Patent Grant
11885225
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. Such static shrouds may be coupled to an engine case that surrounds the compressor, the combustor, and the turbine.
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 components made from materials that have different coefficients of thermal expansion. Due to the differing coefficients of thermal expansion, the components of some turbine shrouds expand at different rates when exposed to combustion products. In some examples, coupling such components with traditional fasteners such as rivets or bolts may not allow for the differing levels of expansion and contraction during operation of the gas turbine engine.
The present disclosure may comprise one or more of the following features and combinations thereof.
A turbine shroud assembly for use with a gas turbine engine may include a carrier segment, a blade track segment, and a retainer. The carrier segment may be made of metallic materials and arranged circumferentially at least partway around a central axis of the gas turbine engine. The carrier segment may be formed to include an attachment-receiving space.
In some embodiments, the blade track segment may be made of ceramic matrix composite materials and supported by the carrier segment to locate the blade track segment radially outward of the axis and define a portion of a gas path of the turbine shroud assembly. The blade track segment may include a shroud wall, a first attachment flange, and a second attachment flange. The shroud wall may extend circumferentially partway around the central axis. The first attachment flange may extend radially outward away from the shroud wall into the attachment-receiving space of the carrier segment. The second attachment flange may be spaced apart axially from the first attachment flange that extends radially outward away from the should wall into the attachment-receiving space of the carrier segment.
In some embodiments, the retainer may extend axially into the carrier segment and through the first attachment flange and the second attachment flange of the blade track segment so as to couple the blade track segment to the carrier segment.
In some embodiments, the first attachment flange of the blade track segment may include a first axially aft-facing surface. The first axially aft-facing surface may face the second attachment flange. The first axially aft-facing surface may extend radially outward and axially forward away from the shroud wall at a first angle relative to a first radial plane. The first radial plane may extend radially and circumferentially relative to the central axis of the gas turbine engine.
In some embodiments, the second attachment flange of the blade track segment may include a first axially forward-facing surface. The first axially forward-facing surface may face the first attachment flange. The first axially forward-facing surface may extend radially outward and axially aft away from the shroud wall at a second angle relative to a second radial plane parallel to the first radial plane.
In some embodiments, the first angle and the second angle may be equal. The first angle and the second angle may be between about 0 and 5 degrees. The first angle and the second angle may be exactly 3 degrees.
In some embodiments, the first attachment flange of the blade track segment may include a second axially forward-facing surface opposite the first axially aft-facing surface. The second axially forward-facing surface may extend away from the shroud wall at a third angle relative to a third radial plane. The third radial plane may be parallel to the first and second radial planes. The second attachment flange of the blade track segment may include a second axially aft-facing surface opposite the first axially forward-facing surface. The second axially aft-facing surface may extend away from the shroud wall at a fourth angle relative to a fourth radial plane. The fourth radial plane may be parallel to the first, second, and third radial planes. The third and fourth angle may be different from the first and second angles.
In some embodiments, the third and fourth angles may be equal. The third and fourth angles may be about 0 degrees.
In some embodiments, the first attachment flange of the blade track segment may include a second axially forward-facing surface opposite the first axially aft-facing surface. The second axially forward-facing surface may extend radially outward and axially forward away from the shroud wall at a third angle relative to a third radial plane. The third radial plane may be parallel to the first and second radial planes. The third angle may be different from the first angle.
In some embodiments, the second attachment flange of the blade track segment may include a second axially aft-facing surface opposite the first axially forward-facing surface. The second axially aft-facing surface may extend radially outward and axially aft away from the shroud wall at a fourth angle relative to a fourth radial plane. The fourth radial plane may be parallel to the first, second, and third radial planes. The fourth angle may be equal to the third angle.
In some embodiments, the third and fourth angles may be between about 0 and 2 degrees. The third and fourth angles may be exactly 0.5 degrees.
In some embodiments, the first attachment flange may be formed to include a first retainer through hole. The first retainer through hole may extend axially through the first attachment flange relative to the central axis between the first axially aft-facing surface and the second axially forward-facing surface. The second attachment flange may be formed to include a second retainer through hole that extends axially through the second attachment flange relative to the central axis between the first axially forward-facing surface and the second axially aft-facing surface. The second retainer through hole may be radially and circumferentially aligned with the first retainer through hole so as to receive the retainer.
According to another aspect of the present disclosure, a turbine shroud assembly for use with a gas turbine engine may include a carrier segment, a blade track segment, and a retainer. The carrier segment may be arranged circumferentially at least partway around a central axis of the gas turbine engine. The blade track segment may be made of ceramic matrix composite materials and supported by the carrier segment.
In some embodiments, the blade track segment may include a shroud wall, a first attachment flange, and a second attachment flange. The shroud wall may extend circumferentially partway around the central axis to define a portion of a gas path of the gas turbine engine. The first attachment flange may extend radially outward away from the shroud wall into the carrier segment. The second attachment flange may be spaced apart axially from the first attachment flange that extends radially outward away from the should wall into the carrier segment.
In some embodiments, the retainer may extend axially into the carrier segment and through the first attachment flange and the second attachment flange of the blade track segment so as to couple the blade track segment to the carrier segment.
In some embodiments, the first attachment flange of the blade track segment may include a first axially aft-facing surface that faces the second attachment flange. The first axially aft-facing surface may extend radially outward and axially forward away from the shroud wall at a first angle relative to a first radial plane. The first radial plane may be orthogonal to the central axis of the gas turbine engine. The second attachment flange of the blade track segment may include a first axially forward-facing surface that faces the first attachment flange. The first axially forward-facing surface may extend radially outward and axially aft away from the shroud wall at a second angle relative to a second radial plane. The second radial plane may be parallel to the first radial plane.
In some embodiments, the first angle and the second angle may be equal. The first angle and the second angle may be about 1.5 degrees.
In some embodiments, the first attachment flange of the blade track segment may include a second axially forward-facing surface opposite the first axially aft-facing surface. The second axially forward-facing surface may extend radially outward and axially forward away from the shroud wall at a third angle relative to a third radial plane. The third radial plane may be parallel to the first and second radial planes. The third angle may be different from the first angle.
In some embodiments, the second attachment flange of the blade track segment may include a second axially aft-facing surface opposite the first axially forward-facing surface. The second axially aft-facing surface may extend away from the shroud wall at a fourth angle relative to a fourth radial plane. The fourth radial plane may be parallel to the first, second, and third radial planes. The fourth angle may be different from the second angle
In some embodiments, the fourth angle may be equal to the third angle. The third and fourth angles may be about 0.5 degrees.
In some embodiments, the first attachment flange may be formed to include a first retainer through hole. The first retainer through hole may extend axially through the first attachment flange relative to the central axis. The second attachment flange may be formed to include a second retainer through hole. The second retainer through hole may extend axially through the second attachment flange relative to the central axis. The second retainer through hole may be radially and circumferentially aligned with the first retainer through hole so as to receive the retainer.
These and other features of the present disclosure will become more apparent from the following description of the illustrative embodiments.
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
The turbine 18 includes at least one turbine wheel assembly 20 and a turbine shroud 22 positioned to surround the turbine wheel assembly 20 as shown in
The blade track segment 28 includes first and second attachment flanges 34, 36 that extend radially outward from a shroud wall 32 that defines a portion of the gas path 25 as shown in
As mentioned above, the blade track segment 28 comprises ceramic matrix composite materials in the illustrative embodiment. To manufacture the ceramic matrix composite blade track segments, ceramic fibers are woven together to form ceramic plies. Layers of ceramic plies are stacked to form the shape of the blade track segment, i.e. the shroud wall and attachment flanges. Once the desired shape is formed, the mold tool is assembled around the blade track segment to get the desired shape of the component before the blade track segment is infiltrated with a slurry material. After infiltration, heat and pressure is then applied to form a ceramic matrix composite black track segment while the mold tool is still in place.
However, when the mold tool is removed from the ceramic matrix composite blade track segment, the attachment features experience a high degree of shear force. Removal of the mold tool creates a shear force along the axially facing surfaces of the attachment flanges. This shear force causes the outer layers of the ceramic plies to pull apart from the underlying layers of ceramic plies of the blade track segment, thereby weakening the ceramic matrix composite material and the structural integrity of the blade track segment.
Thus, the axially facing surfaces 38, 46 of the corresponding attachment flanges 34, 36 each extend radially and axially away from the shroud wall 32 at an angle 42, 50 relative to a radial plane 44, 52 as shown in
The first angle 42 of the first axially aft-facing surface 38 and the second angle 50 of the first axially forward-facing surface 46 reduce the shear force on the first axially aft-facing surface 38 and the first axially forward-facing surface 46 created when the mold tool 102 is removed, thereby reducing the shear force on the first and second attachment flanges 34, 36 such that the ceramic plies remain in place as the mold tool 102 is removed. The reduction in shear force created during the mold tool removal process minimizes damage to the ceramic matrix composite blade track segment 28.
In the illustrative embodiment, the first attachment flange 34 of the blade track segment 28 includes the first axially aft-facing surface 38 that faces the second attachment flange 36 and a second axially forward-facing surface 40 opposite the first axially aft-facing surface 38 as shown in
The second axially forward-facing surface 40 extends radially outward and axially forward away from the shroud wall 32 at a third angle 54 relative to a third radial plane 56 as shown in
The third radial plane 56 is parallel to the first radial plane 44 and the second radial plane 52 in the illustrative embodiment. The third radial plane 56 is located axially forward of the first radial plane 44 and the second radial plane 52. The first axially aft-facing surface 38 and the second axially forward-facing surface 40 of the first attachment flange 34 are not parallel to one another.
The first angle 42 formed by the first axially aft-facing surface 38 and the first radial plane 44 is greater than the third angle 54 formed by the second axially forward-facing surface 40 and the third radial plane 56 as shown in
In the illustrative embodiment, the second attachment flange 36 of the blade track segment 28 includes the first axially forward-facing surface 46 and a second axially aft-facing surface 48 opposite the first axially forward-facing surface 46 as shown in
The second axially aft-facing surface 48 extends away from the shroud wall 32 at a fourth angle 62 relative to a fourth radial plane 64 as shown in
The fourth radial plane 64 is parallel to the first radial plane 44, the second radial plane 52, and third radial plane 56 in the illustrative embodiment. The fourth radial plane 64 is located axially aft of the first, second, and third radial planes 44, 52, 56. The second axially aft-facing surface 48 and the first axially forward-facing surface 46 of the second attachment flange are not parallel to one another.
The second angle 50 formed by the first axially forward-facing surface 46 and the second radial plane 52 is greater than the fourth angle 62 formed by the second axially aft-facing surface 48 and the fourth radial plane 64 as shown in
It will be understood that
In the illustrative embodiment, the first angle 42 and the second angle 50 are equal. In other embodiments, first angle 42 and the second angle 50 may be different.
In some embodiments, the first angle 42 and the second angle 50 may be between 3 degrees and 10 degrees. In some embodiments, the first angle 42 and the second angle 50 may be between 3 degrees and 9 degrees. In some embodiments, the first angle 42 and the second angle 50 may be between 3 degrees and 8 degrees. In some embodiments, the first angle 42 and the second angle 50 may be between 3 degrees and 7 degrees. In some embodiments, the first angle 42 and the second angle 50 may be between 3 degrees and 6 degrees. In some embodiments, the first angle 42 and the second angle 50 may be between 3 degrees and 5 degrees. In some embodiments, the first angle 42 and the second angle 50 may be between 3 degrees and 4 degrees.
In some embodiments, the first angle 42 and the second angle 50 may be between 4 degrees and 5 degrees. In some embodiments, the first angle 42 and the second angle 50 may be between 4 degrees and 6 degrees. In some embodiments, the first angle 42 and the second angle 50 may be between 4 degrees and 7 degrees. In some embodiments, the first angle 42 and the second angle 50 may be between 5 degrees and 6 degrees. In some embodiments, the first angle 42 and the second angle 50 may be between 5 degrees and 7 degrees.
The first angle 42 and the second angle 50 may be about 3 degrees in the illustrative embodiment. In some embodiments, the first angle 42 and the second angle 50 may be exactly 3 degrees. In some embodiments, the first angle 42 and the second angle 50 may be about 4 degrees. In some embodiments, the first angle 42 and the second angle 50 may be exactly 4 degrees. In some embodiments, the first angle 42 and the second angle 50 may be about 5 degrees. In some embodiments, the first angle 42 and the second angle 50 may be exactly 5 degrees.
The third angle 54 is different from the first angle 42 and the fourth angle 62 is different from the second angle 50 in the illustrative embodiment. In the illustrative embodiment, the third angle 54 and the fourth angle 62 are equal.
In some embodiments, the third angle 54 and the fourth angle 62 may be between 0 degrees and 1 degrees. In some embodiments, the third angle 54 and the fourth angle 62 may be between 1 degrees and 2 degrees. In some embodiments, the third angle 54 and the fourth angle 62 may be between 1 degrees and 3 degrees.
In the illustrative embodiment, the third angle 54 and the fourth angle 62 may be about 0.5 degrees. In some embodiments, the third angle 54 and the fourth angle 62 may be exactly 0.5 degrees. In some embodiments, the third angle 54 and the fourth angle 62 may be about 1 degrees. In some embodiments, the third angle 54 and the fourth angle 62 may be exactly 1 degrees. In some embodiments, the third angle 54 and the fourth angle 62 may be about 2 degrees. In some embodiments, the third angle 54 and the fourth angle 62 may be exactly 2 degrees.
In an alternative embodiment, the third angle 54 and the fourth angle 62 may be about 0 degrees such that the third angle 54 is parallel to the third radial plane 56 and the fourth angle 62 is parallel to the fourth radial plane 64. In an additional embodiment, the third angle 54 and the fourth angle 62 may be exactly 0 degrees such that the third angle 54 is parallel to the third radial plane 56 and the fourth angle 62 is parallel to the fourth radial plane 64.
Turning again to the turbine wheel assembly 20, the turbine wheel assembly includes a plurality of blades 21 coupled to a rotor disk 24 for rotation with the rotor disk 24. The hot, high-pressure combustion products from the combustor 16 are directed toward the blades 21 of the turbine wheel assemblies 20 along a gas path 25. The turbine wheel assembly 20 further includes a plurality of vanes 15 as shown in
The turbine shroud 22 is made up of a plurality of turbine shroud assemblies 23 in the illustrative embodiment. The turbine shroud assemblies 23 each extend circumferentially partway around the axis 11 and cooperate to surround the turbine wheel assembly 20. In other embodiments, the turbine shroud 22 is annular and non-segmented to extend fully around the axis 11 and surround the turbine wheel assembly 20. In yet other embodiments, certain components of the turbine shroud 22 are segmented while other components are annular and non-segmented.
Each turbine shroud assembly 23 includes the carrier segment 26, the blade track segment 28, and the retainer 30 as shown in
The carrier segment 26 includes an outer wall 88 and a plurality of mount flanges 90, 92, 94, 96 as shown in
The plurality of mount flanges 90, 92, 94, 96 includes a first mount flange 90 and a second mount flange 92 as shown in
In the illustrative embodiment, the carrier segment 26 further includes a third mount flange 94 and a fourth mount flange 96 as shown in
In the illustrative embodiment, the first attachment flange 34 and the second attachment flange 36 of the blade track segment 28 extend radially outward from the shroud wall 32 into the spaces between the plurality of mount flanges 90, 92, 94, 96. The first attachment flange 34 of the blade track segment 28 extends radially outward from the shroud wall 32 between the first mount flange 90 and the third mount flange 94 so that the first attachment flange 34 is located axially between the first mount flange 90 and the third mount flange 94. The second attachment flange 36 extends radially outward from the shroud wall 32 between the second mount flange 92 and the fourth mount flange 96 so that the second attachment flange is located axially between the fourth mount flange 96 and the second mount flange 92.
In the illustrative embodiment, the first mount flange 90 is formed to include a hole 91 that extends axially through the first mount flange 90 as shown in
In the illustrative embodiment, the second mount flange 92 is formed to include a blind hole 93 that extends axially into the second mount flange 92 as shown in
In the illustrative embodiment, the third and fourth mount flanges 94, 96 are formed to include holes 95, 97 as shown in
The blade track segment includes the shroud wall 32, the first attachment flange 34, and the second attachment flange 36 as shown in
The shroud wall 32 of the blade track segment 28 includes a forward face 65, a middle face 67, and an aft face 69 as shown in
The first attachment flange 34 extends radially outward from a first flange base 58 near the shroud wall 32 to a first flange radially outer end 60 as shown in
The second attachment flange 36 extends radially outward from a second flange base 66 near the shroud wall 32 to a second flange radially outer end 68 as shown in
The axial gap 61 between the first flange base 58 of the first attachment flange 34 and the second flange base 66 of the second attachment flange 36 is smaller than the axial gap 63 between the first flange radially outer end 60 of the first attachment flange 34 and the second flange radially outer end 68 of the second attachment flange 36 as shown in
In the illustrative embodiment, the first attachment flange 34 is formed to include a first retainer through hole 70 and the second attachment flange 36 is formed to include a second retainer through hole 72 as shown in
The first retainer through hole 70 extends axially through the first attachment flange 34 relative to the axis 11 between the first axially aft-facing surface 38 and the second axially forward-facing surface 40. The second retainer through hole 72 extends axially through the second attachment flange 36 relative to the axis 11 between the first axially forward-facing surface 46 and the second axially aft-facing surface 48. The first retainer through hole 70 and the second retainer through hole 72 are radially and circumferentially aligned with one another so as to receive the retainer 30.
While the axially facing surfaces 38, 40, 46, 48 extend at angles 42, 50, 54, 62 relative to the radial planes 44, 52, 56, 64, the through holes 70, 72 each extend axially through the corresponding attachment flange 34, 36. This way, the retainer 30 extends axially through the attachment flanges 34, 36 relative to the axis 11.
The retainer 30 includes a forward pin 76 and an aft pin 78 as shown in
In the illustrative embodiment, the turbine shroud assembly 23 includes two retainers 30, 31 as shown in
The retainer 31 includes a forward pin 80 and an aft pin 82 as shown in
The retainer 30 is substantially similar to the retainer 31, the forward pin 76 is substantially similar to the forward pin 80, and the aft pin 78 is substantially similar to the aft pin 82 in the illustrative embodiment such that description of the retainer 30 applies to the retainer 31, description of the forward pin 76 applies to the forward pin 80, and description of the aft pin 78 applies to the aft pin 82.
The retainer 30 couples the blade track segment 28 to the carrier segment 26 as shown in
In the illustrative embodiment, the retainer 30 extends through the hole 91 formed in the first mount flange 90, through the first retainer through hole 70 formed in the first attachment flange 34, through the holes 95, 97 formed in the third and fourth mount flanges 94, 96, through the second retainer through hole 72 formed in the second attachment flange 36, and into the blind hole 93 formed in the second mount flange 92. The forward pin 76 of the retainer 30 rests in the hole 91 formed in the first mount flange 90, the first retainer through hole 70 formed in the first attachment flange 34, and the hole 95 formed in the third mount flange 94. The aft pin 78 of the retainer 30 rests in the hole 97 formed in the fourth mount flange 96, the second retainer through hole 72 formed in the second attachment flange 36, and the blind hole 93 formed in the second mount flange 92.
To manufacture the blade track segment 28, a mold tool 102 is used as shown in
In the illustrative embodiment, the mold tool 102 includes a forward mold member 104, a middle mold member 106, and an aft mold member 108 as shown in
The angled axial facing surfaces 38, 46 engage angled surfaces on the middle mold member 106, thereby minimizing the shear force along the first axially aft-facing surface 38 of the first attachment flange 34 and the first axially forward-facing surface 46 of the second attachment flange 36 that is created by removing the middle mold member 106.
In other embodiments, where the attachment flanges 34, 36 are completely radial and parallel to the radial planes 44, 52, removal of the middle mold member 106 from between the attachment flanges 34, 36 creates a shear force along each attachment flange 34, 36. This may cause the layers of ceramic plies to separate from each other as the middle mold member 106 is removed. By angling the surfaces 38, 46, the shear force along the surfaces 38, 46 is minimized and prevents the outermost layers of ceramic plies, as suggested in
The angle surfaces 38, 46 may also cause the layers of ceramic plies to be more dense near the radial ends 60, 68 of the attachment flanges 34, 36 compared to the base 58, 66 of the attachment flanges 34, 36. In the illustrative embodiment, the layers extend radially along the attachment flanges 34, 36.
For the purposes of the present disclosure, the modifier about means ±1% of the given value. Of course, greater or lesser deviation is contemplated and may be used in processed method within the spirit of this 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.
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