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1.发明授权公开(公告)号：US12104502B2
公开(公告)日：2024-10-01
申请号：US17904651
申请日：2021-02-18
发明人： Marco Pieri
CPC分类号： F01D5/225 , F01D5/3007 , F01D5/326 , B23P15/006 , B23P15/04 , F05D2220/31 , F05D2230/60 , F05D2240/242 , F05D2240/30 , Y10T29/49321 , Y10T29/49945
摘要： A rotary machine assembly for a turbomachine, such as a rotor, having a rotor wheel where a plurality of circumferentially spaced female dovetail slots are obtained. The rotary machine assembly also comprises a plurality of blades. Between each blade and the adjacent one there is an interface angle. Each blade comprises a male dovetail, configured to fit with a corresponding female dovetail slot of the rotor wheel along an insertion direction. The female dovetail slots are shaped so that the insertion direction of each male dovetail is convergent with the rotation axis of the rotor wheel, so as to form with it an insertion angle, so as to insert gradually all the male dovetails into the female dovetail slots and packing them also gradually. A method for assembling a rotary machine assembly, which does not require any specific tool, is also disclosed.
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公开(公告)号：US12049831B2
公开(公告)日：2024-07-30
申请号：US17765955
申请日：2020-10-01
CPC分类号： F01D5/005 , B23P6/007 , B23P15/006 , F01D5/34 , F05D2230/31 , F05D2240/307
摘要： A method repairs welding of an aircraft turbine engine blade that has a lower surface and an upper surface connected by a leading edge and a trailing edge. The blade further includes a free end referred to as the tip. The method includes the repair welding of the tip and including the steps of: securing a first stop to the leading edge at the tip and a second stop to the trailing edge at the tip, depositing a repair weld bead on the tip, from the first stop to the second stop, and removing the first and second stops. The first and second stops are secured solely by squeezing same on the leading and trailing edges.
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公开(公告)号：US20230407767A1
公开(公告)日：2023-12-21
申请号：US18126774
申请日：2023-03-27
CPC分类号： F01D25/265 , B22D19/009 , B23P15/006 , B23P2700/13 , F05D2240/14 , B23P15/008
摘要： An assembly is provided for a gas turbine engine. This gas turbine engine assembly includes a split case structure. The split case structure includes a plurality of walls and a plurality of case segments. Each of the walls extends axially along and circumferentially about an axial centerline. The walls include a first wall and a second wall radially outboard of and axially overlapping the first wall. Each of the case segments is configured to form a respective portion of the first wall and a respective portion of the second wall. The case segments include a first case segment and a second case segment circumferentially adjacent and attached to the first case segment at a joint.
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4.发明申请公开(公告)号：US20190211433A1
公开(公告)日：2019-07-11
申请号：US15863163
申请日：2018-01-05
CPC分类号： C22F1/183 , B23K20/1205 , B23K20/129 , B23K20/233 , B23K20/24 , B23K20/26 , B23K2101/001 , B23K2103/14 , B23K2103/18 , B23K2103/26 , B23P15/006 , C22F1/002 , F01D5/3061 , F01D5/34
摘要： A method for producing an enhanced property integrally bladed rotor includes solution heat treating a stub-containing rotor hub forging; water quenching the solution heat treated stub-containing rotor hub; aging the water quenched stub-containing rotor hub forging; linear friction welding airfoils onto each of a multiple of stubs of the stub-containing rotor hub forging; and concurrently stress relieving the linear friction welds of each of the multiple of stubs within a predefined area while ensuring that a hub inner diameter does not exceed a predetermined temperature.
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公开(公告)号：US10018047B2
公开(公告)日：2018-07-10
申请号：US14559023
申请日：2014-12-03
发明人： John P. Rizzo
CPC分类号： F01D5/02 , B23B2215/04 , B23P15/006 , B24B1/00 , B24B5/01 , F01D5/34 , F05D2230/10
摘要： Powder metal alloy engine hardware components may be finished using a combination of roughing and grinding techniques. An engine component may be rough ground with a grinding wheel at a relatively high rate of material removal. The engine hardware component may be semi-finished using a turning process. The engine hardware component may be finished using a grinding wheel.
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公开(公告)号：US10005159B2
公开(公告)日：2018-06-26
申请号：US14803700
申请日：2015-07-20
申请人： ROLLS-ROYCE PLC
发明人： Paul Philip Sweeting
IPC分类号： B23K37/08 , B23D19/02 , B25J11/00 , B23P15/00 , F01D5/34 , B23K20/26 , B23K20/12 , F01D5/30 , B23K101/00
CPC分类号： B23K37/08 , B23D19/02 , B23K20/1205 , B23K20/129 , B23K20/26 , B23K2101/001 , B23P15/006 , B25J11/006 , F01D5/3061 , F01D5/34
摘要： Method of trimming weld flash from a weld joint formed between a first component and a second component. The method provides a rotary shear tool having a rotary blade and a second blade. The second blade may be a fixed blade. The method further includes shearing the weld flash from the weld joint by passing the weld flash between the rotary blade and second blade of the rotary shear tool. Also provides a rotary shear tool for trimming weld flash from a weld joint formed between a first component and a second component. The rotary shear tool includes: a rotary blade; a second blade; and a mounting portion for mounting the rotary shear tool on a robotic arm.
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公开(公告)号：US20180073365A1
公开(公告)日：2018-03-15
申请号：US15822350
申请日：2017-11-27
IPC分类号： F01D5/02 , B24C1/00 , B23D45/00 , B23P15/00 , B24B7/04 , B24B7/16 , B24B19/26 , B24B27/00 , F01D25/28 , F01D7/00 , B27C7/04 , B27C7/00 , B27C1/00 , B26D3/00 , B23C3/00 , B24B41/06 , B24B39/06 , B23D45/04
CPC分类号： F01D5/025 , B23C3/00 , B23D45/00 , B23D45/003 , B23D45/046 , B23P15/006 , B24B7/04 , B24B7/16 , B24B19/26 , B24B27/0038 , B24B27/0092 , B24B39/06 , B24B41/061 , B24B41/067 , B24C1/00 , B26D3/00 , B27C1/00 , B27C7/00 , B27C7/04 , F01D5/02 , F01D7/00 , F01D25/285 , F05D2230/10 , F05D2230/90 , F05D2240/20 , F05D2240/24 , F05D2300/13 , F05D2300/131 , F05D2300/132
摘要： A component according to the disclosure may include a body having an aperture therein for receiving one of a turbomachine shaft or a lathe chuck, wherein in response to the body being coupled to the lathe chuck, the aperture is oriented substantially axially relative to an axis of rotation of the body with the lathe chuck; and a flange coupled to and in direct axial contact with the body, the flange including a surface that extends axially relative to the axis of rotation of the body, wherein the surface of the flange comprises a matingly engageable face configured to contact an axially aligned surface during operation of the component and having a sanding indentation thereon, wherein a surface roughness of the surface of the flange is less than a surface roughness of a remainder of the component.
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公开(公告)号：US20170304929A1
公开(公告)日：2017-10-26
申请号：US15648577
申请日：2017-07-13
发明人： Amandine Miner , David K. Jan , Don Mittendorf , Jason Smoke
IPC分类号： B23K20/02 , B23K1/00 , F01D5/30 , B23K20/22 , B23K20/26 , B23P15/00 , F01D5/34 , B23K20/14 , B23K31/02 , B23K101/00 , B23K20/00
CPC分类号： 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
摘要： 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.
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9.发明授权公开(公告)号：US09765632B2
公开(公告)日：2017-09-19
申请号：US13962005
申请日：2013-08-08
申请人： MTU AERO ENGINES AG
发明人： Karl-Hermann Richter
CPC分类号： F01D5/28 , B23P15/006 , C22F1/183 , F01D5/048 , F01D5/146 , F01D5/22 , F01D5/30 , Y02T50/672 , Y02T50/673 , Y10T29/49336
摘要： Disclosed is a process for producing a blade or vane ring segment for a gas turbine, in particular for an aero engine, and also to a correspondingly produced blade or vane ring segment, the process comprising: forging at least two blanks made of a TiAl material, joining the blanks to form a blade or vane ring by means of an integral connection process, and remachining of the blank composite by material-removing processes.
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10.发明授权公开(公告)号：US09714577B2
公开(公告)日：2017-07-25
申请号：US14062611
申请日：2013-10-24
发明人： Harry Lester Kington , Brian Hann
IPC分类号： F01D5/02 , F01D5/04 , F01D5/34 , B22F3/15 , F01D5/14 , B22C9/04 , B22D25/02 , B22F5/00 , B23P15/00 , B22F5/10
CPC分类号： F01D5/147 , B22C9/04 , B22D25/02 , B22F3/15 , B22F5/009 , B22F2005/103 , B23P15/006 , F01D5/04 , F01D5/048 , F01D5/34 , F05D2230/21 , F05D2230/50 , F05D2260/941 , Y10T29/49321
摘要： Embodiments of a gas turbine engine rotor including stress relief features are provided, as are embodiments of method for producing a gas turbine engine rotor. In one embodiment, the method includes producing a hub preform in which a plurality of elongated sacrificial cores are embedded. Blades are attached to an outer circumference of the hub preform by, for example, bonding a blade ring to the outer circumference of the preform. The blades are spaced about the rotational axis of the gas turbine engine rotor and circumferentially interspersed with the plurality of elongated sacrificial cores. The plurality of elongated sacrificial cores are then removed from the hub preform to yield a plurality of stress distribution tunnels extending in the hub preform.
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