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公开(公告)号：US20240246872A1
公开(公告)日：2024-07-25
申请号：US18157450
申请日：2023-01-20
CPC分类号： C04B41/87 , C04B41/5035 , C04B41/5042 , C04B41/5057 , C04B41/522
摘要： A section of a gas turbine engine includes a ceramic component, a metallic component, a seal situated between the metallic component and the ceramic component at a sealing interface, a silicon-based coating disposed on the ceramic component at the sealing interface, and a non-reactive coating disposed on the metallic component at the sealing interface. The non-reactive coating provides thermochemical protection against interaction between the ceramic component, the silicon-based coating, and the metallic component. A method of providing a seal in a gas turbine engine is also disclosed.
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公开(公告)号：US20240139998A1
公开(公告)日：2024-05-02
申请号：US17977370
申请日：2022-10-31
发明人： Raymond Surace
摘要： A method includes providing a continuous mandrel body disposed along an axis. The mandrel body defines, in order along the axis from a first end thereof, a pilot lead-in section, a first article section, a tapered transition section, and a second article section. Beginning at the pilot lead-in section, a continuous fabric sleeve is progressively formed on the mandrel body to the first article section, to the tapered transition section, and then to the second article section to form a fabric-covered mandrel. The portions of the continuous fabric sleeve that are on the first article section and the second article section form, respectively, a first article preform and a second article preform. The fabric-covered mandrel is then divided to separate the article preforms, followed by densifying the article preforms with a ceramic matrix material to thereby form CMC articles.
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公开(公告)号：US11952917B2
公开(公告)日：2024-04-09
申请号：US17882041
申请日：2022-08-05
发明人： David J. Wasserman , Raymond Surace
CPC分类号： F01D9/042 , F01D25/005 , F05D2220/32 , F05D2230/60 , F05D2240/12
摘要： A vane multiplet includes first and second ceramic matrix composite (CMC) singlet vanes that are arranged circumferentially adjacent each other. Each of the CMC singlet vanes includes an airfoil section and a platform at one end of the airfoil section. The platform defines forward and trailing platform edges and first and second circumferential side edges. A CMC overwrap conjoins the CMC singlet vanes. The CMC overwrap includes fiber plies that are fused to the platforms of the CMC singlet vanes.
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公开(公告)号：US11725522B2
公开(公告)日：2023-08-15
申请号：US17149944
申请日：2021-01-15
CPC分类号： F01D5/282 , F01D5/147 , F01D5/18 , F05D2200/11 , F05D2240/301 , F05D2240/304 , F05D2250/75 , F05D2300/6033 , F05D2300/6034
摘要： An airfoil includes an airfoil wall that defines a leading end, a trailing end, and pressure and suction sides that join the leading end and the trailing end. The airfoil wall includes a wishbone-shaped fiber layer structure that has a pair of arms that merge into a single leg. The pair of arms are formed by first and second S-shaped fiber layers each of which is comprised of a network of fiber tows. The first and second S-shaped fiber layers merge to form the single leg. The single leg comprises fiber tows from each of the first and second S-shaped fiber layers that are interwoven, and the single leg forms at least a portion of the trailing end of the airfoil wall.
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公开(公告)号：US20230235705A1
公开(公告)日：2023-07-27
申请号：US18153509
申请日：2023-01-12
摘要： A seal system includes a ceramic component that has a non-core-gaspath surface region that defines a first surface roughness and a core gaspath surface region. A metallic component is situated adjacent the non-core-gaspath surface region. A coating system is disposed on the ceramic component. The coating system includes a silicon-containing layer on the non-core-gaspath surface region and a barrier layer that has a first section on the silicon-containing layer and a second section on the core-gaspath region and that is connected to the first section. The surface of the barrier layer has a second surface roughness that is less than the first surface roughness. The first section is in contact with the metallic component and the second section serves as an environmental barrier on the core-gaspath region.
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公开(公告)号：US20240133034A1
公开(公告)日：2024-04-25
申请号：US17970990
申请日：2022-10-20
IPC分类号： C23C16/458 , C23C16/04
CPC分类号： C23C16/458 , C23C16/045
摘要： A tooling assembly suitable for use in infiltrating a fibrous preform comprises an outer tooling fixture and an inner tooling fixture. The outer tooling fixture comprises a first portion removably attached to a second portion, and a first pair of oppositely disposed windows defined by the first portion and the second portion. Each of the first portion and the second portion comprise a base with a recess. The inner tooling fixture comprises a body defined by at least one portion, the body configured to at least partially surround the fibrous preform, a plurality of holes extending through a thickness of the at least one portion, each hole of the plurality of holes having a length (L) and a diameter (D), and a first neck region engageable with a recess of the first portion or the second portion.
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公开(公告)号：US20230407755A1
公开(公告)日：2023-12-21
申请号：US17843434
申请日：2022-06-17
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F05D2240/12 , F05D2230/60 , F05D2300/6033 , F05D2300/175
摘要： An assembly for a gas turbine engine includes a plurality of vanes having a radially outer platform with a flange that extends radially outward therefrom and a plurality of notches in the flange. A ring is located radially outward from the radially outer platform of the plurality of vanes. An axially extending projection extends through and corresponds with each of the plurality of notches on the flange.
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公开(公告)号：US20230026977A1
公开(公告)日：2023-01-26
申请号：US17385271
申请日：2021-07-26
发明人： Kathryn S. Read , Raymond Surace
摘要： An assembly for a gas turbine engine according to an example of the present disclosure includes at least one platform having a main body extending between a first mate face and a second mate face to establish a gas path surface. The main body has an internal passage extending circumferentially between a first opening along the first mate face and a second opening along the second mate face relative to an assembly axis. A perimeter of the first mate face establishes a first area, a perimeter of the second opening establishes a second area, and the second area is greater than the first area. An airfoil section extends radially from the at least one platform.
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公开(公告)号：US11492914B1
公开(公告)日：2022-11-08
申请号：US17080969
申请日：2020-10-27
发明人： San Quach , Adam P. Generale , Raymond Surace , Lucas Dvorozniak
摘要： A gas turbine engine includes a blade outer air seal, a ceramic vane, and a cooling passage circuit that extends through a first internal passage in the blade outer air seal and a second internal passage in the ceramic vane.
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公开(公告)号：US11313242B2
公开(公告)日：2022-04-26
申请号：US16574840
申请日：2019-09-18
发明人： Alan D. Cetel , Dilip N. Shah , Eric A. Hudson , Raymond Surace
摘要： Aspects of the disclosure are directed to a seal configured to interface with at least a first component and a second component of a gas turbine engine. A method for forming the seal includes obtaining an ingot of a fine grained, or a coarse grained, or a columnar grained or a single crystal material from a precipitation hardened nickel base superalloy containing at least 40% by volume of the precipitate of the form Ni3(Al, X), where X is a metallic or refractory element, and processing the ingot to generate a sheet of the material, where the sheet has a thickness within a range of 0.010 inches and 0.050 inches inclusive.
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