FIELD OF DISCLOSURE

The present disclosure relates generally to gas turbine engines, and more specifically to subassemblies of gas turbine engines including ceramic matrix composite materials.

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. 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.

Some shrouds positioned in the turbine may be exposed to high temperatures from products of the combustion reaction in the combustor. Such shrouds sometimes include blade track components made from ceramic matrix composite materials designed to withstand high temperatures. In some examples, coupling ceramic matrix composite components with traditional arrangements may present problems due to thermal expansion and/or material properties of the ceramic matrix composite components.

SUMMARY

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

A turbine shroud assembly adapted for use in a gas turbine engine may include a carrier, a blade track segment, and an intermediate carrier. The carrier may comprise metallic materials, while the blade track segment may comprise ceramic matrix composite materials. The carrier may be arranged to extend circumferentially at least partway about a center axis. The intermediate carrier may be configured to couple the blade track segment to the carrier

In some embodiments, the carrier may be formed to include a cooling passageway. The cooling passageway may be configured to conduct cooling air through the carrier.

In some embodiments, the blade track segment may be formed to include a runner, a first mount post, and a second mount post. The runner may be shaped to extend circumferentially partway around the center axis. The first mount post may extend radially outward from the runner. The second mount post may extend radially outward from the runner. In some embodiments, the second mount post may be spaced apart axially from the first mount post to define a channel therebetween.

In some embodiments, an intermediate carrier may include an intermediate carrier body, at least one pin, and a retainer. The intermediate carrier body may be arranged axially between the first mount post and the second mount post. The pin may extend axially into the first mount post, the intermediate carrier body, and the second mount post to couple the intermediate carrier body to the blade track segment. The retainer may extend radially and couple the intermediate carrier body with the carrier.

In some embodiments, the intermediate carrier body may be formed to include an impingement passageway. The impingement passageway may have an inlet aligned with an outlet of the cooling passageway. The inlet of the impingement passageway may align with the outlet of the cooling passageway such that the cooling air is configured to be conducted from the cooling passageway, through the impingement passageway, and directed toward the runner included in the blade track segment to cool the blade track segment.

In some embodiments, the turbine shroud assembly may further include an impingement tube. The impingement tube may extend into the cooling passageway and the impingement passageway to direct the cooling air toward the runner included in the blade track segment.

In some embodiments, the impingement tube may define a main passageway and an auxiliary passageway. The main passageway may extend radially through the impingement tube. The auxiliary passageway may extend at an angle relative to the main passageway. The auxiliary passageway may be in fluid communication with the main passageway so that the cooling air is directed toward the runner and toward the intermediate carrier body.

In some embodiments, the impingement tube may be brazed to the carrier to fix the impingement tube to the carrier. In some embodiments, the impingement tube may be press fit through the cooling passageway into the carrier to fix the impingement tube to the carrier.

In some embodiments, the retainer may extend along a retainer axis. The retainer axis may extend radially relative to the center axis.

In some embodiments, the impingement tube may be spaced apart circumferentially from the retainer and extends along a tube axis. The tube axis may be parallel to the retainer axis.

In some embodiments, the carrier may include a carrier body and an impingement tube. The impingement tube may extend radially from the carrier body to direct cooling air toward the runner. In some embodiments, the impingement tube may be spaced apart circumferentially from the entire intermediate carrier.

In some embodiments, the carrier may include a carrier body and a carrier boss. The carrier boss may extend radially inward from the carrier body into the inlet of the impingement passageway.

In some embodiments, the impingement passageway may be shaped to include a first portion and a second portion. The first portion may have a first cross-sectional area. The second portion may define an inlet and may have a second cross-sectional area that is greater than the first cross-sectional area.

In some embodiments, the intermediate carrier may further include an impingement boss. The impingement boss may be integrally formed with the intermediate carrier body. The impingement boss may extend radially away from the intermediate carrier body through the cooling passageway and the impingement passageway may extend through the impingement boss.

In some embodiments, the impingement passageway may be shaped to include a first portion and a second portion. The first portion may have a first cross-sectional area. The second portion may define an outlet and may have a second cross-sectional area that is greater than the first cross-sectional area.

According to another aspect of the present disclosure, a turbine shroud assembly adapted for use in a gas turbine engine may include a carrier, a blade track segment, and an intermediate carrier. The carrier may extend at least partway circumferentially around a central axis. The carrier may be formed to define a cooling passageway that extends through the carrier.

In some embodiments, the blade track segment may include a runner and an attachment portion. The runner may be shaped to extend circumferentially partway around the central axis. The attachment portion may extend radially outward from the runner.

In some embodiments, the intermediate carrier may include an intermediate carrier body and a first retainer. The intermediate carrier body may be coupled with the attachment portion of the blade track segment. The first retainer may extend radially and couple the carrier with the intermediate carrier.

In some embodiments, the intermediate carrier body may be formed to include an impingement passageway. The impingement passageway may have an inlet and an exit. The inlet may be aligned with an outlet of the cooling passageway. The exit may be arranged to direct air toward the blade track segment.

In some embodiments, the turbine shroud assembly may further includes an impingement tube. The impingement tube may extend into the cooling passageway and the impingement passageway. In some embodiments, the impingement tube may be brazed or press fit to the carrier to fix the impingement tube to the carrier.

In some embodiments, the impingement tube may define a main passageway and an auxiliary passageway. The main passageway may extend radially through the impingement passageway. The auxiliary passageway may extend at an angle relative to the main passageway. In some embodiments, the auxiliary passageway may be in fluid communication with the main passageway so that the cooling air is directed toward the runner and toward the intermediate carrier body.

In some embodiments, the carrier may include a carrier body and an impingement tube. The impingement tube may extend radially from the carrier body to direct cooling air toward the runner. In some embodiments, the impingement tube may be spaced apart circumferentially from the entire intermediate carrier.

In some embodiments, the first retainer may extend along a retainer axis. The retainer axis may extend radially relative to the central axis.

In some embodiments, the impingement tube may be spaced apart circumferentially from the first retainer and extends along a tube axis. The tube axis may be parallel to the retainer axis.

In some embodiments, the carrier may include a carrier body and a carrier boss. The carrier boss may extend radially inward from the carrier body into the inlet of the impingement passageway.

In some embodiments, the intermediate carrier may further include an impingement boss. The impingement boss may be integrally formed with the intermediate carrier body.

In some embodiments, the impingement boss may extend radially away from the intermediate carrier body through the cooling passageway. The impingement passageway may extend through the impingement boss.

According to another aspect of the present disclosure, a method may include providing a carrier, a blade track segment, an intermediate carrier, and an impingement tube. The blade track segment may include a runner shaped to extend partway around an axis, a first mount post that extends radially outward from the runner, and a second mount post spaced apart axially from the first mount post that extends radially outward from the runner.

In some embodiments, the method may further include arranging the intermediate carrier axially between the first mount post and the second mount post of the blade track segment. In some embodiments, the method may further include inserting a pin through the first mount post, the intermediate carrier, and the second mount post to couple the blade track segment to the intermediate carrier body.

In some embodiments, the method may further include inserting the impingement tube into a cooling passageway defined in the carrier, fixing the impingement tube to the carrier, and arranging the intermediate carrier in an attachment space formed in the carrier so that the impingement tube extends through the impingement passageways. In some embodiments, the method further include coupling the intermediate carrier with the carrier.

These and other features of the present disclosure will become more apparent from the following description of the illustrative embodiments.

