Patent•
Ceramic matrix composite attachment apparatus and method
03 Jul 2007-
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.
Abstract: 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. A CMC flange ( 20 A) may be formed by attaching a wedge-shaped block ( 26 ) of a ceramic material to a CMC wall structure ( 22 ), and wrapping CMC layers ( 24 ) of the wall structure ( 22 ) at least partly around the block ( 26 ), forming the flange ( 20 A) with an inner oblique face ( 34 ) and an outer face ( 35 ) normal to the wall structure. An adjacent support structure, such as a metal support ring ( 40 A), may abut the outer face ( 35 ) of the CMC flange ( 20 A) and be clamped or bolted to the CMC flange ( 20 A).
Citations
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Patent•
27 Jan 2011TL;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.
Abstract: A turbine shroud apparatus is provided for a gas turbine engine having a central axis. The apparatus includes: (a) an annular support member (14); (b) a turbine shroud (12) disposed in the support member (14), the shroud (12) being a continuous ring comprising a low-ductility material and having opposed flowpath and back surfaces, and opposed forward and aft ends; and (c) a spring (32) mounted between the support member (14) and the shroud (12) and arranged to resiliently urge the shroud (12) to a concentric position within the support member (14).
108 citations
Patent•
16 Feb 2012
TL;DR: In this paper, a composite fan case for a gas turbine engine includes a fan containment case having an outer surface, a front and a rear, which is configured to be axially aligned with a fan blade.
Abstract: A fan case for a gas turbine engine includes a composite fan containment case having an outer surface, a front and a rear. An attachment flange and a mounting ring are respectively provided on the front and the rear. A bolt attachment is supported on the outer surface. The composite fan containment case has a containment area that is configured to be axially aligned with a fan blade. A ballistic liner is arranged in the containment area.
43 citations
Patent•
29 Aug 2014
TL;DR: In this article, a gas turbine engine including an engine case, a retention block attached to the engine case and a blade outer air seal (BOAS) is described, which includes a plurality of layers formed of a ceramic matrix composite (CMC) material.
Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine including an engine case, a retention block attached to the engine case, and a blade outer air seal (BOAS). The BOAS includes a plurality of layers formed of a ceramic matrix composite (CMC) material. At least one of the plurality of layers provides a slot receiving a portion of the retention block.
40 citations
Patent•
22 Sep 2006TL;DR: In this paper, a ring segment for a turbine engine that can be used as a replacement for one or more metal components is proposed to take advantage of the properties provided by ceramic materials.
Abstract: A ceramic ring segment for a turbine engine that may be used as a replacement for one or more metal components. The ceramic ring segment may be formed from a plurality of ceramic plates, such as ceramic matrix composite plates, that are joined together using a strengthening mechanism to reinforce the ceramic plates while permitting the resulting ceramic article to be used as a replacement for components for turbine systems that are typically metal, thereby taking advantage of the properties provided by ceramic materials. The strengthening mechanism may include a bolt or a plurality of bolts designed to prevent delamination of the ceramic plates when in use by keeping the ceramic plates in compression.
37 citations
Patent•
05 May 2015TL;DR: In this article, a shroud hanger assembly is provided for a gas turbine engine with a retainer that engages a pocket formed in a shroud (50) so as to retain the shroud in a desired position relative to the hanger (32).
Abstract: A shroud hanger assembly (30) or shroud assembly (30) is provided for a gas turbine engine wherein a hanger (32) includes a radially depending and axially extending arm. The arm (45) or retainer (60) engages a pocket (56) formed in a shroud (50) so as to retain the shroud (50) in a desired position relative to the hanger (32). An aft retaining structure is provided on the hanger (32) and provides a seat for a seal structure which biases the retainer (60) so that the arm (45) of the hanger (32) maintains engagement in the shroud pocket (56). A baffle (52) may be utilized at the hanger (32) to cool at least some portion of the shroud (50).
36 citations
References
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Patent•
16 May 2003TL;DR: In this article, a hybrid vane for a gas turbine engine having a ceramic matrix composite (CMC) airfoil member bonded to a substantially solid core member is proposed.
Abstract: A hybrid vane ( 50 ) for a gas turbine engine having a ceramic matrix composite (CMC) airfoil member ( 52 ) bonded to a substantially solid core member ( 54 ). The airfoil member and core member are cooled by a cooling fluid ( 58 ) passing through cooling passages ( 56 ) formed in the core member. The airfoil member is cooled by conductive heat transfer through the bond (( 70 ) between the core member and the airfoil member and by convective heat transfer at the surface directly exposed to the cooling fluid. A layer of insulation ( 72 ) bonded to the external surface of the airfoil member provides both the desired outer aerodynamic contour and reduces the amount of cooling fluid required to maintain the structural integrity of the airfoil member. Each member of the hybrid vane is formulated to have a coefficient of thermal expansion and elastic modulus that will minimize thermal stress during fabrication and during turbine engine operation.
152 citations
Patent•
09 Sep 2002TL;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.
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.
146 citations
Patent•
14 May 2003TL;DR: In this paper, a ceramic matrix composite material (CMC) vane for a gas turbine engine was proposed, where the airfoil member and the platform member are formed separately and are then bonded together to form an integral vane component.
Abstract: A ceramic matrix composite material (CMC) vane for a gas turbine engine wherein the airfoil member (12) and the platform member (14) are formed separately and are then bonded together to form an integral vane component (10). Airfoil member and the platform member may be bonded together by an adhesive (20) after being fully cured. Alternatively, respective joint surfaces (16,18) of the green body state airfoil member and platform member may be co-fired together to form a sinter bond (30). A mechanical fastener (38) and/or a CMC doubter (42) may be utilized to reinforce the bonded joint (40). A matrix infiltration process (50) may be used to create or to further strengthen the bond.
139 citations
Patent•
17 Sep 2002TL;DR: In this article, a method of manufacturing a composite structure uses a layer of an insulating material as a mold for forming a substrate of a ceramic matrix composite (CMC) material.
Abstract: A method of manufacturing a composite structure uses a layer of an insulating material ( 22 ) as a mold for forming a substrate of a ceramic matrix composite (CMC) material ( 24 ). The insulating material may be formed in the shape of a cylinder ( 10 ) with the CMC material wound on an outer surface ( 14 ) of the cylinder to form a gas turbine combustor liner ( 20 ). Alternatively, the insulating material may be formed in the shape of an airfoil section ( 32 ) with the CMC material formed on an inside surface ( 36 ) of the insulating material. The airfoil section may be formed of a plurality of halves ( 42, 44 ) to facilitate the lay-up of the CMC material onto an easily accessible surface, with the halves then joined together to form the complete composite airfoil. In another embodiment, a box structure ( 102 ) defining a hot gas flow passage ( 98 ) is manufactured by forming insulating material in the shape of opposed airfoil halves ( 104 ) joined at respective opposed ends by platform members ( 109 ). A layer of CMC material ( 107 ) is then formed on an outside surface of the insulating material. A number of such composite material box structures are then joined together to form a vane ring ( 100 ) for a gas turbine engine.
115 citations
Patent•
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TL;DR: In this article, the leading edge of a gas turbine is attached to the center by a dove tail joint, which allows the lead edge to slide in the radial direction with respect to the centre portion while preventing movement in the axial and circumferential directions, thereby eliminating thermal stresses created by differential thermal expansion between the leading edges and the remainder of the vane.
Abstract: A vane for the turbine section of a gas turbine has an airfoil portion with leading edge, center and trailing edge portions. The leading edge portion is attached to the center portion by a dove tail joint that allows the leading edge portion to slide in the radial direction with respect to the center portion while preventing movement in the axial and circumferential directions, thereby eliminating thermal stresses created by differential thermal expansion between the leading edge portion and the remainder of the vane. An opening in the vane inner shroud that is normally sealed by a closure plate allows the leading edge portion to be readily replaced in the event of damage. The leading edge portion may be formed from a ceramic material and need not be supplied with cooling air.
79 citations