Patent
Ceramic matrix composite component for a gas turbine engine
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
Mounting apparatus for low-ductility turbine shroud
Jason David Shapiro,Roger Lee Doughty,Aaron Michael Dziech,Victor Hugo Silva Correia,Lampes Elias Harry,Robert Carella,Brian Kenneth Corsetti +6 more
TL;DR: In this article, an annular support member (14), a turbine shroud (12), and a spring (32) are arranged between the support member and the turbine shroud to push the shroud to a concentric position within the support members.
Patent
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Patent
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Franck Roger Denis Denece,Alain Dominique Gendraud,Georges Habarou,Hubert Illand,Damien Bonneau +4 more
TL;DR: A turbine ring assembly includes a ring support structure and a plurality of ring sectors, each including a single piece of ceramic matrix composite material as discussed by the authors, each of which includes a first portion forming an annular base with an inside face defining the inside face of the turbine ring and an outside face from which there extends two tab-forming portions including ends that are engaged in housings in the ring structure.
Patent
Blade clearance control using high-CTE and low-CTE ring members
TL;DR: In this article, an engine has a blade stage (10) and a circumferential array of blade outer air seal segments (66), and a support ring (70) carries the blade outer-air-seal segments.
Patent
Ceramic matrix composite attachment apparatus and method
TL;DR: An attachment method and flange for connecting a ceramic matrix composite (CMC) component, such as a gas turbine shroud ring ( 36, 68 ), to a metal support structure was proposed in this paper.
References
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Patent
Hot gas overheat protection device for gas turbine engines
TL;DR: In this paper, a hot gas overheat protection device is provided for gas turbine engines and the like, where an outer metal wall having cooling air supplied through cooling holes therethrough from the outside is shielded from hot gas flow by the provision of highly temperature resistant lining wall elements spaced from the metal wall.
Patent
Lightweight fiber reinforced high temperature stable glass-ceramic abradable seal
John J. Brennan,Richard C. Novak +1 more
TL;DR: In this paper, a composite material suitable for use as an abradable seal is described, which comprises a high temperature stable fiber reinforced glass or glass-ceramic matrix base having at least one layer of abradably ceramic material, plasma sprayed or bonded to it.
Patent
Gas turbine stationary shroud made of a ceramic foam material, and its preparation
TL;DR: In this article, a curved stationary shroud body is made of an open-cell solid ceramic foam having ceramic cell walls with intracellular volume therebetween, tailored to provide requirement properties.
Patent
Cooled shroud for a gas turbine engine
TL;DR: A cooled shroud for a gas turbine engine comprises an annular metallic supporting member having holes therethrough for the flow of cooling air and a layered coating on its inner face.
Patent
Internal combustion chamber arrangement
TL;DR: In this paper, a combustion chamber arrangement for gas turbine propulsion units with a flame tube of ceramic material which is surrounded by a metallic wall while leaving free an intermediate space is presented, where sheet metal mounting members are arranged between the outer walls of which and the metallic walls, especially of a housing without heat contact to the parts of the flame tube that a first and a second intermediate space for peripheral partial flows of cooling air is formed.