Patent Publication Number: US-10787925-B2

Title: Compliant rail hanger

Description:
CROSS REFERENCE TO RELATED APPLICATIONS 
     This application is a continuation of U.S. patent application Ser. No. 15/066,701, filed 10 Mar. 2016, which claims priority to and the benefit of U.S. Provisional Patent Application No. 62/140,663, filed 31 Mar. 2015, the disclosures of which are now expressly incorporated herein by reference. 
    
    
     FIELD OF THE DISCLOSURE 
     The present disclosure relates generally to gas turbine engines, and more specifically to turbine shrouds used in gas turbine engines. 
     BACKGROUND 
     Gas turbine engines are used to power aircraft, watercraft, power generators, and the like. Gas turbine engines typically include a compressor, a combustor, and a turbine. The compressor compresses air drawn into the engine and delivers high pressure air to the combustor. In the combustor, fuel is mixed with the high pressure air and is ignited. Products of the combustion reaction in the combustor are directed into the turbine where work is extracted to drive the compressor and, sometimes, an output shaft, fan, or propeller. Left-over products of the combustion are exhausted out of the turbine and may provide thrust in some applications. 
     Compressors and turbines typically include alternating stages of static vane assemblies and rotating wheel assemblies. The rotating wheel assemblies include disks carrying blades around their outer edges. When the rotating wheel assemblies turn, tips of the blades move along blade tracks included in static shrouds that are arranged around the rotating wheel assemblies. Such static shrouds may be coupled to an engine case that surrounds the compressor, the combustor, and the turbine. 
     Some shrouds are made up of a number of segments arranged circumferentially adjacent to one another to form a ring. Such shrouds sometimes include assembled components having different rates of expansion. Thus, the assembled components may experience areas of localized stress during heating and cooling of the assembly. 
     SUMMARY 
     The present application discloses one or more of the features recited in the appended claims and/or the following features which, alone or in any combination, may comprise patentable subject matter. 
     According to the present disclosure, a turbine shroud may include a plurality of carrier segments comprising metallic materials and arranged circumferentially adjacent to one another around an axis, and a plurality of blade track segments comprising ceramic-matrix composite materials and arranged circumferentially adjacent to one another around the axis. Each carrier segment may include a body and a bracket that extends inwardly in a radial direction from the body toward the axis. Each blade track segment may include a runner and at least one hanger that extends outwardly in the radial direction from the runner. 
     In illustrative embodiments, at least one of the hangers of each blade track segment may engage with the bracket of at least one carrier segment to couple the plurality of blade track segments to the carrier segments. The bracket of each carrier segment may be formed to include a plurality of circumferentially spaced apart fingers extending generally axially from the body and arranged to be engaged by the hangers of the blade track segments. The fingers may be configured to flex inward in the radial direction when engaged by the hangers of the blade track segments. 
     In illustrative embodiments, the turbine shroud may include a plurality of retainer segments comprising metallic materials and arranged circumferentially adjacent to one another around an axis. Each retainer segment may include a body and a bracket that extends inwardly in a radial direction from the body toward the axis. The bracket of each retainer segment may be formed to include a plurality of circumferentially spaced apart fingers extending generally axially from the body of the retainer and arranged to be engaged by the hangers of the blade track segments. The fingers may be configured to flex inward in the radial direction when engaged by the hangers of the blade track segments. 
     In illustrative embodiments, each of the carrier segments may further include a stop wall coupled to the body of the carrier segment radially inward of the plurality of fingers. Each stop wall may be spaced apart from the plurality of fingers such that a flex gap is positioned between the stop wall and the plurality of fingers. Each stop wall may be configured to engage with the plurality of fingers to block the plurality of fingers from flexing radially inward of the stop wall. 
     In illustrative embodiments, each of the fingers may include a free end spaced apart from the body and a radially outer surface extending between the body and the free end. The radially outer surface may be formed to include a contact feature positioned to contact the hangers of the blade track segments. In some embodiments, the contact feature may be a lip extending radially outward from the free end of the finger. In some embodiments, the contact feature may be a convex wall extending axially along and radially outward from the radially outer surface of the finger. In some embodiments, the contact feature may be a convex wall extending circumferentially along and radially outward from the radially outer surface of the fingers. 
     According to another aspect of the present disclosure, a turbine shroud may include a plurality of carrier segments comprising metallic materials and arranged circumferentially adjacent to one another around an axis and a plurality of blade track segments comprising ceramic-matrix composite materials and arranged circumferentially adjacent to one another around the axis. Each carrier segment may include a body and a slot formed along a radially inner portion of the body. Each blade track segment may include a runner and at least one attachment post that extends outwardly in a radial direction from the runner. 
     In illustrative embodiments, the attachment post of each blade track segment may engage with the slot of at least one carrier segment to couple the plurality of blade track segments to the carrier segments. The slot of each carrier segment may be formed to include a plurality of circumferentially spaced apart fingers and may be arranged to be engaged by the attachment posts of the blade track segments. The fingers may be configured to flex inward in the radial direction when engaged by the attachment posts of the blade track segments. 
     In illustrative embodiments, each of the slots may include a circumferentially extending outer wall, a first stop wall extending radially inward from the outer wall, and a second stop wall spaced apart from the first stop wall and extending radially inward from the outer wall. A first portion of the plurality of fingers may be positioned along an intersection of the outer wall and the first stop wall and a second portion of the plurality of fingers may be positioned along an intersection of the outer wall and the second stop wall. The first and second portions of the plurality of fingers may extend radially inward from the outer wall and toward one another. 
     In illustrative embodiments, each of the fingers may include a free end spaced apart from the first and second stop walls and an engagement surface extending between the outer wall and the free end. The first and second stop walls may be configured to engage with the plurality of fingers to block the plurality of fingers from flexing past the first and second stop walls. 
     In illustrative embodiments, the plurality of fingers may each formed to include a contact feature positioned to contact the attachment posts of the blade track segments. In some embodiments, the contact feature is a lip extending radially outward from a free end of the finger. In some embodiments, the contact feature is a convex wall extending axially along and radially outward from radially outer surface of the finger. In some embodiments, the contact feature is a convex wall extending circumferentially along and radially outward from the radially outer surface of the finger. 
     According to another aspect of the present disclosure, a method of assembling a turbine shroud is disclosed. The method may include arranging a plurality of carrier segments comprising metallic materials circumferentially adjacent to one another around an axis, each carrier segment including a body and a bracket that extends inwardly in a radial direction from the body toward the axis. The method may also include arranging a plurality of blade track segments comprising ceramic-matrix composite materials circumferentially adjacent to one another around the axis, each blade track segment including a runner and at least one hanger that extends outwardly in the radial direction from the runner. 
     In illustrative embodiments, the method may include engaging the hangers of the blade track segments with the brackets of the carrier segments to couple the blade track segments with the carrier segments. The bracket of each carrier segment may be formed to include a plurality of circumferentially spaced apart fingers extending generally axially from the body and arranged to be engaged by the hangers of the blade track segments. The fingers may be configured to flex inward in the radial direction when engaged by the hangers of the blade track segments. 
     According to another aspect of the present disclosure, another method of assembling a turbine shroud is disclosed. The method may include arranging a plurality of carrier segments comprising metallic materials circumferentially adjacent to one another around an axis, each carrier segment including a body and a slot formed along a radially inner portion of the body. The method may also include arranging a plurality of blade track segments comprising ceramic-matrix composite materials circumferentially adjacent to one another around the axis, each blade track segment including a runner and at least one attachment post that extends outwardly in the radial direction from the runner. 
     In illustrative embodiments, the method may include engaging the attachment posts of the blade track segments with the slots of the carrier segments to couple the blade track segments with the carrier segments. The slot of each carrier segment may be formed to include a plurality of circumferentially spaced apart fingers and may be arranged to be engaged by the attachment posts of the blade track segments. The fingers may be configured to flex inward in the radial direction when engaged by the attachment posts of the blade track segments. 
     According to another aspect of the present disclosure, an assembly for use in a gas turbine engine may include a support bracket consisting essentially of metallic materials and a supported component comprising ceramic-matrix composite materials. The support bracket may be formed to include a body and a plurality of spaced apart fingers extending generally axially from the body. The supported component may include a body and at least one hanger that extends from the body. 
     In illustrative embodiments, at least one of the hangers of the supported component may engage the spaced apart fingers of the support bracket and the spaced apart fingers may be configured to flex inwardly and outwardly the radial direction. 
     In illustrative embodiments, the support bracket may further include a stop wall coupled to the body radially inward of the plurality of fingers. The stop wall may be spaced apart from the plurality of fingers such that a flex gap is positioned between the stop wall and the plurality of fingers. The stop wall may be configured to engage with the plurality of fingers to block the plurality of fingers from flexing radially inward of the stop wall. 
     In illustrative embodiments, each of the fingers may include a free end spaced apart from the body and a radially outer surface extending between the body and the free end. The radially outer surface may be formed to include a contact feature positioned to contact the hangers of the blade track segments. In some embodiments, the contact feature is a lip extending radially outward from the free end of the finger. In some embodiments, the contact feature is a convex wall extending axially along and radially outward from the radially outer surface of the finger. In some embodiments, the contact feature is a convex wall extending circumferentially along and radially outward from the radially outer surface of the finger. 
     According to yet another aspect of the present disclosure, an assembly adapted for use in a gas turbine engine may include a support consisting essentially of metallic materials and a supported component comprising ceramic-matrix composite materials. The support may include a body and a slot formed along a radially inner portion of the body. The supported component may include a body and at least one attachment post that extends outwardly in a radial direction from the body. 
     In illustrative embodiments, the attachment post of each supported component may engage with the slot of the support to couple the supported component to the support. The slot of the support may be formed to include a plurality of circumferentially spaced apart fingers arranged to be engaged by the attachment posts of the supported component. The fingers may be configured to flex in the radial direction when engaged by the attachment posts of the supported components. 
     In illustrative embodiments, the support may include a circumferentially extending outer wall, a first stop wall extending radially inward from the outer wall, and a second stop wall spaced apart from the first stop wall and extending radially inward from the outer wall. A first portion of the plurality of fingers may be positioned along an intersection of the outer wall and the first stop wall and a second portion of the plurality of fingers may be positioned along an intersection of the outer wall and the second stop wall. The first and second portions of the plurality of fingers may extend radially inward from the outer wall and toward one another. 
     In illustrative embodiments, each of the fingers may include a free end spaced apart from the first and second stop walls and an engagement surface extending between the outer wall and the free end. The first and second stop walls may be configured to engage with the plurality of fingers to block the plurality of fingers from flexing past the first and second stop walls. 
     In illustrative embodiments, the plurality of fingers are each formed to include a contact feature positioned to contact the attachment posts of the blade track segments. In some embodiments, the contact feature is a lip extending radially outward from a free end of the finger. In some embodiments, the contact feature is a convex wall extending axially along and radially outward from radially outer surface of the finger. In some embodiments, the contact feature is a convex wall extending circumferentially along and radially outward from the radially outer surface of the finger. 
     These and other features of the present disclosure will become more apparent from the following description of the illustrative embodiments. 
    
    
     
       BRIEF DESCRIPTION OF THE DRAWINGS 
         FIG. 1  is a cut-away perspective view of a gas turbine engine showing that the engine includes a fan, a compressor, a combustor, and a turbine, the turbine including a turbine shroud positioned radially outward from blades of a turbine wheel assembly as shown in  FIGS. 6 and 7 ; 
         FIG. 2  is an exploded perspective view of a shroud segment included in the turbine shroud showing that a carrier segment and a retainer segment included in the turbine shroud segment each have a plurality of compliant fingers positioned to engage with a blade track segment included in the turbine shroud segment; 
         FIG. 3  is a perspective view of a portion of the retainer segment in  FIG. 2  showing that the retainer segment includes a radially extending wall, a stop wall coupled to the radially extending wall, and a flex gap positioned between the plurality of compliant fingers and the stop wall of the retainer segment; 
         FIG. 4  is a partial sectional view of the shroud segment shown in  FIG. 2  showing a hanger of the blade track segment includes a non-uniform surface and suggesting that only peaks of the non-uniform surface engage with the fingers when the gas turbine engine is in an idle state; 
         FIG. 5  is a view similar to  FIG. 4  suggesting that the hanger of the blade track segment has moved radially inward as the fingers flex during operation of the gas turbine engine to allow additional points of contact between the hanger and retainer segment; 
         FIG. 6  is a partial sectional view of the gas turbine engine of  FIG. 1  showing that the carrier segments and retainer segments couple the blade track segments to an outer case of a turbine section of the gas turbine engine and suggesting that the blade track segment at least partially defines a flow path through the turbine section; 
         FIG. 7  is a detail view of a portion of  FIG. 6  showing that a forward hanger of the blade track segment engages with fingers of the carrier segment and an aft hanger of the blade track segment engages with fingers of the retainer segment; 
         FIG. 8  is an exploded perspective view of another embodiment of a shroud segment in accordance with the present disclosure showing that the shroud segment includes a carrier segment, a retainer segment, and a blade track segment; 
         FIG. 9  is a partial sectional view of a gas turbine engine showing that the carrier segments and retainer segments couple the blade track segments to an outer case of a turbine section of the gas turbine engine and suggesting that the blade track segment at least partially defines a flow path through the turbine section; and 
         FIG. 10  is a detail view of a portion of  FIG. 9  showing that dovetailed attachment posts of the blade track segment engage with fingers included in a pair of attachment members and suggesting that the attachment members engage with the retainer to support the blade track segment. 
     
    
    
     DETAILED DESCRIPTION OF THE DRAWINGS 
     For the purposes of promoting an understanding of the principles of the disclosure, reference will now be made to a number of illustrative embodiments illustrated in the drawings and specific language will be used to describe the same. 
     An illustrative aerospace gas turbine engine  10  includes a fan  12 , a compressor  14 , a combustor  16 , and a turbine  18  as shown in  FIG. 1 . The fan  12  is driven by the turbine  18  and provides thrust for propelling an air vehicle. The compressor  14  compresses and delivers air to the combustor  16 . The combustor  16  mixes fuel with the compressed air received from the compressor  14  and ignites the fuel. The hot, high-pressure products of the combustion reaction in the combustor  16  are directed into the turbine  18  to cause the turbine  18  to rotate about a central axis A and drive the compressor  14  and the fan  12 . 
     The turbine  18  includes at least one turbine wheel assembly  11  and a turbine shroud  20  positioned to surround the turbine wheel assembly  11  as shown in  FIGS. 1 and 6 . The turbine shroud  20  is coupled to an outer case  15  of the gas turbine engine  10 . The turbine wheel assembly  11  includes a plurality of blades  13  coupled to a rotor disk for rotation therewith. The hot, high pressure combustion products from the combustor  16  are directed toward the blades  13  of the turbine wheel assemblies  11 . The blades  13  are in turn pushed by the combustion products to cause the turbine wheel assembly  11  to rotate; thereby, driving the rotating components of the compressor  14  and/or the fan  12 . 
     The turbine shroud  20  extends around the turbine wheel assembly  11  to block combustion products from passing over the blades  13  without pushing the blades  13  to rotate as suggested in  FIGS. 6 and 7 . In the illustrative embodiment, the turbine shroud  20  is made up of a number of shroud segments  22 , one of which is shown in  FIG. 2 , that extend only part-way around the central axis A and cooperate to surround the turbine wheel assembly  11 . In other embodiments, the turbine shroud  20  is annular and non-segmented to extend fully around the central axis A and surround the turbine wheel assembly  11 . In yet other embodiments, portions of the turbine shroud  20  are segmented while other portions are annular and non-segmented. 
     Each shroud segment  22  includes a carrier segment  24 , a retainer segment  26 , and a blade track segment  28  as shown in  FIG. 2 . The carrier segment  24  is configured to support the blade track segment  28  in position adjacent to the blades  13  of the turbine wheel assembly  11 . The blade track segment  28  is generally concentric with and nested into the carrier segment  24  along the central axis A of the gas turbine engine  10 . The retainer segment  26  engages both the carrier segment  24  and the blade track segment  28  to form the shroud segment  22 . 
     In the illustrative embodiment, each of the carrier segments  24  includes case hangers  32 , a retainer bracket  34 , and a forward bracket  36  as shown in  FIG. 2 . The case hangers  32  are spaced apart from one another and connected by a web  31 . The case hangers  32  couple the carrier segments  24  to the outer case  15  of the engine  10  as shown in  FIG. 6 . The retainer bracket  34  is illustratively coupled to the web  31  and positioned to engage the retainer segments  26  to couple the retainer segments  26  with the carrier segments  24  as shown in  FIG. 2 . 
     The forward bracket  36  is positioned to engage with a forward hanger  54  of the blade track segments  28  as suggested in  FIG. 2 . The forward bracket  36  includes a plurality of fingers  38  extending axially from the carrier segment  24 . Each of the fingers  38  is compliant and is configured to flex when engaged by the blade track segments  28 . 
     Each retainer segment  26  includes a hanger  42 , a body  44  coupled to the hanger  42 , and an aft bracket  46  coupled to the body  44  as shown in  FIG. 2 . The hanger  42  engages with the retainer bracket  34  of the carrier segments  24  to couple the retainer segments  26  with the carrier segments  24 . The aft bracket  46  is positioned to engage with an aft hanger  56  of the blade track segments  28 . The aft bracket  46  includes a plurality of fingers  48  extending axially from the body  44  of the retainer segments  26 . Each of the fingers  48  is configured to flex when engaged by the blade track segments  28 . 
     Each blade track segment  28  includes a runner  52 , the forward hanger  54  coupled to the runner  52 , and the aft hanger  56  coupled to the runner  52  as shown in  FIG. 2 . The forward and aft hangers  54 ,  56  extend outward from the runner  52  in a radial direction and away from one another. The runner  52  is configured to block hot gasses from passing over the blades  13  without interacting with the blades  13  when the shroud segments  22  are coupled to the outer case  15  as suggested in  FIGS. 6 and 7 . 
     The fingers  38 ,  48  of the forward and aft brackets  36 ,  46  are circumferentially spaced apart from one another as represented by the retainer segment  26  shown in  FIG. 3 . A finger gap  41  is positioned between each finger  48  to allow the fingers  48  to flex relative to one another as suggested in  FIG. 5 . Each of the fingers  48  includes a free end  43  spaced apart from the body  44  and a radially outer surface  45  extending between the body  44  and the free end  43  as shown in  FIG. 3 . 
     The radially outer surface  45  of the fingers  48  is formed to include a contact feature positioned to contact the aft hangers  56  of the blade track segments  28 . In one embodiment, the contact feature is a lip  47  extending radially outward from the free end  43  of the finger  48 . In another embodiment, the contact feature is a convex wall  49   a  extending axially along and radially outward from the radially outer surface  45  of the finger  48 . In yet another embodiment, the contact feature is a convex wall  49   b  extending circumferentially along and radially outward from the radially outer surface  45  of the finger  48 . In some embodiments, a combination of contact features are used. 
     When assembled, the aft hanger  56  of the blade track segment  28  engages with the fingers  48  of the aft bracket  46  as shown in  FIG. 4 . In the illustrative embodiment, the aft hanger  56  has a non-uniform profile after processing of the blade track segments  28 . High points  51  of the non-uniform profile engage with the fingers  48  while low points  53  are spaced from the fingers  48  during an idle state of the gas turbine engine  10 . 
     The blade track segments  28  may move radially inward during operation of the gas turbine engine  10  as shown in  FIG. 5 . The high points  51  of the non-uniform profile of the aft hanger  56  engage with the fingers  48  and cause them to flex radially inward. The low points  53  move toward the fingers  48  and additional points-of-contact  55  between the aft hanger  56  and fingers  48  are created. Accordingly, the fingers may help maintain multiple contact sites through a range of temperatures experienced during operation as components expand and contract. As such, radial loads are circumferentially distributed along the aft hanger  56 . 
     In the illustrative embodiment, the forward and aft brackets  36 ,  46  also include a stop wall  57  as represented by the retainer segment  26  shown in  FIGS. 3-5 . The stop wall  57  is spaced radially inward from the fingers  48  to define a flex gap  59  between the fingers  48  and the stop wall  57 . The stop wall  57  is positioned to block the fingers  48  from flexing radially inward of the stop wall  57 . The flex gap  59  allows the fingers  48  to flex radially inward until they engage the stop wall  57 . 
     The blade track segments  28  are illustratively formed from ceramic-containing materials as suggested in  FIGS. 4 and 5 . In some embodiments, the blade track segments  28  are formed from ceramic-matrix composite materials. The carrier segments  24  and retainer segments  26  are formed from metallic materials. In some embodiments, the carrier segments  24  and retainer segments  26  are formed as a unitary component and the hangers  54 ,  56  of the blade track segments  28  are inserted through either end to couple the blade track segments  28  with the unitary component. 
     During assembly, a plurality of carrier segments  24  are arranged circumferentially adjacent to one another around the central axis A. A plurality of blade track segments  28  are arranged circumferentially adjacent to one another around the central axis A and the forward hangers  54  are engaged with the fingers  38  as suggested in  FIG. 2 . A plurality of retainer segments  26  are arranged circumferentially adjacent to one another around the central axis A. The hangers  42  of the retainer segments  26  are engaged with the retainer brackets  34  of the carrier segments  24  and the aft hangers  56  of the blade track segments  28  are engaged with the fingers  48  of the retainer segments  26 . 
     Circumferential seal elements  21 ,  23  extend circumferentially along forward and aft sides of each shroud segment  22  as suggested in  FIG. 2 . The seal elements  21 ,  23  are illustratively rope seals. The seal elements  21  are arranged radially between the retainer segments  26  and the blade track segments  28  as shown in  FIGS. 2, 6, and 7 . The seal elements  23  are arranged radially between the carrier segments  24  and the blade track segments  28 . The seal elements  21 ,  23  block gasses from passing through radial interfaces of components included in the shroud segments  22 . In other embodiments, other types of seals may be used as seal elements  21 ,  23 . 
     The assembled shroud segments  22  are coupled to the outer case  15  as shown in  FIGS. 6 and 7 . In the illustrative embodiment, the case hangers  32  of the carrier segments  24  are coupled to a mount ring  17 . A spacer  19  is positioned between the shroud segments  22  and a portion of the mount ring  17  to restrict movement of the shroud segments  22  relative to the mount ring  17 . The mount ring  17  couples to the outer case  15 . One or more pins  90  are coupled to the outer case  15  and engage the mount ring  17  to restrict movement of the mount ring  17  relative to the outer case  15 . 
     In the illustrative embodiment, other components are positioned relative to the outer case, such as an exit  92  of the combustor  16  and a static vane assembly  94  included in the turbine  18  for example, as shown in  FIGS. 6 and 7 . The components cooperate to form a flow path  96  through the engine  10  for passing hot gasses from the combustor  16  over the blades  13  of the turbine wheel assembly  11 . In some embodiments, the static vane assembly  94  may contact the retainer segments  26  to restrict movement of the retainer segments  26  relative to the carrier and blade track segments  24 ,  28 . 
     Another turbine shroud  120  for use in a gas turbine engine  110 , as suggested in  FIGS. 9 and 10 , illustratively includes a plurality of shroud segments  122 , one of which is shown in  FIG. 8 . A turbine  118  of the engine  110  includes at least one turbine wheel assembly  111  and a turbine shroud  120  positioned to surround the turbine wheel assembly  111  as suggested in  FIGS. 9 and 10 . The turbine wheel assembly  111  includes a plurality of blades  113  coupled to a rotor disk for rotation therewith. The turbine shroud  120  extends around the turbine wheel assembly  111  to block combustion products from passing over the blades  113  without pushing the blades  13  to rotate. The turbine shroud  120  is coupled to an outer case  115  of the gas turbine engine  110 . Hot, high pressure combustion products coming from a combustor  116  are directed toward the blades  113  of the turbine wheel assemblies  111 . The blades  113  are in turn pushed by the combustion products to cause the turbine wheel assembly  111  to rotate; thereby, driving other rotating components of the engine  110 . 
     In some embodiments, each of the shroud segments  22  extend only part-way around a central axis of the engine  110  and cooperate to surround the turbine wheel assembly  111 . In other embodiments, the turbine shroud  120  is annular and non-segmented to extend fully around the central axis and surround the turbine wheel assembly  111 . In yet other embodiments, portions of the turbine shroud  120  are segmented while other portions are annular and non-segmented. 
     Each shroud segment  122  includes a carrier segment  124 , a retainer segment  126 , and a blade track segment  128  as shown in  FIG. 8 . The carrier segment  124  is configured to support the blade track segment  128  in position adjacent to the blades  113  of the turbine wheel assembly  111  as shown in  FIGS. 9 and 10 . The blade track segment  128  is generally concentric with and nested into the carrier segment  124  along the central axis of the gas turbine engine  110 . The retainer segment  126  engages both the carrier segment  124  and the blade track segment  128  to form the shroud segment  122 . 
     In the illustrative embodiment, each of the carrier segments  124  includes case hangers  132 , an aft retainer bracket  134 , and a forward retainer bracket  136  as shown in  FIG. 8 . The case hangers  132  are spaced apart from one another and connected by a web  131 . The case hangers  132  couple the carrier segments  124  to the outer case  115  of the engine  110  as shown in  FIGS. 9 and 10 . The aft retainer bracket  134  of the carrier segment  124  is illustratively coupled to the web  131  as shown in  FIG. 8 . The forward and aft retainer brackets  134 ,  136  are positioned to engage the retainer segments  126  to couple the retainer segments  126  with the carrier segments  124 . 
     Each retainer segment  126  includes an aft hanger  142 , a spacer wall  144  coupled to the aft hanger  142 , and a deck  172  coupled to the spacer wall  144  as shown in  FIG. 8 . The deck  172  is formed to include a forward hanger  146  along a forward edge of the deck  172 . The aft hanger  142  engages with the aft retainer bracket  134  of the carrier segments  124  and the forward hanger  146  engages with the forward retainer bracket  136  to couple the retainer segments  126  with the carrier segments  124 . 
     Each blade track segment  128  includes a runner  152 , a forward dovetail post  154  coupled to the runner  152 , and an aft dovetail post  156  coupled to the runner  152  as shown in  FIG. 8 . The forward and aft dovetail posts  154 ,  156  extend outward from the runner  152  in a radial direction and circumferentially along the runner  152 . The runner  152  is configured to block hot gasses from passing over the blades  113  without interacting with the blades  113  when the shroud segments  122  are coupled to the outer case  115  as suggested in  FIGS. 9 and 10 . 
     Each of the decks  172  of the retainer segments  126  are also formed to include apertures  174 ,  176  extending radially through and circumferentially along the deck  172  as shown in  FIG. 8 . The apertures  174 ,  176  are axially spaced from one another and sized to allow the dovetail posts  154 ,  156  to pass through the apertures  174 ,  176 , respectively. The dovetail posts  154 ,  156  are sized to extend radially outward of the deck  172  when the blade track segment  128  engage with the retainer segments  126  as shown in  FIG. 10 . 
     A pair of attachment members  164 ,  166  engage with the dovetail posts  154 ,  156  of the blade track segments  128 , respectively, and engage with the deck  172  of the retainer segments  126  to couple the blade track segments  128  with the retainer segments  126  as shown in  FIG. 10 . Each of the attachment members  164 ,  166  includes a web  162  and a pair of flanges  163  extending radially inward from the web  162  and along axial edges of the web  162  as shown in  FIG. 8 . 
     The attachment members  164 ,  166  are formed to include a plurality of radially extending fingers  165  as shown in  FIG. 8 . The plurality of fingers  165  are coupled circumferentially along the axial edges of the web  162  and are angled toward one another. The attachment members  164 ,  166  are further formed to include a plurality of slots  167  extending axially across the attachment members  164 ,  166  and positioned between circumferentially adjacent fingers  165 . 
     The fingers  165  of the attachment members  164 ,  166  are sized and positioned to engage with the dovetail posts  154 ,  156  of the blade track segments  128  as shown in  FIG. 10 . Each of the fingers  165  is configured to flex radially inward when engaged by the blade track segments  128 . In some embodiments, the flanges  163  are configured to block the fingers  165  from flexing axially forward or aft of the flanges  163 . The fingers  165  are allowed to flex until they engage the flanges  163 . The fingers  165  are also configured to block the dovetail posts  154 ,  156  form passing out of the attachment members  164 ,  166  in a radial direction. 
     In some embodiments, the fingers  165  are formed to include a contact feature positioned to contact the dovetail posts  154 ,  156  of the blade track segments  128 . In one embodiment, the contact feature is a circumferentially extending lip positioned between the fingers  165  and the dovetail posts  154 ,  156 . In another embodiment, the contact feature is a convex wall extending axially along and radially outward from the finger  165 . In yet another embodiment, the contact feature is a convex wall extending circumferentially along and radially outward from the finger  165 . In some embodiments, a combination of contact features are used. 
     During assembly, the dovetail posts  154 ,  156  of the blade track segments  128  pass through the apertures  174 ,  176  of the retainer segments  126  as suggested in  FIG. 10 . The attachment members  164 ,  166  slide over and engage the dovetail posts  154 ,  156  to couple the blade track segments  128  with the retainer segments  126 . A plurality of retainer segments  126  are arranged circumferentially adjacent to one another around the central axis of the engine  110 . In some embodiments, the blade track segments  128  are coupled to the retainer segments  126  after arranging the retainer segments  126  around the central axis. 
     The hangers  142 ,  146  of the retainer segments  126  are engaged with the retainer brackets  134 ,  136  of the carrier segments  124  as shown in  FIG. 10 . In the illustrative embodiment, circumferential seal elements  121 ,  123  extend circumferentially along forward and aft sides of each shroud segment  122  to block gasses from passing through radial interfaces of components included in the shroud segments  122 . In the illustrative embodiment, one or more keys  186  are positioned to extend through apertures  182  formed in the carrier segments  124  and into recesses  184  formed in the retainer segments  126  as suggested in  FIG. 8 . The keys  186  maintain circumferential positioning of the retainer segments  126  relative to the carrier segments  124 . 
     The assembled shroud segments  122  are coupled to the outer case  115  as shown in  FIGS. 9 and 10 . In the illustrative embodiment, the case hangers  132  of the carrier segments  124  are coupled to the outer case. One or more pins  190  are coupled to the outer case  115  and engage the carrier segments  124  to restrict movement of the carrier segments  124  relative to the outer case  115 . 
     In the illustrative embodiment, other components are positioned relative to the outer case, such as an exit  192  of the combustor  116  and a static vane assembly  194  included in the turbine  118  for example, as shown in  FIGS. 9 and 10 . The components cooperate to form a flow path  196  through the engine  110  for passing hot gasses from the combustor  116  over the blades  113  of the turbine wheel assembly  111 . In some embodiments, the static vane assembly  194  may contact the retainer segments  126  to restrict movement of the retainer segments  126  relative to the carrier segments  124 . 
     The blade track segments  128  are illustratively formed from ceramic-containing materials as suggested in  FIGS. 9 and 10 . In some embodiments, the blade track segments  128  are formed from ceramic-matrix composite materials. The carrier segments  124 , retainer segments  126 , and attachment members  164 ,  166  are illustratively formed from metallic materials. In some embodiments, the carrier segments  124  and retainer segments  126  are formed as a unitary component. In some embodiments, the carrier segments  124  or the retainer segments  126  are formed to include dovetail slots having the fingers  165  positioned therein for engaging the dovetail posts  154 ,  156  of the blade track segments  128 . In some embodiments, the dovetail posts  154 ,  156  and apertures  174 ,  176  are formed to extend axially instead of circumferentially. 
     While the illustrative embodiment shows a turbine shroud assembly, the teaching of the present disclosure are not limited to turbine shrouds. Rather, it is contemplated that metallic hangers with compliant fingers (like hanger  54  having compliant fingers  38 ) may be used to support ceramic-containing components (like carrier segments  24 ) in other assemblies throughout a gas turbine engine. In one example, it is contemplated that ceramic-containing combustion liner tiles may be supported by metallic hangers having compliant fingers. In another example, it is contemplated that ceramic-containing exhaust shields may be supported by metallic hangers having compliant fingers. Accordingly, any assembly within a gas turbine engine having features as described herein are contemplated and subsequently enabled by the present disclosure. 
     While the disclosure has been illustrated and described in detail in the foregoing drawings and description, the same is to be considered as exemplary and not restrictive in character, it being understood that only illustrative embodiments thereof have been shown and described and that all changes and modifications that come within the spirit of the disclosure are desired to be protected.