Patent
Impingement tubes for CMC seal segment cooling
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TLDR
In this paper, a turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments, and an impingement tube is used to direct cooling air onto the blade track segments.Abstract:
A turbine shroud adapted for use in a gas turbine engine includes a plurality of metallic carrier segments and a plurality of blade track segments mounted to corresponding metallic carrier segments. Impingement tubes direct cooling air onto the blade track segments to cool the blade track segments when exposed to high temperatures in a gas turbine engine.read more
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Patent
Turbine shroud including plurality of cooling passages
TL;DR: In this paper, the turbine shrouds for turbine systems are disclosed, including a first cooling passage extending within the unitary body, and a plurality of impingement openings formed through the outer surface of the turbine body to fluidly couple the cooling passage to the cooling chamber.
Patent
Method and system for cooling fluid distribution
TL;DR: In this article, a method of controlling a clearance gap in a rotatable machine and a cooling fluid distribution system is presented, which includes a component to be cooled having a body extending along a longitudinal centerline of the component and including a radially outer surface at least partially circumscribing the longitudinal center line.
Patent
Attachment block for blade outer air seal providing convection cooling
Ken F. Blaney,Clark Thomas E +1 more
TL;DR: In this article, a gas turbine engine includes a compressor section and a turbine section, and the turbine section is rotatable about an axis of rotation, and a blade outer air seal is positioned radially outwardly of a radially outer tip of the at least one turbine blade.
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Ceramic matrix composite assembly with compliant pin attachment features
TL;DR: In this paper, a support component comprising metallic materials, a supported component comprising ceramic matrix composite materials, and an attachment pin configured to couple the supported component to the support component is presented.
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Actively cooled engine assembly with ceramic matrix composite components
TL;DR: In this paper, an actively cooled assembly adapted for use in a gas turbine engine is described, and the assembly includes at least one ceramic matrix composite component with an attachment feature, and it is shown that the component can be attached to the turbine.
References
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Patent
Ceramic matrix composite component for a gas turbine engine
TL;DR: 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.
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
Blade outer seal with micro axial flow cooling system
Dmitriy A. Romanov,Jeremy Drake +1 more
TL;DR: A turbine blade outer air seal assembly includes a hot side exposed to a combustion hot gas flow, and a back side that is exposed to an external supply of cooling air as mentioned in this paper, where a plurality of pedestals within each cavity disrupts cooling air flow to increase heat absorption capacity and to increase the surface area capable of transferring heat from the hot side.
Patent
Gas turbine high temperature turbine blade outer air seal assembly
TL;DR: A turbine shroud assembly includes forward and aft hangers, an axisymmetric plenum assembly, ceramic shroud segments, ceramic spacers, and front and aft rope seals.
Patent
Turbine engine ring seal
TL;DR: In this article, a ring seal for a turbine engine can be made up of a plurality of circumferentially abutted ring seal segments, each ring seal segment can comprise of individual channels and can be positioned such that the aft span of one channel can substantially abut the forward span of another channel.