Patent•
Turbine ring assembly
01 Mar 2010-
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.
Abstract: 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. Each ring sector includes a first portion forming an annular base with an inside face defining an 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 support structure. The ring sectors present a section that is substantially π-shaped and the ends of the tabs are held without radial clearance by the ring support structure. The tabs can have a free length in meridian section that is not less than three times their mean width.
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10 Dec 2012TL;DR: In this paper, the paths of the first and second woof threads intersect in at least one transition area (18) extending into the fiber structure from the base of the disconnection, the transition area extending over a distance greater than the pitch (p) between adjacent warp columns in the woof direction.
Abstract: In a fiber structure woven into a single part by means of three-dimensional weaving, first woof threads connect therebetween warp thread layers from a first portion (1) of the fiber structure (10), which are adjacent to a disconnection (16), with warp thread layers from a second portion (14) of the fiber structure, which are located beyond the disconnection, and second woof threads connect therebetween warp thread layers from the second portion (14) of the fiber structure, which are adjacent to the disconnection, with warp thread layers from the first portion (12) of the fiber structure, which are located beyond the disconnection, such that the paths of the first and second woof threads intersect in at least one transition area (18) extending into the fiber structure from the base of the disconnection, the transition area extending over a distance greater than the pitch (p) between adjacent warp columns in the woof direction.
12 citations
Patent•
16 Mar 2016
TL;DR: In this article, a turbine ring assembly comprising a plurality of ring sectors made from ceramic matrix composite material and a ring support structure is described, each ring sector having a part forming an annular base with an inner face defining the inner face of the turbine ring and an outer face from which at least two parts forming lugs (9a, 9b) extend.
Abstract: The invention concerns a turbine ring assembly comprising a plurality of ring sectors (1) made from ceramic matrix composite material and a ring support structure (2), each ring sector (1) having a part forming an annular base (5) with an inner face (6) defining the inner face of the turbine ring and an outer face (8) from which at least two parts forming lugs (9a; 9b) extend, the ring support structure (2) comprising at least two attachment lugs (11a; 11b) extending radially, the lugs (9a; 9b) of each ring sector (1) gripping the attachment lugs (11a; 11b) of the ring support structure (2) at least at the inner radial ends (14a; 14b) of said attachment lugs (11a; 11b).
11 citations
Patent•
10 Mar 2016TL;DR: A gas turbine engine assembly includes a supporting component and a supported component as mentioned in this paper, which includes features engaged by the supported component, and the supporting component comprises ceramic-containing materials, such as ceramic-coated materials.
Abstract: A gas turbine engine assembly includes a supporting component and a supported component. The supporting component includes features engaged by the supported component. The supported component comprises ceramic-containing materials.
10 citations
Patent•
23 Jun 2015TL;DR: An arcuate panel for a thermal control assembly includes an arcuate base, at least one axially extending panel header sealingly attached to a radially outwardly facing surface of the panel base, a plenum therebetween, one or more spray tubes or channels depending radially inwardly from the column base and in fluid communication with the plenum, and radially outerly biasing spring mounted on or attached to the radially internally facing surface as mentioned in this paper.
Abstract: An arcuate panel for a thermal control assembly includes an arcuate panel base, at least one axially extending panel header sealingly attached to a radially outwardly facing surface of the panel base, a plenum therebetween, one or more spray tubes or channels depending radially inwardly from the panel base and in fluid communication with the plenum, and radially outwardly biasing spring means mounted on or attached to the radially inwardly facing surface of the panel base. The panel may include at least one set of clockwise and counter-clockwise hinge wings attached to clockwise and counter-clockwise ends of the panel base, axial positioning means, and circumferential positioning means. The axial positioning means may include a circular row of spring clips mounted on the panel base. A hoop of arcuate panels pivotably attached by hinges may encircle a portion of a casing compressing leaf springs against rings of the casing.
9 citations
Patent•
16 Feb 2018
TL;DR: A turbine ring assembly comprises a plurality of ring sectors (10) made from a ceramic matrix composite material forming a turbine ring (1) and a ring support structure (3) comprising two annular flanges (32, 36), each ring sector having two lugs (14, 15) held respectively between the two ANNULAR flanges as mentioned in this paper.
Abstract: A turbine ring assembly comprises a plurality of ring sectors (10) made from a ceramic matrix composite material forming a turbine ring (1) and a ring support structure (3) comprising two annular flanges (32, 36), each ring sector (10) having two lugs (14, 15) held respectively between the two annular flanges (32, 36) of the ring support structure (3). The two annular flanges (32, 36) of the ring support structure (3) apply stress to the lugs (14, 16) of the ring sectors (10). One (36) of the flanges of the ring support structure (3) is elastically deformable in the axial direction (DA) of the turbine ring (1). The turbine ring assembly further comprises a plurality of stops (40; 41) engaged both in the annular flanges (32; 36) of the ring support structure (3) and the lugs (14; 16) of the ring sectors (10) facing the annular flanges (32; 36).
8 citations
References
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Patent•
21 Jun 2006
TL;DR: In this article, a woven fibrous structure embodied in one piece, used for producing a composite material part and comprising an internal part or a core (72) and a part adjacent to the external surface thereof or a skin (74, 76), is formed by three-dimensional core weaving with at least one weave selected from interlock and multilayer weaves and by skin weaving with a weave which differs from the core weave and selected from a multi-layer weave and a two-dimensional weave.
Abstract: A woven fibrous structure embodied in one piece, used for producing a composite material part and comprising an internal part or a core (72) and a part adjacent to the external surface thereof or a skin (74, 76), is formed by three-dimensional core weaving with at least one weave selected from interlock and multilayer weaves and by skin weaving with a weave which differs from the core weave and selected from a multilayer weave and a two-dimensional weave. It can be also formed by three-dimensional weaving with at least one core interlock weave (72) and weaving with a fabric-, satin or skin twill-type weave, wherein skin weaving is of a multilayer or two-dimensional type. .
162 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•
20 May 1997TL;DR: In this paper, a ring seal is provided for sealing a joint between a turbine blade tip shroud and a mounting structure where an annular gap is formed having an "L" shaped cross section, the ring seal having a "C" shaped configuration and one of the legs of the "C", extending within an axial component of the gap.
Abstract: A seal assembly for a turbine blade tip shroud including a one-piece bent metallic sheet inter-segment seal having an axial component and a vertical component adapted to fit in a groove formed in the end walls of each shroud segment, wherein the shroud segment has a plateform and radially extending ribs, and the seal fits tightly in the groove providing an axial an a radial component to the seal. A ring seal is also provided for sealing a joint between the shroud and a mounting structure where an annular gap is formed having an "L" shaped cross section, the ring seal having a "C" shaped configuration and one of the legs of the "C" extending within an axial component of the "L" shaped gap. The leg has a wave pattern with the peaks of the wave in contact with opposite radial walls of the axial component of the gap for creating a gas seal at the joint.
144 citations
Patent•
19 Dec 1974TL;DR: In this paper, a shroud closely surrounding a high thermal inertia rotor is provided with a support structure having low thermal inertia characteristics, which is selectively exposed to different temperature mediums during transient operation by way of a thermal actuated valve so as to cause a rapid growth thereof during periods of engine acceleration and a slow shrinkage thereof during deceleration of the engine.
Abstract: A shroud closely surrounding a high thermal inertia rotor is provided with a support structure having low thermal inertia characteristics. The support structure is selectively exposed to different temperature mediums during transient operation by way of a thermal actuated valve so as to cause a rapid growth thereof during periods of engine acceleration and a slow shrinkage thereof during periods of deceleration of the engine. In this manner the clearance relationship between the shroud and enclosed rotor is maintained at a minimum during periods of steady-state and transitional operation to thereby increase the efficiency of the combination.
141 citations
Patent•
22 Nov 1976TL;DR: In this article, a high temperature turbine shroud assembly for an aircraft gas turbine engine comprising a plurality of arcuate ceramic blocks arranged in a ring is presented, supported by a pair of annular support members which retain the blocks in the assembly.
Abstract: A high temperature turbine shroud assembly for an aircraft gas turbine engine comprising a plurality of arcuate ceramic blocks arranged in a ring. The blocks are supported by a pair of annular support members which retain the blocks in the assembly. Spring-like fingers associated with the support members apply a preloaded force against a pair of slanted dovetail surfaces on the blocks to force the blocks against rigid stops formed upon the annular support members, thereby establishing their proper radial position within the assembly. The preload applied by the fingers accommodates the thermal expansion differences between the ceramic blocks and the metallic support members. In an alternative embodiment, the blocks are retained between cooperating rigid legs extending from the annular support members and wedged radially inwardly into position by a preloaded spring contacting the back side of the blocks. Heat transfer between the blocks and metallic support members is minimized by providing point or line contact between components, thus reducing the contact area available for heat conduction.
118 citations