NOZZLE GUIDE VANE WITH COMPOSITE HEAT SHIELDS

A nozzle guide vane for a gas turbine engine is disclosed herein. The nozzle guide vane includes an inner endcap, an outer endcap, and at least one airfoil that extends from the inner endcap to the outer endcap. The nozzle guide vane further includes at least one composite heat shield component adapted to shield metallic components from high temperature gasses. 1. A nozzle guide vane for a gas turbine engine , the nozzle guide vane comprisinga metallic support structure including an inner endcap formed to include an inner attachment aperture and an outer endcap formed to include an outer attachment aperture, the outer endcap spaced from the inner endcap in a radial direction,an airfoil including an aerodynamic feature shaped to redirect gasses moving through a gas path between the inner end cap and the outer endcap, an inner attachment feature that extends from the aerodynamic feature into the inner attachment aperture of the inner endcap, and an outer attachment feature that extends from the aerodynamic feature into the outer attachment aperture of the outer endcap, anda ceramic-matrix composite heat shield system adapted to shield the metallic support structure from hot gasses moving through the gas path, the ceramic-matrix composite heat shield system including an inner heat shield arranged radially between the inner endcap and the gas path and an outer heat shield comprising ceramic-matrix composite materials arranged radially between the outer endcap and the gas path.2. The nozzle guide vane of claim 1 , wherein the outer heat shield is sandwiched between the aerodynamic feature and the outer endcap and the inner heat shield is sandwiched between the aerodynamic feature and the inner endcap.3. The nozzle guide vane of claim 2 , wherein the inner heat shield is formed to include an inner locator aperture claim 2 , the outer heat shield is formed to include an outer locator aperture claim 2 , the inner attachment feature extends through the inner locator aperture ...

VANE ASSEMBLY FOR A GAS TURBINE ENGINE

A vane assembly for a gas turbine engine is disclosed herein. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil that extends from the inner platform to the outer platform. The ceramic-containing airfoil is manufactured to have radially discontinuous ribs spaced radially apart from one another between the inner platform and the outer platform.

VANE ASSEMBLIES FOR GAS TURBINE ENGINES

A vane ring for a gas turbine engine includes an outer end wall and a plurality of spars coupled to the outer end wall. The vane ring further includes an inner end wall positioned radially inward of the outer end wall and coupled to the spars. The outer and inner end walls cooperate to form a flowpath. 1. A vane ring for use in a gas turbine engine , the vane ring comprisinga plurality of metal spars, each spar including a web section having an airfoil shape, a first end connector coupled to a radially outer portion of the web section, and a second end connector coupled to a radially inner portion of the web section,a plurality of inner end wall segments positioned to function as a continuous hoop and engage the metal spars, each inner end wall segment including a first flow surface positioned to guide expanding hot gases along a flow path through the gas turbine engine and at least one locator hole sized to receive the second end connector of the metal spars, anda unitary outer end wall forming a one-piece continuous hoop, the outer end wall comprising ceramic-matrix materials and including a second flow surface positioned to cooperate with the first flow surface of the inner end wall segments to form the flow path and a plurality of locator holes sized to receive the first end wall connectors to locate the metal spars circumferentially along the outer end wall.2. The vane ring of claim 1 , further comprising a plurality of outer end caps coupled to the first end connectors and positioned to engage a radially outer surface of the outer end wall.3. The vane ring of claim 2 , wherein the outer end caps are coupled to the first end connectors by one of welding claim 2 , brazing claim 2 , a bi-cast joint claim 2 , or a fastener.4. The vane ring of claim 2 , further comprising a plurality of inner end caps coupled to the second end connectors and positioned to engage a radially inner surface of the inner end wall segments claim 2 , the outer end caps and inner end caps ...

KEYSTONED BLADE TRACK

A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track. 1. A blade-track system for a gas turbine engine , the blade-track system comprisinga plurality of blade track segments positioned circumferentially around a central axis to form a ring providing a blade track, each blade track segment comprising ceramic-matrix composite materials and shaped to extend part-way around the central axis, each blade track segment including opposing circumferential end faces and a radially outer surface, anda track biaser positioned to surround the blade track,wherein the end faces of the blade track segments are engaged with one another and the track biaser is configured to bias the blade track segments toward the central axis such that each blade track segment acts as a keystone to maintain the form of the ring.2. The blade track of claim 1 , wherein the end faces of the blade track segments are configured to engage and form a resultant radially-outward force away from the central axis against the track biaser and wherein the track biaser is positioned to engage the radially outer surface of the blade track segments to provide a radially-inward force against the blade track segments.3. The blade track of claim 2 , wherein the track biaser includes at least one unitary ring sized to surround the blade track and engage the outer surfaces of the blade track segments.4. The blade track of claim 3 , wherein the at least one unitary ring includes a first unitary ring substantially aligned with an axially-forward face of the blade track segments and a second unitary ring substantially aligned with an axially-aft face of the blade track segments.5. The blade track of claim 4 , wherein each of the blade track segments further includes a first bevel surface extending between the axially-forward face and the outer surface and a second bevel surface extending ...

TURBINE VANE WITH HEAT SHIELD

A gas turbine engine may include a body and a turbine-vane ring coupled to the body. The turbine-vane ring may include a plurality of turbine-vane assemblies.

VANE ASSEMBLY FOR A GAS TURBINE ENGINE

A vane assembly for a gas turbine engine is disclosed herein. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil that extends from the inner platform to the outer platform. The ceramic-containing airfoil is manufactured to have radially discontinuous ribs spaced radially apart from one another between the inner platform and the outer platform. 1. A vane assembly for a gas turbine engine , the assembly comprisingan inner platform and an outer platform spaced apart from the inner platform to define a gas path therebetween, anda ceramic-matrix composite airfoil that extends from the inner platform to the outer platform across the gas path, the ceramic-matrix composite airfoil formed to include a pressure side, a suction side, and a plurality of axially-aligned ribs spaced radially apart from one another between the inner platform and the outer platform that interconnect the pressure side with the suction side,wherein the ceramic-matrix composite airfoil includes (i) a core comprising ceramic-containing reinforcements and having a first tube formed to include windows and a second tube formed to include windows, and (ii) an overwrap that wraps around the core to form the pressure side and the suction side of the airfoil, andwherein the windows of the second tube are aligned with the windows of the first tube so that the plurality of axially-aligned ribs are formed by material of the first tube and the second tube arranged between the windows of the first tube and the windows of the second tube.2. The assembly of claim 1 , wherein the first tube and the second tube extend substantially all the way from the inner platform to the outer platform.3. The assembly of claim 1 , wherein the first tube is woven or braided so that the first tube does not have a seam that extends radially between the inner platform and the outer platform.4. The assembly of claim 3 , wherein the second tube is woven or braided so that the second tube ...

Dual-walled ceramic matrix composite (CMC) component with integral cooling and method of making a CMC component with integral cooling

A dual-walled ceramic matrix composite (CMC) component comprises: a CMC core having a hollow shape enclosing at least one interior channel; and a CMC outer layer overlying and spaced apart from the CMC core by a ceramic slurry-cast architecture positioned therebetween. Each of the CMC core and the CMC outer layer comprises ceramic fibers in a ceramic matrix. The CMC core further includes a plurality of through-thickness inner cooling holes in fluid communication with the at least one interior channel. The ceramic slurry-cast architecture defines a cooling fluid path over an outer surface of the CMC core that connects the interior channel(s) to an external environment of the dual-walled CMC component. The CMC outer layer may also include a plurality of through-thickness outer cooling holes in fluid communication with the cooling fluid path, thereby extending the cooling fluid path through the CMC outer layer.

Airfoil assembly with ceramic matrix composite parts and load-transfer features

An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform.

Multi-piece carrier assembly for mounting ceramic matrix composite seal segments

A turbine shroud assembly adapted for use in a gas turbine engine includes a blade track segment and a carrier. The blade track segment includes a runner that extends circumferentially partway around a central axis and an attachment post that extends radially from the runner. The carrier is coupled with the attachment post to support the blade track segment relative to the central axis.

AIRFOIL ASSEMBLY WITH CERAMIC MATRIX COMPOSITE PARTS AND LOAD-TRANSFER FEATURES

An airfoil assembly includes a vane that includes an outer platform, an inner platform, and an airfoil. The outer platform defines an outer boundary of a gas path. The inner platform is spaced apart axially from the outer platform relative to an axis and defines an inner boundary of the gas path. The airfoil extends axially between and interconnects the outer platform and the inner platform. Force loads caused by gases interacting with the airfoil are configured to be transmitted from the airfoil assembly to a case arranged around the airfoil assembly. 1. An airfoil assembly for a gas turbine engine , the airfoil assembly comprisinga ceramic matrix composite vane adapted to interact with hot gases flowing through a gas path of the gas turbine engine during use of the airfoil assembly, the ceramic matrix composite vane including an outer platform that defines an outer boundary of the gas path, an inner platform spaced apart axially from the outer platform relative to an axis to define an inner boundary of the gas path, an airfoil that extends axially between and interconnects the outer platform and the inner platform, and an outer vane mount that extends axially outward away from the outer platform,a metallic support spar that extends axially through an interior cavity formed in the ceramic matrix composite vane, anda metallic sleeve configured to receive force loads applied to the ceramic matrix composite vane by the hot gases during use of the airfoil assembly, the metallic sleeve located axially outward of the outer platform outside of the gas path, and wherein the metallic sleeve includes a sleeve body arranged around the outer vane mount of the ceramic matrix composite vane and the metallic support spar and a first load-transfer tab that extends from the sleeve body toward the outer vane mount of the ceramic matrix composite vane and engages the outer vane mount to transmit the force loads from the ceramic matrix composite vane to the metallic sleeve.2. The ...

VANE ASSEMBLY FOR A GAS TURBINE ENGINE

A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends between the inner platform and the outer platform. A reinforcement spar extends between the inner platform and the outer platform through a hollow core of the ceramic-containing airfoil. 1. (canceled)2. A vane assembly for a gas turbine engine , the vane assembly comprisingan inner platform made from a metallic material, the inner platform including an inner panel and an inner projection that extends radially outward away from the inner panel,an outer platform made from a metallic material, the outer platform including an outer panel and an outer projection that extends radially inward away from the outer panel and toward the inner platform, the outer platform spaced apart radially from the inner platform to define a gas path therebetween,a ceramic-containing airfoil that extends radially between the inner platform and the outer platform and adapted to receive aerodynamic loads during use of the gas turbine engine, the ceramic-containing airfoil formed to define a hollow core, and the ceramic-containing airfoil is arranged around the inner projection and the outer projection to locate the inner projection and the outer projection in the hollow core such that a first portion of the aerodynamic loads applied to the ceramic-containing airfoil are transferred to the inner platform through the inner projection and to the outer platform through the outer projection during use of the gas turbine engine, anda reinforcement spar made from a metallic material that extends radially between the inner platform and the outer platform through the hollow core of the ceramic-containing airfoil and the reinforcement spar supports an interior surface of the ceramic-containing airfoil such that a second portion of the aerodynamic loads applied to the ceramic-containing airfoil are ...

TURBINE VANE ASSEMBLY WITH CERAMIC MATRIX COMPOSITE COMPONENTS

Turbine vane assemblies incorporating both metallic and ceramic matrix composite materials are provided in the present disclosure. The turbine vane assemblies further include interface components that allow for differing rates of thermal expansion in the ceramic matrix composite components and the metallic components. 1. A turbine vane assembly , the assembly comprisinga ceramic matrix composite heat shield adapted to withstand high temperatures, the ceramic matrix composite heat shield shaped to include an inner end wall, an outer end wall spaced in a radial direction from the inner end wall to define a primary gas path therebetween, and an airfoil that extends from the inner end wall to the outer end wall,a metallic support structure that extends radially through the ceramic matrix composite heat shield, the metallic support structure including a first plate arranged radially inward or radially outward of the ceramic matrix composite heat shield and a spar that extends radially from the first plate through the ceramic matrix composite heat shield, andinterface components configured to that interconnect the ceramic matrix composite heat shield with the metallic support structure to allow for differing rates of thermal expansion in the ceramic matrix composite components and the metallic components, the interface components including at least one bias spring arranged radially between the ceramic matrix composite heat shield and the first plate of the metallic support structure.2. The assembly of claim 1 , wherein the at least one bias spring directly engages one of the outer end wall and the inner end wall of the ceramic matrix composite heat shield claim 1 , and the at least one bias spring directly engages the first plate.3. The assembly of claim 2 , wherein the interface components include a plurality of bias springs that each directly engages one of the outer end wall and the inner end wall of the ceramic matrix composite heat shield claim 2 , and each of the ...

Multi-piece carrier assembly for mounting ceramic matrix composite seal segments

A turbine shroud assembly includes a blade track, a multi-piece carrier and a mount assembly. The carrier includes a fore body and an aft body. Attachment pin of the mount assembly extends between fore body and aft body and through an eyelet in an attachment post of the blade track.

Turbine vane assembly with reinforced end wall joints

The present disclosure is related to turbine vane assemblies comprising ceramic matrix composite materials. The turbine vane assemblies further including reinforcements that strengthen joints in the turbine vane assemblies.

Anti-rotation feature

A blade track assembly and methods thereof includes an anti-rotation device having an arcuate body and tabs extending for engagement within an anti-rotation slot of the blade track. The anti-rotation device may be formed to include an annular shape connected at a flange of the casing to reduce spatial requirements while blocking against rotation of the blade track.

DUAL-WALLED CERAMIC MATRIX COMPOSITE (CMC) COMPONENT WITH INTEGRAL COOLING AND METHOD OF MAKING A CMC COMPONENT WITH INTEGRAL COOLING

A dual-walled ceramic matrix composite (CMC) component comprises: a CMC core having a hollow shape enclosing at least one interior channel; and a CMC outer layer overlying and spaced apart from the CMC core by a ceramic slurry-cast architecture positioned therebetween. Each of the CMC core and the CMC outer layer comprises ceramic fibers in a ceramic matrix. The CMC core further includes a plurality of through-thickness inner cooling holes in fluid communication with the at least one interior channel. The ceramic slurry-cast architecture defines a cooling fluid path over an outer surface of the CMC core that connects the interior channel(s) to an external environment of the dual-walled CMC component. The CMC outer layer may also include a plurality of through-thickness outer cooling holes in fluid communication with the cooling fluid path, thereby extending the cooling fluid path through the CMC outer layer. 1. A dual-walled ceramic matrix composite (CMC) component with integral cooling , the dual-walled CMC component comprising:a CMC core having a hollow shape enclosing at least one interior channel; anda CMC outer layer overlying and spaced apart from the CMC core by a ceramic slurry-cast architecture positioned therebetween, each of the CMC core and the CMC outer layer comprising ceramic fibers in a ceramic matrix,wherein the CMC core includes a plurality of through-thickness inner cooling holes in fluid communication with the at least one interior channel, andwherein the ceramic slurry-cast architecture defines a cooling fluid path over an outer surface of the CMC core, the cooling fluid path connecting the at least one interior channel to an external environment of the dual-walled CMC component.2. The dual-walled CMC component of claim 1 , wherein the CMC outer layer further comprises a plurality of through-thickness outer cooling holes in fluid communication with the cooling fluid path claim 1 , thereby extending the cooling fluid path through the CMC outer ...

TURBINE SHROUD WITH I-BEAM CONSTRUCTION

A turbine shroud assembly of a gas turbine engine includes a blade track having an I-beam construction including ceramic materials and defining a flow surface to guide exhaust products through a turbine section of the gas turbine engine. 1. A turbine shroud assembly comprisinga carrier arranged around at least a portion of central axis and forming a load stage, the carrier comprising metallic materials and including a forward hanger and an aft hanger, anda blade track comprising ceramic-containing materials, the blade track including a runner that extends at least partway about the central axis having a flow surface arranged to define a gas flow path and an attachment flange extending from the runner radially outward for engagement with the load stage of the carrier,wherein the blade track has an I-beam cross-sectional shape when viewed in the circumferential direction.2. The turbine shroud assembly of claim 1 , wherein the attachment flange includes a stalk attached to the runner and a pair of branches each connected with the stalk and extending in opposite directions to each form a free end.3. The turbine shroud assembly of claim 2 , wherein the branches each extend from the stalk generally parallel to the central axis.4. The turbine shroud assembly of claim 2 , wherein the blade track is formed of at least one of a number of laminate layers and a three-dimensional interlock.5. The turbine shroud assembly of claim 4 , wherein the blade track is formed of a number of laminate layers including a first set of layers forming a portion of the stalk and a portion of one of the pair of branches claim 4 , and a second set of layers forming another portion of the stalk and a portion of the other of the pair of branches.6. The turbine shroud assembly of claim 5 , wherein the number of laminate layers includes a third set of layers forming portions of each of the pair of branches.7. The turbine shroud assembly of claim 6 , wherein a fill region is formed at an intersection ...

CERAMIC MATRIX COMPOSITE ASSEMBLY WITH COMPLIANT PIN ATTACHMENT FEATURES

An assembly adapted for use in a gas turbine engine. The assembly includes 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. The attachment pin includes compliant features to distributes loads applied to the supported component. 1. A turbine shroud adapted to be mounted outward of blades included in a turbine wheel assembly and block gasses from passing over the blades without interacting with the blades , the turbine shroud comprisinga carrier segment comprising metallic materials and configured to be mounted to other metallic components within the gas turbine engine,a blade track segment comprising ceramic matrix composite materials, the blade track segment including a runner that extends partway around a central axis to face a primary gas path of the gas turbine engine and an attachment feature with an eyelet formed therethrough, andan attachment pin configured to couple the blade track segment to the carrier segment, the attachment pin including a shaft comprising metallic materials that extends through the eyelet in the attachment feature of the blade track segment and a compliant wrap that extends around the shaft along at least a portion of the shaft arranged inside the eyelet, wherein the compliant wrap has greater material compliance than the shaft so that loads applied onto the blade track segment by the attachment pin are distributed along the attachment feature of the blade track segment.2. The turbine shroud of claim 1 , wherein the attachment pin includes locator shoulders comprising metallic materials that extend out from the shaft to directly engage the attachment feature of the blade track segment.3. The turbine shroud of claim 2 , wherein the compliant wrap is arranged along a length of the attachment pin between the locator shoulders.4. The turbine shroud of claim 3 , wherein the ...

VANE ASSEMBLY FOR A GAS TURBINE ENGINE

A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A clamp mechanism couples the inner platform and the outer platform to the ceramic-containing airfoil. 1. A vane assembly for a gas turbine engine , the assembly comprisingan inner platform,an outer platform,a ceramic-containing airfoil that extends from the inner platform to the outer platform and is received in the inner platform and the outer platform so that substantially all aerodynamic loads applied to the ceramic-containing airfoil are transferred directly to the inner platform and the outer platform, anda clamp mechanism that extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil to couple the inner platform and the outer platform to the ceramic-containing airfoil while maintaining a spaced-apart relationship with the ceramic-containing airfoil so that aerodynamic loads applied to the ceramic-containing airfoil bypass the clamp mechanism.2. The vane assembly of claim 1 , wherein the clamp mechanism includes a perforated impingement tube that extends through the hollow core of the ceramic-containing airfoil to conduct cooling air into the ceramic-containing airfoil.3. The vane assembly of claim 2 , wherein the clamp mechanism includes an inner plate spaced apart from the ceramic-containing airfoil by the inner platform and an outer plate spaced apart from the ceramic-containing airfoil by the outer platform.4. The vane assembly of claim 3 , wherein the inner plate is coupled to the outer plate by a shaft that extends through the perforated impingement tube.5. The vane assembly of claim 3 , wherein the outer plate is coupled to the perforated impingement tube for movement therewith and is biased away from the inner platform by a biasing member.6. The vane ...

VANE ASSEMBLY FOR A GAS TURBINE ENGINE

A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A reinforcement spar made from a metallic material extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil. 1. A vane assembly for a gas turbine engine , the assembly comprisingan inner platform made from a metallic material,an outer platform made from a metallic material,a ceramic-containing airfoil that extends from the inner platform to the outer platform and engaged with at least one of the inner platform and the outer platform so that some aerodynamic loads applied to the ceramic-containing airfoil are transferred directly to at least one of the inner platform and the outer platform, anda reinforcement spar made from a metallic material that extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil and engages an interior surface of the ceramic-containing airfoil so that some aerodynamic loads applied to the ceramic-containing airfoil are transferred directly to at least one of the inner platform and the outer platform.2. The vane assembly of claim 1 , wherein a first end of the ceramic-containing airfoil is received in one of the inner platform and the outer platform to transfer load.3. The vane assembly of claim 2 , wherein the interior surface of the ceramic-containing airfoil that is engaged by the reinforcement spar is adjacent to a second end of the ceramic-containing airfoil.4. The vane assembly of claim 3 , wherein the reinforcement spar engages the interior surface of the ceramic-containing airfoil along half or less of the distance between the inner platform and the outer platform.5. The vane assembly of claim 3 , wherein the ceramic-containing airfoil is disengaged from the inner platform and the ...

TURBINE SHROUD ASSEMBLY WITH MULTI-PIECE SUPPORT FOR CERAMIC MATRIX COMPOSITE MATERIAL SEAL SEGMENTS

An assembly adapted for use in a gas turbine engine or other engine has a carrier component and a blade track segment. The assembly includes a mounting system for coupling the blade track segment to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine. 1. A turbine shroud segment adapted for use in a gas turbine engine , the turbine shroud segment comprisinga carrier segment comprising metallic materials,a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment that extends radially outward from the runner, anda mounting system configured to couple the blade track segment to the carrier segment, the mounting system including a brace and retaining nuts, wherein the brace includes a bracket that engages the attachment portion of the blade track segment and a plurality of shafts that extend from the bracket through the carrier segment into engagement with the retaining nuts to couple the blade track segment to the carrier segment,wherein the carrier segment includes a plurality of locating pads that each extend radially inwardly through corresponding radially-opening apertures in the brace to directly contact the blade track segment and radially locate the blade track segment relative to the brace.2. The turbine shroud segment of claim 1 , wherein the locating pads are all spaced circumferentially from one another about the central axis.3. The turbine shroud segment of claim 2 , wherein at least one locating pad is spaced axially from another locating pad along the central axis.4. The turbine shroud segment of claim 3 , wherein the plurality of locating pads includes at least three locating pads.5. The turbine shroud segment of claim 1 , wherein the bracket includes a first track-location arm that engages the ...

TURBINE SHROUD ASSEMBLY WITH SEALED PIN MOUNTING ARRANGEMENT

A shroud assembly adapted for use with a gas turbine engine includes a seal segment, a carrier, and a mount system. The seal segment extends circumferentially at least partway around an axis to define a gas path boundary of the shroud assembly. The carrier is configured to support the seal segment in position radially relative to the axis. The mount system couples the seal segment with the carrier. 1. A shroud assembly adapted for use with a gas turbine engine , the shroud assembly comprisinga seal segment comprising ceramic matrix composite materials, the seal segment including a shroud wall that extends circumferentially partway around an axis to define a gas path boundary of the shroud assembly and at least one mount post that extends radially outward away from the shroud wall,a carrier comprising metallic materials and configured to support the seal segment in position radially relative to the axis, the carrier including an outer wall that extends circumferentially at least partway about the axis, a first support arm that extends radially inward from the outer wall, and a second support arm that extends radially inward from the outer wall and spaced apart axially from the first support arm to define a cavity that receives the at least one mount post of the seal segment, anda mount system configured to couple the seal segment with the carrier, the mount system including at least one pin that extends axially through a first opening in the first support arm, a second opening in the at least one mount post, and into a third opening in the second support arm to interlock the seal segment with the carrier and a cover plate coupled with the carrier and engaged with the first support arm to close the first opening and block gases from passing into the cavity through the first opening and to block the pin from escaping through the first opening.2. The shroud assembly of claim 1 , wherein the first support arm is formed to define a retaining slot that is sized to receive ...

Turbine shroud assembly with hangers for ceramic matrix composite material seal segments

An assembly adapted for use in a gas turbine engine or other engine has a carrier component and a supported component, illustratively used as a heat shield. The assembly includes a mounting system for coupling the supported component to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine.

COMPOSITE AIRFOIL FOR A GAS TURBINE ENGINE

Stationary vanes and rotating blades of a gas turbine engine are disclosed that include airfoils formed from ceramic matrix composite materials. The airfoils include at least one layer of ceramic-containing matrix material and ceramic-containing reinforcing fibers suspended in the matrix material. A core of the airfoils is surrounded by the at least one layer of ceramic-containing fiber/matrix material. 1. An airfoil for a gas turbine engine , the airfoil comprisingan interior layer of ceramic matrix composite material having an exterior surface that faces away from a core of the airfoil and an interior surface that faces the core of the airfoil, the interior layer including a ceramic-containing matrix material and a tube of ceramic-containing reinforcing fibers suspended in the ceramic-containing matrix material, andan exterior wrap of ceramic matrix composite material bonded to the exterior surface of the interior layer, the exterior wrap including at least one sheet containing a ceramic-containing matrix material and ceramic-containing reinforcing fibers suspended in the ceramic-containing matrix material,wherein the core of the airfoil extends along an axis and the tube of ceramic-containing reinforcing fibers included in the interior layer extends all the way around the axis without forming a seam that extends along the axis.2. The airfoil of claim 1 , wherein the tube of ceramic-containing reinforcing fibers included in the interior layer includes reinforcing fibers that are woven together.3. The airfoil of claim 1 , wherein the tube of ceramic-containing reinforcing fibers included in the interior layer includes reinforcing fibers that are braided together.4. The airfoil of claim 1 , wherein the airfoil has a leading edge and a trailing edge and the exterior wrap forms a seam at the trailing edge of the airfoil that extends parallel to the axis.5. The airfoil of claim 1 , wherein the airfoil includes at least one reinforcing rib extending through the core ...

TURBINE WHEEL WITH COMPOSITE BLADED RING

A turbine wheel for use in a gas turbine engine having a bladed ring attached to a rotor disk. The bladed ring includes features to fit within slots of the rotor disk to couple the bladed ring to the rotor disk. 1. A turbine wheel for a gas turbine engine , the turbine wheel comprisinga metallic disk formed to include a slot that extends through the disk in an axial direction from a forward side to an aft side of the disk and inwardly in a radial direction from an outer radius of the disk toward a central axis, anda composite-bladed ring including a ring positioned to surround the outer radius of the disk, a key extending radially inward of the ring and positioned to engage the slot to maintain circumferential alignment of the ring with the disk during rotation of the metallic disk, and a composite blade coupled to the ring and extending radially outward from the ring.2. The turbine wheel of claim 1 , wherein the ring is unitary and the key is positioned to slide in a radial direction within the slot such that the disk may expand relative to the ring.3. The turbine wheel of claim 2 , wherein the ring is formed to include an outer radius and a thickness such that a gap is positioned between the ring and the disk to allow radial expansion of the disk relative to the ring.4. The turbine wheel of claim 2 , wherein the key has a generally rectangular shape when viewed along the central axis.5. The turbine wheel of claim 2 , wherein the ring resists centrifugal loads placed on the ring independent of the disk during rotation of the disk and composite-bladed ring about the central axis.6. The turbine wheel of claim 5 , wherein the centrifugal loads are carried as hoop stress in the ring.7. The turbine wheel of claim 1 , wherein the ring claim 1 , the key claim 1 , and the composite blade are formed as a unitary structure.8. The turbine wheel of claim 1 , further comprising at least one compliant pad having a compliance greater than the metallic disk and the composite ...

FULL HOOP BLADE TRACK WITH AXIALLY KEYED FEATURES

A turbine shroud for a gas turbine engine includes an annular metallic carrier, a blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection locates the ceramic blade track relative to the metallic carrier. 1. A turbine shroud for use in a gas turbine engine having a central axis , the turbine shroud comprisingan annular metallic carrier,a one-piece annular ceramic runner concentric with the annular metallic carrier that extends around the central axis, anda cross-key connection formed between the annular metallic carrier and the one-piece annular ceramic blade track to locate the one-piece annular ceramic runner relative to the annular metallic carrier, the cross-key connection including a plurality of keys and a plurality of corresponding keyways that receive the plurality of keys,wherein the plurality of keys extend in an axial direction from the one-piece annular ceramic runner parallel to the central axis and the plurality of corresponding keyways that are formed in the annular metallic carrier.2. The turbine shroud of claim 1 , wherein the one-piece ceramic runner comprises ceramic matrix material and ceramic-containing reinforcements suspended in the ceramic matrix material.3. The turbine shroud of claim 2 , wherein the ceramic matrix material includes silicon-carbide and the ceramic-containing reinforcements include silicon-carbide.4. The turbine shroud of claim 2 , wherein the ceramic-containing reinforcements include plies of reinforcing fabric that extends around the central axis.5. The turbine shroud of claim 2 , wherein the plurality of keys are integral with the one-piece annular ceramic runner and each of the plurality of keys comprises ceramic matrix material and ceramic-containing reinforcements suspended in the ceramic matrix material.6. The turbine shroud of claim 1 , wherein the plurality of keys extend from an aft side of the one-piece annular ceramic runner into the ...

TURBINE SHROUD

A turbine shroud for a gas turbine engine includes an annular metallic carrier and a ceramic-containing blade track. A connection is formed between the annular metallic carrier and the ceramic-containing blade track by insert pins extending through metallic carrier into the ceramic-containing blade track. 1. A turbine shroud comprisingan annular metallic carrier formed to include a plurality of apertures that extend in a radial direction through the annular metallic carrier,a blade track including a ceramic annular runner and a plurality of pin receivers that extend inwardly in a radial direction from an outer radial surface toward an inner radial surface of the ceramic annular runner, anda plurality of insert pins each arranged to extend through one of the plurality of apertures formed in the annular metallic carrier into a corresponding one of the plurality of pin receivers to locate the ceramic annular runner relative to the annular metallic carrier.2. The turbine shroud of claim 1 , wherein the ceramic annular runner includes a forward section claim 1 , an aft section spaced apart axially from the forward section claim 1 , and a midsection extending between the forward section and the aft section and the pin receivers are formed in the midsection of the ceramic annular runner.3. The turbine shroud of claim 1 , wherein the plurality of pin receivers are spaced apart from each other circumferentially around the ceramic annular runner.4. The turbine shroud of claim 1 , wherein the pin receivers extend in a radial direction partway through the ceramic annular runner from the outer radial surface toward the inner radial surface.5. The turbine shroud of claim 1 , wherein turbine shroud comprises at least three insert pins and the ceramic annular runner comprises at least three corresponding pin receivers.6. The turbine shroud of claim 1 , wherein each of the pin receivers includes an axial dimension and a circumferential dimension and the axial dimension is larger ...

COMPOSITE TURBINE VANE WITH THREE-DIMENSIONAL FIBER REINFORCEMENTS

A turbine vane made from ceramic matrix composite material and adapted for use in a gas turbine engine is disclosed in this paper. Turbine vanes in accordance with the present disclosure are made from ceramic matrix composites with three-dimensionally woven or braided reinforcing tows. 1. A turbine vane made from ceramic matrix composite material and adapted for use in a gas turbine engine , the turbine vane comprisingan in inner band configured to define a circumferentially extending inner flow path surface;an outer band configured to define a circumferentially extending outer flow path surface; andan airfoil that extends from the inner band to the outer band across a flow path defined between the inner flow path surface and the outer flow path surface,wherein the turbine vane includes a three-dimensionally woven reinforcement fibers suspended in matrix material, the three-dimensionally woven reinforcement fibers including a plurality of tows each shaped to provide at least a portion of the inner band, the outer band, and the airfoil.2. The turbine vane of claim 1 , wherein the airfoil includes a primary airfoil portion made at least in part from the three-dimensionally woven reinforcement fibers and the three-dimensionally woven fiber reinforcements of the primary airfoil portion are shaped to provide a pressure side wall and a suction side wall spaced apart from the pressure side wall to define a cooling cavity therebetween.3. The turbine vane of claim 2 , wherein the three-dimensionally woven fiber reinforcements of the primary airfoil portion are shaped to provide a rib that extends from the pressure side wall to the suction side wall through the cooling cavity.4. The turbine vane of claim 3 , wherein the rib is interrupted between the radially inner band and the radially outer band such that spaces are formed between portions of the rib.5. The turbine vane of claim 2 , wherein the airfoil includes a trailing-edge insert coupled to the primary airfoil portion ...

TURBINE SHROUD ASSEMBLY WITH MULTI-PIECE SUPPORT FOR CERAMIC MATRIX COMPOSITE MATERIAL SEAL SEGMENTS

An assembly adapted for use in a gas turbine engine or other engine has a carrier component and a blade track segment. The assembly includes a mounting system for coupling the blade track segment to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine. 1. A turbine shroud segment adapted for use in a gas turbine engine , the turbine shroud segment comprisinga carrier segment comprising metallic materials,a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment that extends radially outward from the runner, anda mounting system configured to couple the blade track segment to the carrier segment, the mounting system including (i) a brace formed to include a bracket that extends at least partway about the central axis and engages a radially-outwardly facing surface of the attachment of the blade track segment and a plurality of shafts that extend from the bracket through the carrier segment to couple the blade track segment to the carrier segment, (ii) a first clamp that extends around and engages the bracket of the brace and the attachment of the blade track segment to couple the blade track segment to the brace, and (iii) a second clamp that extends around and engages the bracket of the brace and the attachment of the blade track segment opposite the first clamp to couple the blade track segment to the brace,wherein the bracket includes a plurality of locating pads that each extend radially outward from the bracket into contact with a radially-inwardly facing surface of the carrier segment to radially locate the blade track segment.2. The turbine shroud segment of claim 1 , wherein the mounting system includes a plurality of first clamps and a plurality of second clamps and the plurality of locating pads are all ...

TURBINE SHROUD ASSEMBLY WITH MULTI-PIECE SUPPORT FOR CERAMIC MATRIX COMPOSITE MATERIAL SEAL SEGMENTS

An assembly adapted for use in a gas turbine engine or other engine has a carrier component and a blade track segment. The assembly includes a mounting system for coupling the blade track segment to the carrier component. In an illustrative embodiment, the assembly is a turbine shroud segment for blocking gasses from passing over turbine blades included in the gas turbine engine. 1. A turbine shroud segment adapted for use in a gas turbine engine , the turbine shroud segment comprisinga carrier segment comprising metallic materials,a blade track segment comprising ceramic matrix composite materials, the blade track segment formed to include a runner shaped to extend partway around a central axis and an attachment having a first radial wall that extends radially outward from the runner, a second radial wall spaced apart axially from the first radial wall that extends radially outward from the runner, and an attachment panel that extends axially between the first radial wall and the second radial wall to define a channel, anda mounting system configured to couple the blade track segment to the carrier segment, the mounting system including a brace located in the channel of the attachment and configured to distribute coupling and pressure loads applied to the blade track segment, a fastener that extends through the carrier segment and the attachment panel into the channel and mates with the brace to couple the blade track segment to the carrier segment, and a spring seal arranged between the carrier segment and the attachment of the blade track segment and engaged with the first and second radial walls of the attachment to block gases from flowing between the carrier segment and the blade track segment,wherein the carrier segment includes a plurality of locating pads that each extend radially inwardly through corresponding radially-opening apertures formed in the spring seal to directly contact the blade track segment and radially locate the blade track segment ...

Material testing system and method of use

The present disclosure relates to a material testing system for use in testing material strength of various gas turbine engine components. The material testing system provides a load force onto portions of gas turbine engine components.

TURBINE SHROUD WITH TUBULAR RUNNER-LOCATING INSERTS

A turbine shroud for a gas turbine engine includes a carrier and a blade track. The blade track includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner. The inserts extend through the carrier to couple the annular runner with the carrier. 1. A turbine shroud comprisingan annular metallic carrier arranged around a central axis of the turbine shroud and formed to include a plurality of keyways extending in a radial direction into the annular metallic carrier, anda blade track including a ceramic annular runner and a plurality of ceramic inserts extending outward in a radial direction away from the ceramic annular runner,wherein each of the plurality of ceramic inserts are tubular and are arranged to extend into a corresponding one of the plurality of keyways formed in the annular metallic carrier to locate the blade track and the annular metallic carrier relative to the central axis while allowing radial growth of the annular metallic carrier and the blade track at different rates during use of the turbine shroud.2. The turbine shroud of claim 1 , wherein the ceramic annular runner includes a forward section claim 1 , an aft section spaced apart axially from the forward section claim 1 , and a midsection extending between the forward section and the aft section and the ceramic inserts extend outwardly from the midsection of the ceramic annular runner.3. The turbine shroud of claim 1 , wherein the blade track is formed to include a sensor passage extending radially through at least one of the ceramic inserts and the ceramic annular runner.4. The turbine shroud of claim 3 , further comprising a sensor coupled to the at least one ceramic insert for movement therewith and the sensor extends radially inward through the sensor passage toward the ceramic annular runner.5. The turbine shroud of claim 4 , wherein the sensor comprises a blade-tip probe.6. The turbine shroud of claim 1 , wherein the annular metallic carrier ...

TURBINE VANE ASSEMBLY WITH REINFORCED END WALL JOINTS

The present disclosure is related to turbine vane assemblies comprising ceramic matrix composite materials. The turbine vane assemblies further including reinforcements that strengthen joints in the turbine vane assemblies. 1. A turbine vane adapted for use in an aerospace gas turbine engine , the turbine vane comprisingan airfoil comprising ceramic matrix composite materials having ceramic-containing fibers infiltrated with ceramic matrix, the airfoil shaped to redirect hot gasses moving along a primary gas path within the aerospace gas turbine engine,an end wall comprising ceramic matrix composite materials having ceramic-containing fibers co-infiltrated with ceramic matrix along with the ceramic-containing fibers of the airfoil, the end wall including a panel that extends circumferentially from the airfoil about a central axis to define a boundary of the primary gas path and a rim that extends radially from the panel outside the primary gas path along an outer surface of the airfoil, andreinforcements configured to interconnect the airfoil and the end wall and strengthen a joint therebetween, the reinforcements arranged to extend between the outer surface of the airfoil and the rim of the end wall.2. The turbine vane of claim 1 , wherein the reinforcements are provided by tufted fibers pushed from one of the airfoil and the rim of the end wall into the other of the airfoil and the rim of the end wall.3. The turbine vane of claim 1 , wherein the reinforcements are provided by rods that extend through an outer surface of the airfoil facing away from a central cavity of the airfoil and an inner surface of the rim that faces the airfoil.4. The turbine vane of claim 3 , wherein the rods comprise ceramic-containing material.5. The turbine vane of claim 3 , wherein the rods are co-infiltrated with ceramic matrix along with the airfoil and the end wall.6. The turbine vane of claim 3 , wherein the airfoil is shaped to include a leading edge claim 3 , a trailing edge claim ...

KEYSTONED BLADE TRACK

A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track. 1. A blade track for a gas turbine engine , the blade track comprising a plurality of blade track segments , each of the plurality of blade track segments shaped to extend circumferentially part-way around an axis , and the plurality of blade track segments being positioned circumferentially around the axis to form a ring , andan annular hoop arranged circumferentially around the entire ring whereby the annular hoop applies a radially-inward force toward the axis against each of the plurality of blade track segments such that each of the plurality of blade track segments acts as a keystone to maintain a form of the ring.2. The blade track of claim 1 , wherein each of the plurality of blade track segments includes opposing circumferential end faces and a radially outer surface extending between the end faces and wherein the end faces of neighboring blade track segments are engaged with one another.3. The blade track of claim 2 , wherein the annular hoop comprises an annular composite-lock structure positioned to engage the radially outer surface of each of the plurality of blade track segments.4. The blade track of claim 3 , wherein the annular composite-lock structure includes ceramic-matrix materials and at least one reinforcement fiber of ceramic-containing material suspended in the ceramic-matrix materials of the annular composite-lock structure and the annular composite-lock structure extends circumferentially around the entire ring to provide the radially-inward force toward the axis against each of the plurality of blade track segments such that each blade track segment acts as a keystone to maintain the form of the ring.5. The blade track of claim 1 , wherein each of the plurality of blade track segments includes a runner that defines a radially outer surface and a pair of ...

TURBINE SHROUD ASSEMBLY WITH SEALED PIN MOUNTING ARRANGEMENT

A shroud assembly adapted for use with a gas turbine engine includes a seal segment, a carrier, and a mount system. The seal segment extends circumferentially at least partway around an axis to define a gas path boundary of the shroud assembly. The carrier is configured to support the seal segment in position radially relative to the axis. The mount system couples the seal segment with the carrier. 1. A shroud assembly adapted for use with a gas turbine engine , the shroud assembly comprisinga seal segment including a shroud wall that extends circumferentially partway around an axis to define a gas path boundary of the shroud assembly and a first mount post that extends radially outward away from the shroud wall,a carrier configured to support the seal segment in position radially relative to the axis, the carrier including an outer wall that extends circumferentially at least partway about the axis, a first support arm that extends radially inward from the outer wall, and a second support arm that extends radially inward from the outer wall and spaced apart axially from the first support arm, anda mount system that includes a first pin and a cover plate, the first pin extends axially through a first opening in the first support arm, a second opening in the first mount post, and into a third opening in the second support arm to interlock the seal segment with the carrier, and the cover plate extending at least partway into the first opening to close the first opening and block the pin from escaping through the first opening.2. The shroud assembly of claim 1 , wherein the cover plate includes a peg that extends axially at least partway into the first opening and a panel that extends away from the peg and engages the first support arm.3. The shroud assembly of claim 2 , wherein the panel is larger than the first opening to limit movement of the cover plate into the first opening.4. The shroud assembly of claim 2 , wherein the cover plate is integrally formed with the ...

CERAMIC MATRIX COMPOSITE ASSEMBLY WITH COMPLIANT PIN ATTACHMENT FEATURES

An assembly adapted for use in a gas turbine engine. The assembly includes 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. The attachment pin includes compliant features to distributes loads applied to the supported component. 1. A turbine shroud adapted to be mounted outward of blades included in a turbine wheel assembly and block gasses from passing over the blades without interacting with the blades , the turbine shroud comprisinga carrier segment comprising metallic materials and configured to be mounted to other metallic components within the gas turbine engine,a blade track segment comprising ceramic matrix composite materials, the blade track segment including a runner that extends partway around a central axis and an attachment feature with an eyelet formed through the attachment feature, the eyelet is formed to include a chamfer around an insertion end of the eyelet, andan attachment pin configured to couple the blade track segment to the carrier segment, the attachment pin including a shaft that extends through the eyelet in the attachment feature of the blade track segment, and a compliant wrap that extends around a portion of the shaft.2. The turbine shroud of claim 1 , wherein the compliant wrap has split construction so that is can be assembled over the shaft.3. The turbine shroud of claim 1 , wherein the compliant wrap is located in the opening of the attachment feature of the blade track segment.4. The turbine shroud of claim 1 , wherein the attachment pin includes locator shoulders that extend out from the shaft and the compliant wrap is arranged along a length of the attachment pin between the locator shoulders.5. The turbine shroud of claim 4 , wherein the carrier is formed to include a mount aperture claim 4 , the attachment feature of the blade track segment is located so that the ...

Actively cooled engine assembly with ceramic matrix composite components

An actively cooled assembly adapted for use in a gas turbine engine is disclosed herein. In illustrative embodiments, the assembly includes at least one ceramic matrix composite component with an attachment feature.

TURBINE SHROUD ASSEMBLY

A turbine shroud or other assembly adapted for use in a gas turbine engine is disclosed in this paper. In illustrative embodiments, a metallic carrier included in the assembly is configured to be manufactured by casting or additive layer manufacturing. 1. A turbine shroud adapted mount outward of blades included in a turbine wheel assembly and block gasses from passing over the blades without interacting with the blades , the turbine shroud comprisinga blade track segment comprising ceramic matrix composite materials, the blade track segment including a runner that extends partway around a central axis to face a primary gas path of the gas turbine engine and an attachment feature that extends radially outward from the runner away from the central axis, anda carrier segment comprising metallic materials and configured to be mounted to other metallic components within the gas turbine engine, the carrier segment shaped to form a relief of a portion of a radially-outwardly facing side of the blade track segment such that a constant gap is formed between a portion of the runner and the attachment feature.2. The turbine shroud of claim 1 , wherein the carrier segment is formed to include a central panel and peripheral walls claim 1 , the central panel surrounded by the peripheral walls and shaped to form the relief of the portion of the radially-outwardly facing side of the blade track segment claim 1 , and the peripheral walls arranged radially outward of and along forward claim 1 , aft claim 1 , and circumferential side edges of the runner included in the blade track segment.3. The turbine shroud of claim 2 , further comprising seal elements received in radially-inwardly opening channels formed by at least some of the peripheral walls.4. The turbine shroud of claim 2 , wherein the central panel forms a primary sheet of material with a substantially constant thickness and reinforcement ribs that extend radially outwardly from the primary sheet of material to reinforce ...

Turbine engine assembly with tubular locating inserts

An assembly for a gas turbine engine includes a carrier and a supported component comprising ceramic matrix composite materials. The supported component includes an annular runner and a plurality of inserts that extend radially outward away from the annular runner. The inserts extend into the carrier to couple the supported component with the carrier.

Turbine shroud with i-beam construction

A turbine shroud assembly of a gas turbine engine includes a blade track having an I-beam construction including ceramic materials and defining a flow surface to guide exhaust products through a turbine section of the gas turbine engine.

Full hoop blade track with axially keyed features

Vane assembly for a gas turbine engine

A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A clamp mechanism couples the inner platform and the outer platform to the ceramic-containing airfoil.

Vane assembly for a gas turbine engine

A vane assembly for a gas turbine engine is disclosed in this paper. The vane assembly includes an inner platform, an outer platform, and a ceramic-containing airfoil. The ceramic-containing airfoil extends from the inner platform to the outer platform. A reinforcement spar made from a metallic material extends from the inner platform to the outer platform through a hollow core of the ceramic-containing airfoil.

Turbine wheel with composite bladed ring

Airfoil for a gas turbine and fabrication method

Full hoop blade track with axially keyed features

A turbine shroud for a gas turbine engine includes an annular metallic carrier, a blade track, and a cross-key connection formed between the annular metallic carrier and the ceramic blade track. The cross-key connection locates the ceramic blade track relative to the metallic carrier.

Keystoned blade track

A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Turbine shroud assembly with flange mounted ceramic matrix composite turbine shroud ring

A turbine assembly adapted for use with a gas turbine engine includes an outer case, a blade track segment, and a carrier. The outer case extends circumferentially at least partway around an axis of the engine. The blade track segment is configured to define a portion of a gas path of the turbine assembly. The carrier is coupled with the outer case and the blade track segment to support the blade track segment in position radially relative to the axis.

Composite keystoned blade track

A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.

Anti-rotation feature

A blade track assembly and methods thereof includes an anti-rotation device having an arcuate body and tabs extending for engagement within an anti-rotation slot of the blade track. The anti-rotation device may be formed to include an annular shape connected at a flange of the casing to reduce spatial requirements while blocking against rotation of the blade track.

Turbine shroud cartridge assembly with sealing features

A turbine shroud assembly for use with a gas turbine engine includes a blade track segment coupled to a carrier segment, and a sheet-metal seal that seals therebetween. The blade track segment includes a shroud wall that extends circumferentially partway around an axis and an attachment feature that extends radially outward from the shroud wall. The carrier is coupled with the attachment feature to support the blade track segment.

Turbine shroud segment having a seal segment perimeter seal with separated buffer cavities

A turbine shroud segment of a gas turbine engine includes a carrier segment, a blade track segment, and a plurality of seals arranged between the carrier segment and the blade track segment. The plurality of seals are arranged between the carrier segment and the blade track segment to block gases from passing between the carrier segment and the blade track segment.

Multi-piece carrier assembly for mounting ceramic matrix composite seal segments

A turbine shroud assembly includes a blade track, a multi-piece carrier and a mount assembly. The carrier includes a fore body and an aft body. Attachment pin of the mount assembly extends between fore body and aft body and through an eyelet in an attachment post of the blade track.