstract: Dual alloy bladed rotors are provided, as are methods for manufacturing dual alloy bladed rotors. In one embodiment, the method includes arranging bladed pieces in a ring formation such that contiguous bladed pieces contact along shank-to-shank bonding interfaces. The ring formation is positioned around a hub disk, which is contacted by the bladed pieces along a shank-to-hub bonding interface. A metallic sealing material is deposited between contiguous bladed pieces utilizing, for example, a laser welding process to produce an annular seal around the ring formation. A hermetic cavity is then formed, which is circumferentially bounded by the annular seal and which encloses the shank-to-shank and shank-to-hub bonding interface. Afterwards, a Hot Isostatic Pressing process is performed during which the ring formation and the hub disk are exposed to elevated pressures external to the hermetic cavity sufficient to diffusion bond the shank-to-shank and shank-to-hub bonding interface.
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