-
公开(公告)号：US08858873B2
公开(公告)日：2014-10-14
申请号：US13675439
申请日：2012-11-13
Applicant: Honeywell International Inc.
Inventor： Don Mittendorf
CPC classification number: C22C19/05 , C22C19/03 , C22C19/057 , F01D5/28 , F05D2300/175
Abstract: A nickel-based super alloy includes, by weight, about 1.5% to about 5.5% chromium, about 8% to about 12% aluminum, about 4% to about 8% tantalum, about 1.5% to about 5.5% tungsten, less than about 1% of one or more of elements selected from a group consisting of carbon, boron, zirconium, yttrium, hafnium, and silicon, and a balance of nickel.
Abstract translation: 一种镍基超级合金包括按重量计约1.5％至约5.5％的铬，约8％至约12％的铝，约4％至约8％的钽，约1.5％至约5.5％的钨，小于约 选自碳，硼，锆，钇，铪和硅中的一种或多种元素的1％，余量为镍。
-
公开(公告)号：US10933469B2
公开(公告)日：2021-03-02
申请号：US16126222
申请日：2018-09-10
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Don Mittendorf , Vladimir K Tolpygo
Abstract: A method of forming an abrasive nickel-based alloy on a turbine blade tip includes producing or obtaining a metal powder that is mixed with a carbon powder to form a carbon-enriched metal powder. The metal powder includes a refractory element. The method further includes bonding the carbon-enriched metal powder to the turbine blade tip. The step of bonding includes raising the temperature of the carbon-enriched metal powder past its melting point, thereby causing the carbon to combine with the refractory elements to form abrasive carbide particles.
-
公开(公告)号：US20200078867A1
公开(公告)日：2020-03-12
申请号：US16126222
申请日：2018-09-10
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Don Mittendorf , Vladimir K Tolpygo
Abstract: A method of forming an abrasive nickel-based alloy on a turbine blade tip includes producing or obtaining a metal powder that is mixed with a carbon powder to form a carbon-enriched metal powder. The metal powder includes a refractory element. The method further includes bonding the carbon-enriched metal powder to the turbine blade tip. The step of bonding includes raising the temperature of the carbon-enriched metal powder past its melting point, thereby causing the carbon to combine with the refractory elements to form abrasive carbide particles.
-
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.
-
公开(公告)号：US10399176B2
公开(公告)日：2019-09-03
申请号：US15648577
申请日：2017-07-13
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Amandine Miner , David K. Jan , Don Mittendorf , Jason Smoke
IPC: F01D5/30 , B23K1/00 , B23K20/02 , B23K31/02 , B23P15/00 , B23K20/14 , B23K20/22 , B23K20/26 , F01D5/34 , B23K101/00 , B23K20/00
Abstract: Dual alloy turbine rotors and methods for manufacturing the same are provided. The dual alloy turbine rotor comprises an assembled blade ring and a hub bonded to the assembled blade ring. The assembled blade ring comprises a first alloy selected from the group consisting of a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy. The hub comprises a second alloy. The method comprises positioning a hub within a blade ring to define an interface between the hub and the blade ring. The interface is a non-contacting interface or a contacting interface. The interface is enclosed by a pair of diaphragms. The interface is vacuum sealed. The blade ring is bonded to the hub after the vacuum sealing step.
-
Patent Agency Ranking
26.发明授权公开(公告)号：US10385433B2
公开(公告)日：2019-08-20
申请号：US15071630
申请日：2016-03-16
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Christopher David Gatto , Jude Miller , Benjamin Dosland Kamrath , Don Mittendorf , Jason Smoke , Mark C. Morris
IPC: C22F1/10 , C21D1/34 , F01D5/02 , F01D5/28 , F04D29/32 , C21D1/00 , F04D29/02 , B23P15/00 , F01D5/06 , F01D5/34
Abstract: Methods for processing bonded dual alloy rotors are provided. In one embodiment, the method includes obtaining a bonded dual alloy rotor including rotor blades bonded to a hub disk. The rotor blades and hub disk are composed of different alloys. A minimum processing temperature (TDISK_PROCESS_MIN) for the hub disk and a maximum critical temperature for the rotor blades (TBLADE_MAX) is established such that TBLADE_MAX is less than TDISK_PROCESS_MIN. A differential heat treatment process is then performed during which the hub disk is heated to processing temperatures equal to or greater than TDISK_PROCESS_MIN, while at least a volumetric majority of each of the rotor blades is maintained at temperatures below TBLADE_MAX. Such a targeted differential heat treatment process enables desired metallurgical properties (e.g., precipitate hardening) to be created within the hub disk, while preserving the high temperature properties of the rotor blades and any blade coating present thereon.
-
公开(公告)号：US09951632B2
公开(公告)日：2018-04-24
申请号：US14806933
申请日：2015-07-23
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： David R Waldman , Don Mittendorf , Mark C. Morris , Michael Vinup
IPC: B23K20/00 , F01D5/30 , B23K20/12 , B23K20/22 , B23K20/02 , B23K20/14 , B23K20/08 , B23K9/167 , B23K9/23 , B23K5/14 , B23K5/00 , B23K10/02 , B23K15/00 , B23K26/32 , B23K26/21 , F01D5/08 , F01D5/34 , F01D11/00 , B23K103/08
CPC classification number: F01D5/3061 , B23K20/1205 , B23K20/16 , B23K2101/001 , F01D5/082 , F01D5/34 , F01D11/006 , F05D2230/239 , F05D2300/606 , F05D2300/607 , Y02T50/671 , Y02T50/673 , Y02T50/676
Abstract: Hybrid bonded turbine rotors and methods for manufacturing the same are provided. A method for manufacturing a hybrid bonded turbine rotor comprises the steps of providing turbine disk having a rim portion comprising a live rim of circumferentially continuous material and a plurality of live rim notches in an outer periphery of the turbine disk alternating with a plurality of raised blade attachment surfaces defining the outer periphery; providing a plurality of turbine blades, each of which comprising an airfoil portion and a shank portion, the shank portion having a base surface; metallurgically bonding a compliant alloy material layer to either or both of the raised blade attachments surfaces of the turbine disk and the base surfaces of the blade shanks; and linear friction welding the plurality of blades to the turbine disk so as to form a bond plane between the raised blade attachments surfaces of the turbine disk and the base surfaces of the blade shanks, the compliant alloy material layer being disposed at the bond plane.
-
公开(公告)号：US09726022B2
公开(公告)日：2017-08-08
申请号：US14713220
申请日：2015-05-15
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Don Mittendorf , David K. Jan , Jason Smoke , Amandine Miner
CPC classification number: F01D5/147 , B23P15/006 , F01D5/04 , F01D5/045 , F01D5/046 , F01D5/048 , F01D5/066 , F01D5/088 , F01D5/18 , F01D5/187 , F01D5/28 , F01D5/30 , F05D2230/60 , Y02T50/671 , Y02T50/676 , Y10T29/49321 , Y10T29/49323 , Y10T29/49341
Abstract: Embodiments of an axially-split radial turbine, as are embodiments of a method for manufacturing an axially-split radial turbine. In one embodiment, the method includes the steps of joining a forward bladed ring to a forward disk to produce a forward turbine rotor, fabricating an aft turbine rotor, and disposing the forward turbine rotor and the aft turbine rotor in an axially-abutting, rotationally-fixed relationship to produce the axially-split radial turbine.
-
公开(公告)号：US09724780B2
公开(公告)日：2017-08-08
申请号：US14297406
申请日：2014-06-05
Applicant: HONEYWELL INTERNATIONAL INC.
Inventor： Amandine Miner , David K Jan , Don Mittendorf , Jason Smoke
IPC: B23K31/02 , B23K20/02 , B23K1/00 , B23P15/00 , B23K20/14 , B23K20/22 , B23K20/26 , F01D5/30 , F01D5/34 , B23K20/00 , B23K101/00
CPC classification number: B23K20/028 , B23K1/00 , B23K1/0018 , B23K20/002 , B23K20/021 , B23K20/023 , B23K20/14 , B23K20/22 , B23K20/26 , B23K31/02 , B23K2101/001 , B23P15/006 , F01D5/3061 , F01D5/34 , F05D2220/323 , F05D2230/236 , F05D2230/60 , F05D2300/17 , F05D2300/606 , F05D2300/607 , Y10T29/49323
Abstract: Dual alloy turbine rotors and methods for manufacturing the same are provided. The dual alloy turbine rotor comprises an assembled blade ring and a hub bonded to the assembled blade ring. The assembled blade ring comprises a first alloy selected from the group consisting of a single crystal alloy, a directionally solidified alloy, or an equi-axed alloy. The hub comprises a second alloy. The method comprises positioning a hub within a blade ring to define an interface between the hub and the blade ring. The interface is a non-contacting interface or a contacting interface. The interface is enclosed by a pair of diaphragms. The interface is vacuum sealed. The blade ring is bonded to the hub after the vacuum sealing step.
-
30.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.
-
-
-
-
-
-
-
-
-
Search Results
33
records
(took 0.024 seconds)
