CERAMIC MATRIX COMPOSITE COMPONENTS WITH INSERTS

Abstract

A gas turbine engine is disclosed that includes a compressor, a combustor, and a turbine. The turbine includes a turbine shroud having a blade track formed from a ceramic matrix composite material. The combustor includes a combustor liner formed from one or more ceramic matrix composite tiles.

Description

CROSS REFERENCE TO RELATED APPLICATIONS

This application claims priority to and the benefit of U.S. Provisional Patent Application No. 62/037,879, filed 15 Aug. 2014, the disclosure of which is now expressly incorporated herein by reference.

TECHNICAL FIELD:

The present invention generally relates to gas turbine engines, and more particularly, but not exclusively, to ceramic-containing components used in gas turbine engines.

BACKGROUND

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 the air/fuel mixture is ignited. Products of the combustion reaction in the combustor are directed into the turbine where work is extracted to drive various components of the gas turbine engine. In operation, ceramic-containing components of both the combustor and the turbine are exposed to hot, high-pressure air that results from the combustor reaction.

Holes are sometimes formed in ceramic-containing components of the combustor and the turbine that are exposed to the combustion reaction products. Such holes can conduct cooling air or accommodate the passage of fasteners through a ceramic-containing component. Forming holes directly into ceramic-containing components, however, can present complications. Namely, holes formed directly into ceramic-containing components can expose environmentally sensitive portions of the ceramic-containing components to the combustion reaction products, which may result in the degradation of the ceramic-containing components over time.

SUMMARY

The present disclosure may comprise one or more of the following features and combinations thereof.

According to one aspect of the present disclosure, a turbine shroud adapted for use in a gas turbine engine may include a blade track made from ceramic matrix composite materials and an insert. The blade track may be formed to include an aperture extending through at least a portion of the blade track. The insert may be formed to include a passageway that extends through the aperture to conduct gasses through the aperture while blocking gasses from interacting with surfaces of the blade track that define the aperture.

In some embodiments, the insert may include a liner that forms the passageway and a retention flange that extends outwardly from the liner along a side of the blade track that extends away from the aperture to block movement of the liner through the aperture away from the side of the blade track. The aperture formed in the blade track may be a round bore that extends along an axis, and the passageway formed in the insert may be coaxial with the aperture. The liner may have an outer diameter that is greater than a diameter of the aperture so that the insert is interference fit with the blade track. The turbine shroud may also include a bond layer between the liner and a side wall that defines the aperture to couple the insert to the blade track. The bond layer may be made of silicon-containing braze material. The bond layer may be made of a silicon-containing cement material. The insert may be a monolithic component made from a substantially homogenous material. The material may be silicon carbide, or the material may be one of the following: aluminum oxide, zirconium oxide, or rare earth oxide. The material may be a rare earth silicate, or the material may be one of the following: a rare earth aluminate, an alkaline aluminosilicate, or mullite.

According to another aspect of the present disclosure, a combustor adapted for use in a gas turbine engine may include a shell, a liner tile made from ceramic matrix composite materials, and an insert. The shell may be made from metallic materials. The liner tile may be coupled to the shell and formed to include an aperture extending through at least a portion of the liner tile. The insert may be formed to include a passageway that extends through the aperture to shield surfaces of the liner tile that define the aperture.

In some embodiments, the turbine shroud may further include a fastener that extends through the passageway to couple the liner tile to the shell. The insert may include a liner that forms the passageway and a retention flange that extends outwardly from the liner along a side of the liner tile that extends away from the aperture to block the liner from moving through the aperture away from the side. The aperture formed in the liner tile may be a round bore that extends along an axis and the passageway formed in the insert may be coaxial with the aperture.

According to yet another aspect of the present disclosure, an assembly adapted for use in a gas turbine engine may include a component made from ceramic matrix composite materials and an insert. The component may be formed to include an aperture extending through the component from a relatively-high pressure side of the component to a relatively-low pressure side of the component. The insert may be formed to include a passageway that extends through the aperture to conduct gasses through the aperture from the relatively-high pressure side of the component to the relatively-low pressure side of the component while blocking gasses from interacting with surfaces of the component that define the aperture.

In some embodiments, the insert may include a liner that forms the passageway and a retention flange that extends outwardly from the liner along the relatively-high pressure side of the component to block the liner from moving through the aperture toward the relatively-low pressure side of the component. The aperture formed in the component may be a round bore that extends along an axis and the passageway formed in the insert may be coaxial with the aperture. The assembly may further include a fastener that extends through the passageway to couple the component to another part of the assembly.

BRIEF DESCRIPTION OF THE FIGURES

FIG. 1 is a cut-away perspective view of a gas turbine engine;

FIG. 2 is a detail view of a portion of a turbine included in the gas turbine engine of FIG. 1 showing an insert shielding a ceramic turbine component along a hole formed in the component;

FIG. 3 is a cross-sectional view of the portion of the turbine shown in FIG. 2;

FIG. 4 is an exploded perspective assembly view of the ceramic turbine component and the insert included in the portion of the turbine shown in FIGS. 2-3;

FIG. 5 is a cross-sectional view of a portion of a combustor included in the gas turbine engine of FIG. 1;

FIG. 6 is a detail view of components included in a portion of the combustor of FIG. 5;

FIG. 7 is a cross-sectional view of a portion of another combustor adapted for use in the gas turbine engine of FIG. 1; and

FIG. 8 is a detail view of components included in a portion of the combustor of FIG. 7.

DETAILED DESCRIPTION OF THE ILLUSTRATIVE EMBODIMENTS

For the purposes of promoting an understanding of the principles of the invention, reference will now be made to the embodiments illustrated in the drawings and specific language will be used to describe the same. It will nevertheless be understood that no limitation of the scope of the invention is thereby intended. Any alterations and further modifications in the described embodiments, and any further applications of the principles of the invention as described herein are contemplated as would normally occur to one skilled in the art to which the invention relates.

Referring now to FIG. 1, a cut-away view of an illustrative aerospace gas turbine engine 10 is shown. The gas turbine engine 10 includes a compressor 12, a combustor 14, and a turbine 16, each of which is surrounded and supported by a metallic case 18. The compressor 12 is configured to increase the pressure and the temperature of atmospheric air and to deliver the air at the increased pressure and temperature to the combustor 14. The combustor 14 mixes the air with fuel, ignites the air/fuel mixture, and delivers the combustion products (i.e., hot, high-pressure gases) to the turbine 16. The turbine 16 converts the combustion products to mechanical energy (i.e., rotational power) that drives the compressor 12 and an output shaft 21. Left-over combustion products from the turbine 16 may be discharged to a low pressure air stream, thereby producing thrust.

The turbine 16 includes static turbine vane rings 20, 22 and a turbine wheel assembly 23 having turbine blades 24 positioned between the vane rings 20, 22 as shown in FIG. 3. The turbine vane assemblies 20, 22 extend across the flow path of the combustion products delivered from the combustor 14 to the turbine 16. The static turbine vane assemblies 20, 22 direct the combustion products entering and exiting the turbine wheel assembly 23. The turbine blades 24 are pushed by the combustion products to cause the turbine wheel assembly 23 to rotate.

Referring now to FIGS. 2-3, a magnified perspective view of a portion of a turbine shroud 26 included in the turbine 16 is shown. The turbine shroud 26 blocks combustion products from passing over the turbine blades 24 without pushing the blades 24 to cause rotation of the turbine wheel assembly 23. The turbine shroud 26 includes a turbine blade track 28 and a metallic support ring 30 as shown in FIGS. 2-3.

The turbine blade track 28 is illustratively constructed of a ceramic matrix composite material. In one example, the ceramic matrix composite material may include silicon-carbide fibers formed into fabric sheets and a silicon-carbide matrix. In another example, the ceramic matrix composite material may include another ceramic-based material that including reinforcing fibers and a matrix material.

The turbine blade track 28 extends circumferentially to surround the turbine wheel assembly 23 to directly block combustion products delivered to the turbine 16 from passing over the turbine blades 24 as suggested in FIGS. 2-3. Combustion products allowed to pass over the turbine blades 24 of the turbine wheel assembly 23 do not cause the blades 24 to rotate, thereby contributing to lost performance within the engine 10.

Cooling apertures 46, sometimes called cooling holes, are formed in the turbine blade track 28 to conduct cooling gasses to hot portions of the turbine blade track 28 as shown in FIGS. 2 and 3. The apertures 46 are illustratively machined into the blade track 28 after the blade track 28 has been coated so that a side wall 47 defining the aperture 46 is uncoated and may be susceptible to chemical interaction with cooling gases passing through the apertures 46. Inserts 48 are positioned in the apertures 46 to shield the side walls 47 of the apertures 46 from cooling gases moving through the apertures 46 thereby blocking chemical interactions between the turbine blade track 28 and cooling gases moving through the apertures 46.

The metallic support ring 30 is coupled to the metallic case 18 as shown in FIGS. 2-3. The metallic support ring 30 extends circumferentially to surround the turbine blade track 28 and support the blade track 28 relative to the metallic case 18. The metallic support ring 30 includes a pair of axially-extending ledges 32 configured to engage the blade track 28 as shown in FIGS. 2-3.

The turbine blade track 28 includes a blade track runner 34 and a pair of hangers 36 as shown in FIGS. 2 and 3. Combustion products delivered to the turbine 16 cause the plurality of turbine blades of the turbine wheel assembly to rotate along the blade track runner 34. Each of the pair of hangers 36 is interconnected with the blade track runner 34 and extends generally radially-outwardly therefrom as shown in FIGS. 2-3.

The turbine blade track 28 is coupled to the metallic support ring 30 such that the pair of hangers 36 of the blade track 28 engage the pair of ledges 32 of the metallic support ring 30 as shown in FIGS. 2-3. As such, the pair of hangers 36 and the pair of ledges 32 cooperate to form a retention system when the turbine blade track 28 and the metallic support ring 30 are installed within the metallic case 18.

Each of the pair of hangers 36 includes a forward surface 40 and an aft surface 42 opposite the forward surface 40 as shown in FIG. 3. The hangers 36 further cooperate with the runner 34 and the support ring 30 to define an interior region 44 as shown in FIGS. 2-4. The forward surface 40 of the forward hanger 36 is exposed to a higher pressure than the aft surface 42. As such, the forward surface 40 is referred to herein as a relatively-high pressure side of the blade track 28, and the aft surface 42 is referred to herein as a relatively-low pressure side of the blade track 28.

One of the hangers 36 of the turbine blade track 28 is formed to include the aperture 46 having a diameter D as shown in FIG. 4. The aperture 46 is illustratively a round bore that extends along an axis 45. In other embodiments, the aperture 46 may have an oval, rectangular, or other shape. The aperture 46 extends along an axis 45 through the surfaces 40, 42 into the interior region 44. An insert 48 is positioned in the aperture 46 such that the insert 48 extends from the forward surface 40 to the aft surface 42. The insert 48 blocks gasses communicated from the relatively-high pressure side to the relatively-low pressure side from interacting with the side wall 47 that defines the aperture 46.

The insert 48 includes a liner 50 and a retention flange 52 coupled to and extending outwardly from the liner 50 as shown in FIGS. 2-4. The retention flange 52 illustratively has a cylindrical shape and an outer diameter D1 that is greater than the diameter D of the aperture 46. The liner 50 illustratively has a cylindrical shape and an outer diameter D2 that is approximately equal to the diameter D of the aperture 46 and less than the diameter D1. As such, the liner 50 is sized to be received in the aperture 46.

The insert 48 is positioned in the aperture 46 such that the liner 50 is entirely received in the aperture 46 as shown in FIGS. 2-3. In addition, the insert 48 is positioned in the aperture 46 such that the retaining flange 52 engages the forward surface 40. Engagement between the retaining flange 52 and the planar surface 40 blocks movement of the liner 50 through the aperture 46 and away from the relatively-high pressure side/toward the relatively-low pressure side of the aperture 46.

The retaining flange 52 is illustratively sized to withstand pressure from the hot, high-pressure gases that is applied to the relatively-high pressure side of the blade track 28. Specifically, the retaining flange 52 has a uniform thickness that resists shearing of the retaining flange 52 when pressure is applied to the relatively-high pressure side of the blade track 28. In other embodiments, the retaining flange 52 may be tapered or chamfered.

The insert 48 is formed to include a passageway 54 that extends through the liner 50 and the retaining flange 52 when the insert 48 is positioned in the aperture 46 as shown in FIG. 3. The passageway 54 extends along the axis 45 so that the passageway 54 and the aperture 46 coaxially extend along the axis 45. In operation, when the insert 48 is positioned in the aperture 46, cooling gases are conducted through the passageway 54. As such, the gasses interact with interior surfaces (not shown) of the liner 50 and the retaining flange 52 included in the insert 48 rather than the side wall 47 of the aperture 46.

Referring now to FIG. 3, the insert 48 is illustratively a monolithic component (i.e., the liner 50 and the retaining flange 52 are formed as a single, unitary, and integral piece). The insert 48 is illustratively constructed from silicon carbide. In another embodiment, the insert 48 may be constructed from at least one of the following: aluminum oxide, zirconium oxide, or rare earth oxide. In yet another embodiment, the insert 48 may be constructed from a rare earth silicate. In another embodiment still, the insert 48 may be constructed from at least one of the following: a rare earth aluminate, an alkaline aluminosilicate, or mullite. Finally, in yet another embodiment, the insert 48 may be constructed from at least one of the following: chromium, cobalt, or molybdenum. In each of the embodiments described above, the insert 48 may be constructed from a material having a substantially homogenous composition.

In addition, in each of the embodiments described above, the insert 48 may be constructed from a material having a substantially non-homogenous composition. In one example, the insert 48 may include a composite braided tube suspended in a matrix material (e.g. ceramic matrix). In other examples, the insert 48 may comprise a fiber reinforced oxide or a particulate reinforced composite. In any case, for each of above-described embodiments, the insert 48 is made from a material providing an environmental barrier that prevents gasses from interacting with the ceramic blade track 28 and thereby compromising the mechanical integrity of the blade track 28.

A bond layer 56 is located between the liner 50 and portions of the side wall 47 which defines the aperture 46 as indicated above and shown in FIG. 3. The bond layer 56 is operable to couple the insert 48 to the one of the hangers 36.

The bond layer 56 is illustratively made of a silicon-containing braze material. For example, the bond layer 56 may be made of a silicon-metal silicide braze material. In other embodiments, the bond layer 56 may be made of a silicon-containing cement material. For example, the bond layer 56 may be made of a cement formed from a silicon-based slurry or from a pre-ceramic polymer that yields silica, silicate, or silicon oxycarbide. In yet another embodiment, the bond layer 56 may be made of a material including calcium aluminate.

Though not shown in the figures, the insert 48 may be coupled to the one of the hangers 36 without the use of an adhesive agent. For instance, the insert 48 may be constructed from a material having a greater coefficient of thermal expansion than the one of the ceramic hangers 36. Once the insert 48 is positioned in the aperture 46, exposure of the insert 48 and the one of the hangers 36 to engine operating temperatures may cause the insert 48 to expand, thereby urging the liner 50 against the side wall 47. As a result of expanding, the diameter D2 of the liner 50 may be greater than the diameter D of the aperture 46 so that an interference fit is formed between the liner 50 and the side wall 47.

Referring to FIG. 5, a combustor 114 of a gas turbine engine 110 illustratively includes a plurality of inserts 148. Specifically, the plurality of inserts 148 are positioned in apertures 149 formed in a liner 158 of the combustor 114. When the plurality of inserts 148 are positioned in the apertures 149, the plurality of inserts 148 shield portions of the liner 158 that define the apertures 149 from hot, high-pressure gases inside the combustor 114.

The combustor 114 includes a shell 160, the liner 158, fuel nozzles 162, and a heat shield 164 as shown in FIG. 5. The shell 160 is constructed from a metallic material and defines an annular cavity 161 that extends along an axis 163 as shown in FIG. 5. The liner 158 is arranged inside the cavity 161 defined by the shell 160 and extends around an annular combustion chamber 166 in which fuel is ignited to produce the hot, high-pressure gases that drive the gas turbine engine 110. The fuel nozzles 162 are circumferentially arranged around the combustion chamber 166 and provide fuel to the combustion chamber 166. The heat shield 164 is arranged to protect the shell 160 from the hot, high-pressure gases.

The shell 160 of the combustor 114 illustratively includes an outer shell member 168 and an inner shell member 170 that is generally concentric with and nested inside the outer shell member 168. Each of the outer and inner shell members 168, 170 are coupled to the liner 158 as shown in FIG. 5.

The liner 158 of the combustor 114 is illustratively assembled from a plurality of liner tiles 171-174 secured to the shell 160 by a plurality of metallic fasteners 176 as shown in FIG. 5. In the illustrative embodiment, each of the liner tiles 171-174 is constructed from a ceramic matrix composite material. Each of the liner tiles 171-174 is arranged around the circumference of the outer or inner shell members 168, 170. Each of the liner tiles 171-174 includes a body 177 and plurality of axially-extending tabs 178 arranged along an axially-forward side of a corresponding body 177.

The apertures 149 extend through at least a portion of the liner tiles 171-174 as shown in FIGS. 5-6. In the illustrative embodiment, the apertures 149 extend through the axially-extending tabs 178 of the liner tiles 171-174. The apertures 149 are aligned with corresponding apertures 151 which are formed in the outer and inner shell members 168, 170 of the shell 160. The apertures 149, 151 are aligned and extend parallel to an axis 179 that is perpendicular to the axis 163 as shown in FIG. 6. When the liner tiles 171-174 are coupled to the shell 160 using the metallic fasteners 176, the metallic fasteners 176 extend through the apertures 149, 151 as shown in FIGS. 5-6.

The plurality of inserts 148 are positioned in the plurality of apertures 149 as indicated above and shown in FIG. 5. Each of the plurality of inserts 148 is substantially similar to the insert 48 shown in FIGS. 2-4 and described herein. Accordingly, similar reference numbers in the 100 series indicate features that are common between the insert 48 and the plurality of inserts 148. The description of the insert 48 is hereby incorporated by reference to apply to the plurality of inserts 148, except in instances when it conflicts with the specific description and drawings of the inserts 148.

Referring to FIG. 6, one of the plurality of inserts 148 is shown positioned in the aperture 149 formed in the liner tile 172. The insert 148 is positioned in the aperture 149 such that a liner 150 of the insert 148 is received in the aperture 149. In addition, the insert 148 is positioned in the aperture 149 such that a retaining flange 152 of the insert 148 extends outwardly from the aperture 149 and engages a surface 180 of the liner tile 172. As such, the retaining flange 152 blocks the liner 150 from moving through the aperture 149 and away from the surface 180. The insert 148 shields a portion of the surface 180 as well as other portions of the liner tile 172 that define the aperture 149 from the hot, high-pressure gases inside the combustor 114.

The insert 148 is formed to include a passageway 154 that extends through the retaining flange 152 and the liner 150 parallel to the axis 179 as shown in FIG. 6. When the insert 148 is positioned in the aperture 149 as shown in FIG. 6, the passageway 154 extends through the aperture 149. As such, the passageway 154 aligns with one of the apertures 151 along the axis 179.

One of the plurality of metallic fasteners 176 extends through the passageway 154 to couple the liner tile 172 to the inner shell member 170 as shown in FIG. 6. The one of the fasteners 176 illustratively includes a head 182, a body 183 coupled to the head 182, and a threaded end 184 coupled to the body 183. The one fastener 176 is positioned in the passageway 154 and the one aperture 151 such that the head 182 engages the retaining flange 152, the body 183 extends through the passageway 154 and the aperture 151, and the threaded end 184 extends to a point located outside of the inner shell member 170. A metallic nut 185 is secured to the threaded end 184 to prevent the fastener 176 from moving through the aperture 151 and away from the inner shell member 170.

Referring to FIG. 7, a combustor 214 of a gas turbine engine 210 illustratively includes a plurality of inserts 248. Specifically, the plurality of inserts 248 are positioned in apertures 249 formed in a liner 258 of the combustor 214. When the plurality of inserts 248 are positioned in the apertures 249, the plurality of inserts 248 shield portions of the liner 258 that define the apertures 249 from hot, high-pressure gases inside the combustor 214.

The combustor 214 is substantially similar to the combustor 114 shown in FIGS. 5-6 and described herein. Accordingly, similar reference numbers in the 200 series indicate features that are common between the combustor 114 and the combustor 214. The description of the combustor 114 is hereby incorporated by reference to apply to the combustor 214, except in instances when it conflicts with the specific description and drawings of the inserts 214.

Unlike the liner 158 of the combustor 114, the liner 258 of the combustor 214 is illustratively assembled from a plurality of ceramic liner tiles 271-272 secured to the shell 260 by a plurality of metallic fasteners 276 as shown in FIG. 7. Unlike the liner tiles 171-174 of the liner 158, the liner tiles 271-272 do not include axially-extending tabs.

Apertures 249 extend through at least a portion of the liner tiles 271-272 as shown in FIGS. 7-8. In the illustrative embodiment, the apertures 249 extend through radially-extending tabs 291 of the liner tiles 271-272. The apertures 249 open into apertures 251 which are formed in the outer and inner shell members 268, 270 of the shell 260. The apertures 249, 251 are aligned and extend parallel to an axis 289 that is parallel to the axis 163 as shown in FIGS. 5-8. When the liner tiles 271-272 are coupled to the shell 260 using the metallic fasteners 276, the metallic fasteners 276 extend through the apertures 249, 251 as shown in FIGS. 7-8.

Referring to FIG. 8, one of the plurality of inserts 248 is shown positioned in the aperture 249 formed in the liner tile 272. The insert 248 is positioned in the aperture 249 such that the liner 250 of the insert 248 is received in the aperture 249. In addition, the insert 248 is positioned in the aperture 249 such that the retaining flange 252 of the insert 248 extends outwardly from the aperture 249 and engages a surface 290 of the liner tile 272. As such, the retaining flange 252 blocks the liner 250 from moving through the aperture 249 and away from the surface 290. Unlike the surface 180 of the liner 158, the surface 290 extends perpendicular to the axis 163.

The insert 248 is formed to include a passageway 254 that extends through the retaining flange 252 and the liner 250 parallel to the axis 289 as shown in FIG. 8. When the insert 248 is positioned in the aperture 249 as shown in FIG. 8, the passageway 254 extends through the aperture 249. As such, the passageway 254 aligns with the aperture 251 along the axis 289.

One of the plurality of metallic fasteners 276 extends through the passageway 254 to couple the liner tile 272 to the inner shell member 270 as shown in FIG. 8. The one of the fasteners 276 illustratively includes a head 282, a body 283 coupled to the head 282, and a threaded end 284 coupled to the body 283. The one fastener 276 is positioned in the passageway 254 and the one aperture 251 such that the head 282 engages the retaining flange 252, the body 283 extends through the passageway 254 and the aperture 251, and the threaded end 284 extends to a point located outside of the inner shell member 270. A metallic nut 285 is secured to the threaded end 284 to prevent the fastener 276 from moving through the aperture 251 and away from the inner shell member 270.

While the invention has been illustrated and described in detail in the drawings and foregoing description, the same is to be considered as illustrative and not restrictive in character, it being understood that only the preferred embodiments have been shown and described and that all changes and modifications that come within the spirit of the inventions are desired to be protected. It should be understood that while the use of words such as preferable, preferably, preferred or more preferred utilized in the description above indicate that the feature so described may be more desirable, it nonetheless may not be necessary and embodiments lacking the same may be contemplated as within the scope of the invention, the scope being defined by the claims that follow. In reading the claims, it is intended that when words such as “a,” “an,” “at least one,” or “at least one portion” are used there is no intention to limit the claim to only one item unless specifically stated to the contrary in the claim. When the language “at least a portion” and/or “a portion” is used the item can include a portion and/or the entire item unless specifically stated to the contrary.

Claims

1. A turbine shroud adapted for use in a gas turbine engine, the turbine shroud comprising

a blade track made from ceramic matrix composite materials and formed to include an aperture extending through at least a portion of the blade track, and

an insert formed to include a passageway that extends through the aperture to conduct gasses through the aperture while blocking gasses from interacting with surfaces of the blade track that define the aperture.

2. The assembly of claim 1, wherein the insert includes a liner that forms the passageway and a retention flange that extends outwardly from the liner along a side of the blade track that extends away from the aperture to block movement of the liner through the aperture away from the side of the blade track.

3. The assembly of claim 2, wherein the aperture formed in the blade track is a round bore that extends along an axis and the passageway formed in the insert is coaxial with the aperture.

4. The assembly of claim 3, wherein the liner has an outer diameter that is greater than a diameter of the aperture so that the insert is interference fit with the blade track.

5. The assembly of claim 3, further comprising a bond layer between the liner and a side wall that defines the aperture to couple the insert to the blade track.

6. The assembly of claim 5, wherein the bond layer is made of silicon-containing braze material.

7. The assembly of claim 5, wherein the bond layer is made of a silicon-containing cement material.

8. The assembly of claim 2, wherein the insert is a monolithic component made from a substantially homogenous material.

9. The assembly of claim 8, wherein the material is silicon carbide.

10. The assembly of claim 8, wherein the material is one of the following: aluminum oxide, zirconium oxide, or rare earth oxide.

11. The assembly of claim 8, wherein the material is a rare earth silicate.

12. The assembly of claim 8, wherein the material is one of the following: a rare earth aluminate, an alkaline aluminosilicate, or mullite.

13. A combustor adapted for use in a gas turbine engine, the combustor comprising

a shell made from metallic materials,

a liner tile made from ceramic matrix composite materials that is coupled to the shell and is formed to include an aperture extending through at least a portion of the liner tile, and

an insert formed to include a passageway that extends through the aperture to shield surfaces of the liner tile that define the aperture.

14. The combustor of claim 13, further comprising a fastener that extends through the passageway to couple the liner tile to the shell.

15. The combustor of claim 13, wherein the insert includes a liner that forms the passageway and a retention flange that extends outwardly from the liner along a side of the liner tile that extends away from the aperture to block the liner from moving through the aperture away from the side.

16. The assembly of claim 15, wherein the aperture formed in the liner tile is a round bore that extends along an axis and the passageway formed in the insert is coaxial with the aperture.

17. An assembly adapted for use in a gas turbine engine, the assembly comprising

a component made from ceramic matrix composite materials and formed to include an aperture extending through the component from a relatively-high pressure side of the component to a relatively-low pressure side of the component, and

an insert formed to include a passageway that extends through the aperture to conduct gasses through the aperture from the relatively-high pressure side of the component to the relatively-low pressure side of the component while blocking gasses from interacting with surfaces of the component that define the aperture.

18. The assembly of claim 17, wherein the insert includes a liner that forms the passageway and a retention flange that extends outwardly from the liner along the relatively-high pressure side of the component to block the liner from moving through the aperture toward the relatively-low pressure side of the component.

19. The assembly of claim 18, wherein the aperture formed in the component is a round bore that extends along an axis and the passageway formed in the insert is coaxial with the aperture.

20. The assembly of claim 19, further comprising a fastener that extends through the passageway to couple the component to another part of the assembly.