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公开(公告)号：EP2236650A1
公开(公告)日：2010-10-06
申请号：EP10158950.5
申请日：2010-04-01
发明人： Lee, Kang N. , Thomas, David J
CPC分类号： C23C26/00 , C04B41/009 , C04B41/52 , C04B41/89 , C23C28/042 , C23C28/321 , C23C28/3215 , C23C28/345 , C23C28/3455 , C23C30/00 , F01D5/288 , F05D2250/621 , Y10T428/24545 , C04B35/565 , C04B35/806 , C04B35/10 , C04B35/803 , C04B35/584 , C04B41/5096 , C04B41/5024 , C04B41/5037 , C04B41/522 , C04B41/4527 , C04B41/5027 , C04B41/4529 , C04B41/4539 , C04B41/455 , C04B41/5022
摘要： An article (10) includes a substrate (16) defining a surface imperfection (20,22) and a coating (14) deposited over the substrate. The coating (14,12) does not substantially reproduce the surface imperfection, and the coating (14,12) comprises mullite and at least one rare earth silicate, rare earth oxide, alumina, boron oxide, alkali metal oxide, alkali earth metal oxide, silicon, barium strontium aluminosilicate, barium aluminosilicate, strontium aluminosilicate, calcium aluminosilicate, magnesium aluminosilicate, or lithium aluminosilicate. In some examples, the coating may be a first coating (14) deposited from a slurry over the substrate, and a second coating (12) may be deposited over the first coating. In other examples, a first coating (14) that substantially reproduces the surface imperfection may be deposited over the substrate, and the coating (12) that does not substantially reproduce the surface imperfection may be deposited over the first coating.
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公开(公告)号：EP3103964B1
公开(公告)日：2018-08-01
申请号：EP16171549.5
申请日：2016-05-26
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites Inc
发明人： Vetters, Daniel Kent , Thomas, David J , Freeman, Ted J. , Dierksmeier, Douglas D , Jun, Shi , Engel, Todd Z.
CPC分类号： F01D11/08 , F01D9/04 , F01D25/005 , F01D25/243 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/24 , F05D2240/55 , F05D2300/6033
摘要： A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (CMC) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore. The seal segment bore is radially spaced from the arcuate flange by a spacing flange which extends radially outward from the arcuate flange to effect receipt within the seal segment bore of an elongated pin. The elongated pin extends through the carrier bore and the seal segment bore, and the elongated pin has a lateral cross-sectional dimension of at least three-eighths of an inch.
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公开(公告)号：EP2886803B1
公开(公告)日：2020-03-11
申请号：EP14195163.2
申请日：2014-11-27
发明人： Thomas, David J , Freeman, Ted J
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公开(公告)号：EP3106620A1
公开(公告)日：2016-12-21
申请号：EP16171542.0
申请日：2016-05-26
申请人： Rolls-Royce Corporation , Rolls-Royce High Temperature Composites Inc , Rolls-Royce North American Technologies, Inc.
摘要： A cartridge for a ceramic matrix composite (CMC) seal segment of a segmented turbine shroud of a gas turbine engine is provided. The cartridge comprises a carrier segment and a CMC seal segment. A surface of the carrier segment and a surface of the CMC seal segment form a mating region proximate the entire perimeter of the CMC seal segment. The carrier segment surface may comprise a channel, and a compressible mating element may be disposed within the channel. Air may be supplied to a cavity, formed by the carrier and CMC seal segment, and the mating region.
摘要翻译： 提供了一种用于燃气涡轮发动机的分段涡轮机护罩的陶瓷基质复合材料（CMC）密封段的筒。 盒包括载体区段和CMC密封区段。 载体区段的表面和CMC密封区段的表面形成接近CMC密封区段的整个周边的配合区域。 载体段表面可以包括通道，并且可压缩配合元件可以设置在通道内。 可以将空气供应到由载体和CMC密封段形成的空腔以及配合区域。
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5.发明公开SHROUD CARTRIDGE HAVING A CERAMIC MATRIX COMPOSITE SEAL SEGMENT 审中-公开MANTELKARTUSCHE MIT KERAMISCHEM MATRIXVERBUNDSTOFFDICHTSEGMENT
公开(公告)号：EP3103964A1
公开(公告)日：2016-12-14
申请号：EP16171549.5
申请日：2016-05-26
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites Inc
发明人： Vetters, Daniel Kent , Thomas, David J , Freeman, Ted J. , Dierksmeier, Douglas D , Jun, Shi , Engel, Todd Z.
CPC分类号： F01D11/08 , F01D9/04 , F01D25/005 , F01D25/243 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2240/24 , F05D2240/55 , F05D2300/6033
摘要： A shroud for radially encasing a turbine in a gas turbine engine is provided. The shroud comprises a carrier which defines a pin-receiving carrier bore, and a ceramic matrix composite (CMC) seal segment comprising an arcuate flange with a surface facing the turbine and a part that defines a pin-receiving seal segment bore. The seal segment bore is radially spaced from the arcuate flange by a spacing flange which extends radially outward from the arcuate flange to effect receipt within the seal segment bore of an elongated pin. The elongated pin extends through the carrier bore and the seal segment bore, and the elongated pin has a lateral cross-sectional dimension of at least three-eighths of an inch.
摘要翻译： 提供了一种用于将涡轮径向包围在燃气涡轮发动机中的罩。 护罩包括限定销接收载体孔的载体和陶瓷基体复合材料（CMC）密封段，陶瓷基体复合材料（CMC）密封段包括具有面向涡轮的表面的弓形凸缘和限定销接收密封部分孔的部分。 密封段孔与弧形凸缘径向间隔开间隔凸缘，该间隔凸缘从弧形凸缘径向向外延伸，以在细长销的密封段孔内接收。 细长销延伸穿过承载孔和密封段孔，并且细长销具有至少八分之八英寸的横向横截面尺寸。
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公开(公告)号：EP3106630B1
公开(公告)日：2018-02-28
申请号：EP16171539.6
申请日：2016-05-26
申请人： Rolls-Royce Corporation , Rolls-Royce High Temperature Composites Inc , Rolls-Royce North American Technologies, Inc.
CPC分类号： F01D11/12 , F01D9/02 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2250/15 , F05D2260/30 , F05D2260/38 , F05D2260/941 , F05D2300/6033
摘要： A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.
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7.发明公开TURBINE SHROUD HAVING CERAMIC MATRIX COMPOSITE SEAL SEGMENT 有权TURBINENUMMANTELUNG MIT KERAMISCHEM MATRIXVERBUNDSTOFFDICHTSEGMENT
公开(公告)号：EP3106630A1
公开(公告)日：2016-12-21
申请号：EP16171539.6
申请日：2016-05-26
申请人： Rolls-Royce Corporation , Rolls-Royce High Temperature Composites Inc , Rolls-Royce North American Technologies, Inc.
CPC分类号： F01D11/12 , F01D9/02 , F01D25/246 , F05D2220/32 , F05D2240/11 , F05D2250/15 , F05D2260/30 , F05D2260/38 , F05D2260/941 , F05D2300/6033
摘要： A segmented turbine shroud for radially encasing a rotatable turbine in a gas turbine engine comprising a carrier, a ceramic matrix composite (CMC) seal segment, and an elongated pin. The carrier defines a pin-receiving carrier bore and the CMC seal segment defines a pin-receiving seal segment bore. The elongated pin extends through the carrier bore and the seal segment bore. The pin-receiving carrier bore includes a cantilevered member such that the carrier bore has a length sufficient to effect radial flexion between the carrier bore and the pin received within the carrier bore during operation of the turbine.
摘要翻译： 一种用于在包括载体，陶瓷基体复合（CMC）密封段和细长销）的燃气涡轮发动机中径向包围可旋转涡轮的分段涡轮机罩。 载体限定销接收载体孔，CMC密封段限定销接收密封段孔。 细长销延伸穿过承载孔和密封段孔。 销接收承载孔包括悬臂构件，使得承载孔具有足够的长度，以在涡轮机的运行期间在承载孔和承载孔内的销之间产生径向弯曲。
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8.发明公开CERAMIC MATRIX COMPOSITE SEAL SEGMENT FOR A GAS TURBINE ENGINE 有权KERAMIKMATRIX-VERBUNDWERKSTOFFDICHTUNGSSEGMENTFÜREINEN GASTURBINENMOTOR
公开(公告)号：EP3103963A1
公开(公告)日：2016-12-14
申请号：EP16171446.4
申请日：2016-05-25
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites Inc
发明人： Vetters, Daniel Kent , Thomas, David J , Freeman, Ted J. , Dierksmeier, Douglas D , Shi, Jun , Engel, Todd Z.
CPC分类号： F01D11/08 , F01D9/04 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2240/24 , F05D2300/6033
摘要： A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.
摘要翻译： 一种陶瓷基体复合材料（CMC）密封段，用于分段涡轮机护罩，用于在燃气涡轮发动机中径向包围涡轮机。 CMC密封段包括具有面向涡轮的表面的弧形凸缘和限定用于接收细长销的孔的部分，孔的长度为其中容纳的细长销的长度的至少70％。 CMC密封段由载体承载，其中至少一个细长销被接收在孔内。 限定销接收孔的CMC密封段部分通过从弧形凸缘径向向外延伸的间隔凸缘与弧形凸缘径向间隔开。
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公开(公告)号：EP3106620B1
公开(公告)日：2019-10-30
申请号：EP16171542.0
申请日：2016-05-26
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公开(公告)号：EP3103963B1
公开(公告)日：2018-03-07
申请号：EP16171446.4
申请日：2016-05-25
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites Inc
发明人： Vetters, Daniel Kent , Thomas, David J , Freeman, Ted J. , Dierksmeier, Douglas D , Shi, Jun , Engel, Todd Z.
CPC分类号： F01D11/08 , F01D9/04 , F01D25/24 , F01D25/246 , F05D2220/32 , F05D2240/24 , F05D2300/6033
摘要： A ceramic matrix composite (CMC) seal segment for use in a segmented turbine shroud for radially encasing a turbine in a gas turbine engine. The CMC seal segment comprises an arcuate flange having a surface facing the turbine and a portion defining a bore for receiving an elongated pin, with the bore having a length that is at least 70% of the length of the elongated pin received therein. The CMC seal segment is carried by the carrier by at least one of the elongated pins being received within the bore. The CMC seal segment portion defining a pin-receiving bore is radially spaced from the arcuate flange by a spacing flange extending radially outward from the arcuate flange.
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