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公开(公告)号：US12055043B2
公开(公告)日：2024-08-06
申请号：US18108136
申请日：2023-02-10
发明人： Pantcho P. Stoyanov , Eli N. Ross
IPC分类号： F16J15/08 , B23K9/04 , F01D11/00 , F16J15/16 , B23K103/10
CPC分类号： F01D11/003 , B23K9/04 , F16J15/0806 , F16J15/16 , B23K2103/10 , F05D2240/55 , F05D2300/177
摘要： A method includes providing a powdered high entropy alloy and forming the powdered high entropy alloy into a seal body with a heat source. The seal body extends between a leading edge and a trailing edge and includes a first component contact surface adjacent the leading edge and a second component contact surface adjacent the trailing edge. The seal body is operable at temperatures in excess of 700° C.
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公开(公告)号：US11739663B2
公开(公告)日：2023-08-29
申请号：US16454975
申请日：2019-06-27
CPC分类号： F01D25/246 , F01D25/28 , F23R3/002 , F23R3/50 , F23R3/60 , F05D2220/32 , F05D2240/35 , F05D2300/177 , F05D2300/50212 , F05D2300/6033 , F23R2900/00018
摘要： A flow path assembly for a gas turbine engine is provided. The flow path assembly may include an outer casing comprising a metal material having a first coefficient of thermal expansion, a ceramic structure comprising a ceramic material having a second coefficient of thermal expansion, and a mounting component attached on a first end to the outer casing and attached on a second end to the ceramic structure. The mounting component may be constructed from at least two materials transitioning from the first end to the second end such that the coefficient of thermal expansion is different at the first end than the second end.
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公开(公告)号：US20180126489A1
公开(公告)日：2018-05-10
申请号：US15343565
申请日：2016-11-04
CPC分类号： B23K26/0643 , B23K26/0096 , B23K26/02 , B23K26/082 , B23K26/0884 , B23K26/14 , B23K26/322 , B23K26/40 , B23K2101/001 , B23K2103/04 , B23K2103/14 , B23K2103/166 , B23P6/002 , F01D9/02 , F01D25/24 , F04D29/522 , F05D2220/32 , F05D2230/13 , F05D2240/35 , F05D2300/171 , F05D2300/174 , F05D2300/177 , F23R3/002
摘要： The present disclosure is directed to a system for performing in-situ laser machining on a component within a gas turbine engine, in which the component includes a substrate defining a surface. The system includes a laser system disposed externally of the gas turbine engine, a focusing optic, and a conduit. The laser system includes a laser unit that produces an output beam. The focusing optic is disposed between the laser unit and the component. The conduit defines a first end external of the engine and a second end that ingresses into the engine through an access port. The conduit includes a plurality of mirrors within the conduit. The plurality of mirrors directs the output beam from the laser system onto the component.
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4.发明授权公开(公告)号：US09932657B2
公开(公告)日：2018-04-03
申请号：US14858421
申请日：2015-09-18
申请人： IHI Corporation
发明人： Yasuhiro Aoki , Akihiro Sato
CPC分类号： C22C19/057 , C22C19/056 , C22F1/10 , C30B11/00 , C30B29/52 , F01D5/28 , F05D2220/30 , F05D2230/40 , F05D2300/131 , F05D2300/132 , F05D2300/133 , F05D2300/135 , F05D2300/175 , F05D2300/177 , F05D2300/607
摘要： The present invention provides a Ni-based single crystal superalloy which has the following composition by weight: 0.1 wt % or more and 9.9 wt % or less of Co, 5.1 wt % or more and 10.0 wt % or less of Cr, 1.0 wt % or more and 4.0 wt % or less of Mo, 8.1 wt % or more and 11.0 wt % or less of W, 4.0 wt % or more and 9.0 wt % or less of Ta, 5.2 wt % or more and 7.0 wt % or less of Al, 0.1 wt % or more and 2.0 wt % or less of Ti, 0.05 wt % or more and 0.3 wt % or less of Hf, 1.0 wt % or less of Nb and less than 3.0 wt % of Re with the remainder including Ni and unavoidable impurities. This Ni-based single crystal superalloy has a low Re content and also has excellent high-temperature strength, mainly creep strength.
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公开(公告)号：US20180031002A1
公开(公告)日：2018-02-01
申请号：US15225499
申请日：2016-08-01
IPC分类号： F04D29/58 , F04D27/00 , F02C3/04 , F04D29/056 , F04D29/52 , F02K3/06 , F04D19/00 , F04D29/02
CPC分类号： F04D29/5853 , F01D25/02 , F01D25/162 , F02C7/047 , F04D19/002 , F04D27/009 , F04D29/023 , F04D29/056 , F04D29/522 , F04D29/584 , F05D2220/36 , F05D2240/15 , F05D2260/20 , F05D2300/177 , Y02T50/675
摘要： A fan section includes a fan inlet case, fan bearing assembly, and an annular heatshield. The fan bearing assembly may be coupled to the fan inlet case and the annular heatshield may be mounted to the fan inlet case. In various embodiments, the annular heatshield is configured to reduce convective heat transfer from heated fluid to the fan bearing assembly.
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公开(公告)号：US20170356092A1
公开(公告)日：2017-12-14
申请号：US15176699
申请日：2016-06-08
发明人： Zhongfen Ding , Mark R. Jaworowski
CPC分类号： C23F1/28 , C23G1/10 , F01D5/005 , F01D5/288 , F05D2220/32 , F05D2230/10 , F05D2300/177 , F05D2300/21 , F05D2300/228 , F05D2300/229 , F05D2300/608
摘要： During a material removal method, a component is received that includes a component body and a coating on the component body. The component body includes metallic first material. The coating includes second material that is different from the first material. A solution is received that includes nitric acid and hydrogen peroxide. At least a portion of the coating is subjected to the solution in order to remove at least some of the second material from the component.
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公开(公告)号：US09835032B2
公开(公告)日：2017-12-05
申请号：US14727194
申请日：2015-06-01
CPC分类号： F01D5/082 , F01D5/081 , F01D5/3007 , F05D2220/32 , F05D2230/12 , F05D2230/30 , F05D2240/81 , F05D2250/294 , F05D2260/20 , F05D2300/177 , Y02T50/676
摘要： A rotor disk is provided. The rotor disk may comprise a disk lug and a trench. The disk lug may be fixed to a distal surface of the rotor disk. The trench may be disposed on a surface of the disk lug. The trench may extend radially inwards from a distal surface of the disk lug. The trench may be configured to at least partially define a flow path by which cooling air may reach a distal surface of the disk lug in order to provide disk lug cooling.
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公开(公告)号：US20170306783A1
公开(公告)日：2017-10-26
申请号：US15137524
申请日：2016-04-25
发明人： Daniel Anthony Grande , Agnieszka M. Wusatowska-Sarnek , Thomas D. Kasprow , David Ulrich Furrer , Sergei F. Burlatsky
CPC分类号： F01D11/122 , C23C4/073 , C23C4/126 , C23C4/131 , C23C4/134 , F01D11/125 , F01D25/005 , F05D2220/32 , F05D2230/30 , F05D2230/311 , F05D2230/312 , F05D2230/60 , F05D2230/90 , F05D2300/175 , F05D2300/177 , F05D2300/2282 , F05D2300/514 , F05D2300/6032 , F05D2300/615
摘要： A blade outer airseal has a body comprising: an inner diameter (ID) surface; an outer diameter (OD) surface; a leading end; and a trailing end. The airseal body has a metallic substrate and a coating system atop the substrate along at least a portion of the inner diameter surface. At least over a first area of the inner diameter surface, the coating system comprises an abradable layer system comprising a plurality of layers including a relatively erosion-resistant first layer atop a relatively abradable second layer.
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公开(公告)号：US09784215B2
公开(公告)日：2017-10-10
申请号：US14536273
申请日：2014-11-07
申请人： ROHR, INC.
CPC分类号： F02K1/80 , F01D25/243 , F01D25/30 , F02K1/04 , F05D2220/30 , F05D2230/642 , F05D2300/176 , F05D2300/177 , F05D2300/20 , F05D2300/6033 , Y02T50/672
摘要： A ceramic turbine engine exhaust component, such as a ceramic matrix composite (“CMC”) exhaust center body may be positioned around a metallic attachment ring. The attachment ring may have a greater coefficient of thermal expansion than the CMC center body. A plurality of bolts radially-spaced around the circumference of the attachment ring may be inserted through apertures in the center body with a sliding fit, and may be coupled to the attachment ring. The bolts may slide within the apertures, allowing the attachment ring to thermally expand without applying extra loads on the exhaust center body due to the expansion.
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公开(公告)号：US20170239763A1
公开(公告)日：2017-08-24
申请号：US15590934
申请日：2017-05-09
CPC分类号： B23P6/045 , B22D21/005 , B23K35/025 , B23K35/3033 , B23K2101/001 , B23P6/002 , B23P6/005 , C22C19/03 , F01D5/005 , F01D11/08 , F05D2220/32 , F05D2230/80 , F05D2240/11 , F05D2300/123 , F05D2300/177
摘要： A structural element for repairing a damaged component comprising a shaped cavity configured to receive the damaged component and a repair material, the shaped cavity comprising a material having a first melting point and the repair material comprising a material having a second melting point that is lower than the first melting point. The shaped cavity may comprise a preform for the damaged component. The preform may comprise a mold configured to reconstruct the shape of the damaged component. The repair material may comprise a first material and a second material, the second material having a melting point that is lower than the first material. The repair material may comprise a Nickel-Boron composition. The repair material may have a melting point that is approximately 40 degrees Fahrenheit lower than the melting point of the damaged component.
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