Patent
Ceramic matrix composite component for a gas turbine engine
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TLDR
In this article, the gap between the CMC member and the support member is kept purposefully small to limit the stress developed in the material when it is deflected against the support by the force of a rubbing blade tip.Abstract:
A ceramic matrix composite (CMC) component for a combustion turbine engine ( 10 ). A blade shroud assembly ( 30 ) may be formed to include a CMC member ( 32 ) supported from a metal support member ( 32 ). The CMC member includes arcuate portions ( 50, 52 ) shaped to surround extending portions ( 46, 48 ) of the support member to insulate the metal support member from hot combustion gas ( 16 ). The use of a low thermal conductivity CMC material allows the metal support member to be in direct contact with the CMC material. The gap ( 42 ) between the CMC member and the support member is kept purposefully small to limit the stress developed in the CMC member when it is deflected against the support member by the force of a rubbing blade tip ( 14 ). Changes in the gap dimension resulting from differential thermal growth may be regulated by selecting an angle (A) of a tapered slot ( 76 ) defined by the arcuate portion.read more
Citations
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Patent
Turbine blade and method of forming blade tip for eliminating turbine blade tip wear in rubbing
TL;DR: Coating systems for a cooled turbine blade tip, such as a metal turbine tip, are provided in this paper, where the coating system includes an abrasive layer overlying the surface of the turbine tip.
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Apparatus and method for forming apparatus
TL;DR: In this article, an apparatus consisting of a first article, a second article, and a third article disposed adjacent to one another, with the first article and the second article disposed between the third article and a gas path, is described.
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Shroud configuration having inclined seal
John Alan Eastman,Gary Michael Itzel,David Richard Johns,Bryan Lewis,Charles Malinowski,Victor John Morgan,ヴィクター・ジョン・モーガン,ゲーリー・マイケル・イゼェル,ジョン・アラン・イーストマン,チャールズ・マリノウスキ,デイヴィッド・リチャード・ジョンズ,ブライアン・ルイス +11 more
TL;DR: In this article, a shroud segment installed in this configuration comprises an outer shroud having a leading edge groove and a trailing edge groove 222 and a plurality of inner shrouds 214 having an leading edge hook and a trailed edge hook 218.
References
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Patent
Use of high temperature insulation for ceramic matrix composites in gas turbines
TL;DR: In this article, a ceramic composition for insulating components, made of ceramic matrix composites, of gas turbines is provided, which comprises a plurality of hollow oxide-based spheres of various dimensions, a phosphate binder, and at least one oxide filler powder, whereby the binder partially fills gaps between the spheres and the filler powders.
Patent
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TL;DR: A turbine ring has an annular metallic carrier which is mounted within the inside of the turbine casing and within the carrier there is provided a ceramic abradable ring as mentioned in this paper, and a cooling air circuit is provided to regulate the temperature of only the annular carrier such that the latter always exerts a centripetal compression force on the ring under all operational conditions of the gas turbine.
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Turbine ring incorporating elements of a ceramic composition divided into sectors
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Ceramic faced outer air seal for gas turbine engines
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TL;DR: In this article, the ceramic facing material of an outer air seal (30) at the leading edge region (36) is densified by a plasma gun to produce a glazed area (52) which is resistant to erosion.
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Turbine blade shroud assembly
TL;DR: In this paper, a turbine blade shroud assembly for a gas turbine engine includes a metal substrate ring on the engine, a continous ceramic barrier ring inside the substrate ring and exposed to hot gas in a hot gas flow path of the engine and a wire mesh compliant ring between the barrier and substrate rings.