Systems and methods for forming a turbine engine cover element with integral sacrificial ring

Abstract

Turbine engine seals can prevent or reduce airflow along surfaces of a turbine engine, such as along a turbine shroud or along a rotor. 3D printers can be used to produce turbine engine seals, such as brush seals or labyrinth seals. Such seals can be formed as a single piece including a hard ring and a sacrificial ring. The sacrificial ring and the hard ring can be circularly symmetric. The sacrificial ring is formed on an inner surface of the hard ring.

Description

[0001] Cross-reference to related applications

[0002] This patent application claims priority and benefit to U.S. Provisional Patent Application No. 63 / 615,673, filed December 28, 2023, entitled “SYSTEMS AND METHODS FORFORMING A TURBINE ENGINE SHROUD ELEMENT WITH AN INTEGRAL SACRIFICIAL RING”. The entire contents of U.S. Provisional Patent Application No. 63 / 615,673 are incorporated herein by reference. Technical Field

[0003] The systems and methods involve additive manufacturing, 3D printing, and selective laser melting (SLM) printing of 3D objects. The systems and methods also involve using additive manufacturing techniques to produce turbine engine components with integral sacrificial rings (e.g., sacrificial rings in honeycomb seals). Background Technology

[0004] Turbine engines use sacrificial seals to reduce airflow passing over the outer edges of turbine blades or along the rotor. A common sacrificial seal material is a metallic honeycomb. The honeycomb is welded to a backing plate, which can be bolted into the turbine engine to form brush seals and labyrinth seals. Brush seals can be located on the outside of the turbine. The turbine blades can impact the honeycomb without damaging it. Grooves can be carved into the honeycomb by the turbine blades. Therefore, brush seals reduce airflow along the shroud rather than through the turbine. Labyrinth seals can be positioned along the outer surface of the turbine rotor. The teeth of the labyrinth seal attached to the rotor impact the honeycomb of the labyrinth seal, thereby reducing airflow passing beside the rotor without through the turbine. Those familiar with turbines or turbine engines are familiar with brush seals and labyrinth seals. Summary of the Invention

[0005] The following overview is provided to facilitate understanding of some of the innovative features characteristic of the disclosed examples and is not intended to be a complete description. A full understanding of the various aspects of these examples can be obtained by considering the entire specification, claims, drawings, and abstract as a whole.

[0006] One aspect of the subject matter described in this disclosure can be implemented by a system. The system may include a seal configured to reduce airflow along the surface of a turbine engine, wherein: the seal is formed as a single piece including a hard ring and a sacrificial ring; the sacrificial ring and the hard ring are circularly symmetrical; and the sacrificial ring is formed on the inner surface of the hard ring.

[0007] Another aspect of the subject matter described in this disclosure can be achieved by a method. The method may include: producing a seal that is formed as a single piece comprising a hard ring and a sacrificial ring, wherein: the seal is configured to reduce airflow along the surface of a turbine engine; the sacrificial ring and the hard ring are circularly symmetrical; and the sacrificial ring is formed on the inner surface of the hard ring.

[0008] Another aspect of the subject matter described in this disclosure can be implemented by a system. The system may include a turbine engine shroud formed as an integral part including a first sacrificial ring and a second sacrificial ring, wherein: the turbine engine shroud and the first sacrificial ring are configured to form a brush seal for the turbine engine; and the turbine engine shroud and the second sacrificial ring are configured to form the outer portion of a labyrinth seal for the turbine engine.

[0009] In some implementations of the method and apparatus, the hard ring is a brush seal configured to surround a turbine rotor including a plurality of turbine blades, and the sacrificial ring is configured to be impacted by the turbine blades without damaging them. In some implementations of the method and apparatus, the seal is a non-rotating element of the turbine engine. In some implementations of the method and apparatus, the seal is additively manufactured. In some implementations of the method and apparatus, the seal is configured to form the outer portion of a labyrinth seal of the turbine engine, the sacrificial ring is a wear-resistant liner configured to be worn by a plurality of labyrinth seal teeth attached to the rotor of the turbine engine, and the sacrificial ring is a non-rotating element of the turbine engine. In some implementations of the method and apparatus, the seal is a 3D-printed seal. In some implementations of the method and apparatus, the turbine engine shroud includes the hard ring. In some implementations of the method and apparatus, the system may further include a turbine engine shroud comprising the rigid ring and a second sacrificial ring attached to the inner surface of the turbine engine shroud, wherein the turbine engine shroud, the sacrificial ring, and the second sacrificial ring are formed as a single integral piece. Furthermore, the turbine engine shroud, the sacrificial ring, and the second sacrificial ring are circularly symmetrical about a common axis, the turbine engine shroud and the sacrificial ring are configured to form a brush seal of the turbine engine, and the turbine engine shroud and the second sacrificial ring are configured to form the outer portion of a labyrinth seal of the turbine engine.

[0010] In some implementations of the method and apparatus, the method may include printing a turbine engine shroud including the seal using a 3D printer. In some implementations of the method and apparatus, the seal is configured to form a brush seal of the turbine engine, the turbine engine including a turbine rotor including a plurality of turbine blades, and the brush seal is configured to surround the turbine rotor and be impacted by the turbine blades without damaging the turbine blades. In some implementations of the method and apparatus, the seal is a non-rotating element of the turbine engine. In some implementations of the method and apparatus, the method may include printing the seal as a single piece including the hard ring and the sacrificial ring using a 3D printer. In some implementations of the method and apparatus, the seal is configured to form the outer portion of a labyrinth seal of the turbine engine, and the sacrificial ring is a wearable liner configured to be worn by a plurality of labyrinth seal teeth of the labyrinth seal, wherein the labyrinth seal teeth are attached to the rotor of the turbine engine, and the sacrificial ring is a non-rotating element of the turbine engine. In some implementations of the method and apparatus, the turbine engine shroud includes the rigid ring. In some implementations of the method and apparatus, the method may include: printing the turbine engine shroud using a 3D printer, the turbine engine shroud including the rigid ring and including a second sacrificial ring attached to an inner surface of the turbine engine shroud, wherein the turbine engine shroud, the sacrificial ring, and the second sacrificial ring are formed as a single integral part, the turbine engine shroud, the sacrificial ring, and the second sacrificial ring are circularly symmetrical about a common axis, the turbine engine shroud and the sacrificial ring are configured to form a brush seal of the turbine engine, and the turbine engine shroud and the second sacrificial ring are configured to form the outer portion of a labyrinth seal of the turbine engine.

[0011] In some implementations of the method and apparatus, the turbine engine shroud is additively manufactured as a single piece. In some implementations of the method and apparatus, the turbine engine shroud, the first sacrificial ring, and the second sacrificial ring are circularly symmetrical about a common axis. In some embodiments of the method and apparatus, the first sacrificial ring comprises a honeycomb material. Attached Figure Description

[0012] The accompanying drawings further illustrate examples and, together with the detailed description, serve to explain the examples disclosed herein. In the drawings, the same reference numerals refer to the same or functionally similar elements throughout the various views, and the drawings are incorporated into and form part of the specification.

[0013] Figure 1 This is an image of honeycomb material that can be used as a sacrificial element in turbine engine seals.

[0014] Figure 2 This is a high-level conceptual drawing illustrating a section of a turbine engine seal, which has a honeycomb material welded to a hard ring section.

[0015] Figure 3 It is based on some aspects of the high-level concept drawings of SLM type 3D printers.

[0016] Figure 4 This is a high-level conceptual drawing illustrating an example of a 3D-printed seal based on some aspects.

[0017] Figure 5 This is a high-level conceptual drawing illustrating an example of a brush seal based on some aspects.

[0018] Figure 6 This is a high-level conceptual drawing illustrating an example of a labyrinth seal based on some aspects.

[0019] Figure 7 These are high-level conceptual drawings illustrating examples of 3D-printed turbine engine shrouds and rotors based on some aspects.

[0020] Figure 8 This is an example of a high-level conceptual drawing of a turbine engine shroud printed by a 3D printer, based on some aspects.

[0021] Figure 9 This is a high-level flowchart illustrating examples of methods for forming a seal with an integral sacrificial ring, based on some aspects.

[0022] Figure 10 This is a high-level flowchart illustrating examples of methods for forming a turbine shroud element with an integral sacrificial ring, based on some aspects. Detailed Implementation

[0023] The specific values ​​and configurations discussed in the following non-limiting embodiments may vary and are cited only to illustrate one or more embodiments, and are not intended to limit their scope.

[0024] Examples will now be described more fully below with reference to the accompanying drawings, in which exemplary examples are shown. The embodiments disclosed herein may be implemented in many different forms and should not be construed as limited to those set forth herein; rather, these examples are provided so that this disclosure will be thorough and complete and will fully convey the scope of the examples to those skilled in the art. Throughout the document, the same reference numerals denote the same elements.

[0025] The terminology used herein is for the purpose of describing particular examples only and is not intended to be limiting. As used herein, the singular forms “a,” “an,” and “the” are also intended to include the plural forms unless the context clearly indicates otherwise. It should also be understood that, when used in this specification, the terms “comprising” and / or “including” specify the presence of the stated features, integrals, steps, operations, elements, and / or components, but do not exclude the presence or addition of one or more other features, integrals, steps, operations, elements, components, and / or combinations thereof.

[0026] Throughout the specification and claims, terms may have fictitious meanings suggested or implied in the context beyond their explicitly stated meanings. Similarly, the phrase "in one example" as used herein does not necessarily refer to the same example, and the phrase "in another example" as used herein does not necessarily refer to a different example. The claimed subject matter is intended to encompass combinations of all or part of the embodiments.

[0027] Unless otherwise defined, all terms used herein (including technical and scientific terms) have the same meaning as commonly understood by one of ordinary skill in the art. It should also be understood that terms, such as those defined in commonly used dictionaries, should be interpreted as having a meaning consistent with their meaning in the context of the relevant field and will not be interpreted in an idealized or overly formalized sense, unless expressly defined herein.

[0028] It should be understood that the specific examples described herein are shown by way of illustration and not as limiting the claims. The main aspects may be adopted in various examples without departing from the scope of the claims. Those skilled in the art will recognize or be able to identify many equivalents of the specific procedures described herein using only conventional experimentation. These equivalents are considered to be within the scope covered by the claims.

[0029] When used in conjunction with the term "comprising" in the claims and / or description, the word "a" can mean "one," but it also has the same meaning as "one or more," "at least one," and "one or more." The term "or" as used in the claims is used to mean "and / or," unless explicitly stated to refer only to alternatives, or the alternatives are mutually exclusive, although this disclosure supports the definition of "and / or" referring only to alternatives. Throughout this application, the term "approximately" is used to indicate that a value includes the inherent variation in the error of the apparatus, the method used to determine that value, or a variation present in the object of study.

[0030] As used in this specification and claims, the words “comprising” (and any form of inclusion, such as “comprising” and “including”), “having” (and any form of having, such as “having” and “having”), “comprising” (and any form of inclusion, such as “comprising with” and “containing”), or “containing” (and any form of containing, such as “containing” and “having”) are inclusive or open-ended and do not exclude additional, unlisted elements or method steps.

[0031] As used herein, the term "or combinations thereof" refers to all permutations and combinations of the items listed preceding the term. For example, "A, B, C, or combinations thereof" is intended to include at least one of the following: A, B, C, AB, AC, BC, or ABC, and may also be BA, CA, CB, CBA, BCA, ACB, BAC, or CAB if the order is significant in the particular context. Continuing with this example, what is explicitly included are combinations that contain repetitions of one or more items or terms, such as BB, AAA, AB, BBC, AAABCCCC, CBBAAA, CABABB, etc. Those skilled in the art will understand that there is generally no limit to the number of items or terms in any combination unless otherwise apparent from the context.

[0032] According to this disclosure, all compositions and / or methods disclosed and claimed herein can be prepared and performed without excessive experimentation. While compositions and methods have been described according to preferred embodiments, it will be apparent to those skilled in the art that changes may be made to the compositions and / or methods described herein, as well as the steps or sequence of steps of the methods, without departing from their concept, spirit, and scope. All such similar substitutions and modifications that are apparent to those skilled in the art are considered to be within the spirit, scope, and concept defined by the appended claims.

[0033] Figure 1 This is an image of honeycomb material 100, which can be used as a sacrificial element in a turbine engine seal. Those familiar with turbines and turbine engines will recognize this honeycomb material 100. The honeycomb material 100 is designed and manufactured so that turbine blades or other turbine rotor elements are not damaged upon impact with it. Thus, the honeycomb material is an abrasive element that can be worn by rotating elements (e.g., rotor blades, labyrinth seal teeth, etc.) that carve channels in the honeycomb material 100 as the rotor rotates. As a result, a seal can be formed to reduce or prevent airflow along the sides of the turbine shroud or along the turbine rotor, allowing substantially all airflow to pass through the turbine. Therefore, the seal can contribute to improved turbine efficiency. The figure shows a honeycomb composed of six side units. Other unit sizes and shapes can be used in the sacrificial element, as is known in the art.

[0034] Figure 2 This is a high-level conceptual drawing illustrating section 200 of a turbine engine seal, which has a honeycomb material 100 welded to the hard ring section 201. Those familiar with turbines and turbine engines will recognize... Figure 2 The illustrated honeycomb seal section. The illustrated example has a flange 202 and a hard ring section 201 that can be machined from a single piece of metal. A sacrificial element 203 may be welded to or otherwise adhered to the hard ring to produce the honeycomb seal section 200. Note that the seal is generally referred to as a honeycomb seal regardless of the shape of the unit in the sacrificial element. The honeycomb seal section can be bolted to the turbine housing via mounting holes in a flange. Multiple honeycomb seal sections can thus form a complete ring, thereby providing a honeycomb seal that reduces or prevents airflow along the surface of the rotor or turbine housing.

[0035] Figure 3 This is a high-level concept drawing of an SLM-type 3D printer 300 based on some aspects. A powder feeder 310 deposits powder 312 to produce a powder layer 305 in a powder bed 308. The powder layer deposited initially can be located directly on the powder bed 308, or on a substrate that can be set in the powder bed before powder layer deposition. A beam scanner 301 can move a beam source 302 or manipulate an energy beam 311 generated by the beam source 302. The energy beam can be a laser beam, an electron beam, etc. The energy beam 311 generates a melt pool 304, in which the energy beam 311 melts some of the powder in the powder layer 305. The powder layer 305 is currently the uppermost layer in the powder bed 308. The melt pool 304 has a melt pool depth 303. The melt pool depth 303 is illustrated to be large enough to melt the powder in the powder layer 305 and some of the layers in the layer 306 directly below the powder layer 305. In some implementations, the molten pool can extend downwards through multiple underlying layers. A beam scanner moves the molten pool 304 along a path through powder layer 305 to selectively melt some of the powder, thereby creating a composition layer. The first deposited powder layer becomes the bottom composition layer 307. 3D objects can be printed by iteratively depositing powder layers, using an energy beam to melt a pattern into the powder layers to create composition layers, depositing another powder layer, etc., to create a stack of composition layers that form the 3D object.

[0036] Figure 4 This is a high-level conceptual drawing illustrating an example of a 3D-printed seal 400 based on some aspects. A 3D-printed seal, such as the one shown in the example, can be made by, for example, in... Figure 3The illustration shows a 3D printer printing process. The entire 3D-printed seal 400 can be printed as a single unit, thus forming a single piece, also known as an integral part, which includes a flange 402, a hard ring 405, and a sacrificial ring 406. After printing, the seal can be mounted in a turbine engine via mounting holes 401 in the flange 402. The rotor of the turbine engine can rotate about a common axis 403 and can be circularly symmetrical about this common axis 403. Other components of the turbine engine, such as the seal (e.g., seal 400), can also be circularly symmetrical about the common axis. Figure 4 The seal illustrated has a common axis 403, which, when the seal is in a turbine engine, can coincide with the common axis of the turbine engine and the turbine rotor. Figure 4 The example has a flange 402, a hard ring 405, and a sacrificial ring 406 that are symmetrical about a common axis. A 3D printer can easily print a seal with a sacrificial ring having an inner surface 407 that is symmetrical about the common axis, while the hard ring is asymmetrical about the common axis. Furthermore, the entire seal can be printed simultaneously and as a single unit. In this way, the sacrificial ring is attached to the inner surface of the hard ring because the sacrificial ring and the hard ring are printed as a single piece. Therefore, it is not necessary to weld the sacrificial element to the hard element.

[0037] Figure 5 This is a high-level conceptual diagram illustrating an example of a brush seal 500 according to some aspects. The brush seal 500 is a seal configured to surround a turbine rotor and prevent airflow along the inner surface of the turbine shroud. Airflow along the inner surface of the turbine shroud can bypass the turbine 501, resulting in ineffective turbine operation. The turbine 501 may have a plurality of turbine blades 503 attached to a rotor 502. The brush seal 500 can be configured to surround the turbine 501. In this way, the rotor with the attached turbine blades can be positioned within the brush seal. The turbine 501, including the rotor 502 and the turbine blades 503, can rotate within the brush seal 500 such that the tips of the turbine blades 503 impact the sacrificial ring without damaging any of the turbine blades. This impact can etch grooves in the sacrificial ring. Figure 5 The brush seal 500 illustrated herein can be 3D printed as a single piece. The turbine 501, rotor 502, and turbine blades 503 can be rotating elements that rotate within the brush seal, which is a non-rotating element surrounding a non-rotating element. The sacrificial ring 406 of the brush seal 500 can be a wear-resistant liner configured to be worn by the turbine blades 503 attached to the rotor 502 and rotating within the brush seal. The turbine blades 503 can wear the sacrificial ring 406 by etching grooves in it.

[0038] Figure 6This is a high-level conceptual diagram illustrating an example of a labyrinth seal 600 according to some aspects. As is known in the art, a turbine rotor 502 can be held in place within a turbine engine by means of bearing elements (not shown). The bearing elements hold the rotor in place while providing substantially frictionless rotor rotation. Structures within the turbine engine, such as the bearing elements, provide opportunities for airflow along the rotor. Airflow along the rotor instead of through the turbine would result in inefficient turbine operation. The labyrinth seal 600 is a seal configured to prevent airflow along the rotor 502. The labyrinth seal 600 may include a hard ring 602, a sacrificial ring 601, and labyrinth seal teeth 606. The hard ring 602 and the sacrificial ring 601 may be non-rotating elements forming the outer portion of the labyrinth seal. The labyrinth seal teeth 606 are attached to the rotor 502 and are therefore rotating elements. The labyrinth seal 600 can be formed by positioning the rotor within the hard ring 602 and the sacrificial ring 601. Thus, the hard ring 602 and the sacrificial ring 601 can be configured to surround the rotor 502 and the labyrinth seal teeth 606 attached to the rotor 502. The labyrinth seal teeth 606 can be attached to the rotor 502 such that the labyrinth seal teeth 606 can etch grooves in the sacrificial ring 601 as the rotor 502 rotates. Thus, the sacrificial ring 601 of the labyrinth seal 600 can be a wear-resistant liner configured to wear down the labyrinth seal teeth 606 attached to the rotor 502 and rotating within the labyrinth seal 600. The labyrinth seal teeth 606 can wear down the sacrificial ring 601 by etching grooves in it. The labyrinth seal teeth 606 and the sacrificial ring 601 together form a labyrinthine path for air flowing along the rotor. Compared to a straight path, the labyrinthine path reduces airflow along the rotor. Figure 6 The example illustrated has a spar 603 connecting a hard ring 602 to a flange. The flange, spar 603, hard ring 602, and sacrificial ring 601 can be 3D printed in a single run of a 3D printer and thus formed as a single piece. The sacrificial ring is formed on the inner surface of the hard ring.

[0039] Figure 7 This is a high-level conceptual drawing illustrating an example of a 3D-printed turbine engine shroud 700 and rotor 502 based on several aspects. The turbine engine shroud 700 includes a brush seal 701, a hard ring 602 of a labyrinth seal 702, and a sacrificial ring 601 of the labyrinth seal 702. The labyrinth seal teeth can be seen attached to the rotor. Figure 7In the example, the turbine shroud 700 can be 3D printed and thus formed as a single piece. The turbine shroud 700 can include a sacrificial ring 406 for a brush seal 701, and the turbine shroud itself can be a rigid ring supporting the sacrificial ring 406. Thus, the rigid ring of the brush seal 701 is equivalent to the portion of the turbine shroud 700 that supports the sacrificial ring 406 of the brush seal. Note that the function of the rigid ring is to provide rigid support for the sacrificial ring. The turbine shroud may also include a sparsity 603, a rigid ring 602 for a labyrinth seal 702, and a sacrificial ring 601 for the labyrinth seal 702. Here, a single turbine stage of a turbine engine is shown. The 3D printed turbine shroud can be configured to have additional turbine stages and additional stages of the turbine engine. The turbine engine can include only a single turbine shroud or multiple turbine shrouds attached end-to-end.

[0040] Figure 8 This is an example of a high-level conceptual drawing of a turbine engine shroud printed by a 3D printer, based on some aspects. Figure 3 The illustrated 3D printer is printing. Figure 7 The turbine engine cover is shown in the example.

[0041] Figure 9 This is a high-level flowchart illustrating an example of a method 900 for forming a seal having an integral sacrificial ring, according to some aspects. At block 901, a seal is produced as a single piece including a hard ring and a sacrificial ring, wherein the seal is formed as a single piece including a hard ring and a sacrificial ring, the sacrificial ring and the hard ring being circularly symmetrical, and the sacrificial ring being formed on the inner surface of the hard ring.

[0042] Figure 10 This is a high-level flowchart illustrating an example of a method for forming a turbine engine shroud element having an integral sacrificial ring 1000, according to some aspects. At block 1001, a turbine engine shroud is printed using a 3D printer, the turbine engine shroud including a sacrificial ring and a second sacrificial ring attached to the inner surface of the turbine engine shroud, wherein the turbine engine shroud, the sacrificial ring and the second sacrificial ring are integral, the turbine engine shroud, the sacrificial ring and the second sacrificial ring are circularly symmetrical about a common axis, the turbine engine shroud and the sacrificial ring are configured to form a brush seal of the turbine engine, and the turbine engine shroud and the second sacrificial ring are configured to form the outer portion of a labyrinth seal of the turbine engine.

Claims

1. A system comprising: A seal, configured to reduce airflow along the surface of the turbine engine. in: The seal is formed as a single piece including a hard ring and a sacrificial ring; The sacrificial ring and the hard ring are circularly symmetrical; and The sacrificial ring is formed on the inner surface of the hard ring.

2. The system according to claim 1, wherein: The hard ring is a brush seal configured to surround a turbine rotor comprising multiple turbine blades; and The sacrificial ring is configured to withstand the impact of the turbine blades without damaging them.

3. The system according to claim 1, wherein, The seal is a non-rotating component of the turbine engine.

4. The system according to claim 1, wherein, The seal is manufactured using additive manufacturing.

5. The system according to claim 1, wherein: The seal is configured to form the outer portion of the labyrinth seal of the turbine engine; The sacrificial ring is an abrasive liner, which is configured to be worn by a plurality of labyrinth seal teeth of the labyrinth seal. The labyrinth seal teeth are attached to the rotor of the turbine engine; and The sacrificial ring is a non-rotating element of the turbine engine.

6. The system according to claim 1, wherein, The seal is a 3D-printed seal.

7. The system according to claim 1, wherein, The turbine engine shroud includes the rigid ring.

8. The system according to claim 1, further comprising: A turbine engine shroud, the turbine engine shroud including the rigid ring and a second sacrificial ring attached to the inner surface of the turbine engine shroud. in: The turbine engine shroud, the sacrificial ring, and the second sacrificial ring are formed as a single integral part; The turbine engine shroud, the sacrificial ring, and the second sacrificial ring are circularly symmetrical about a common axis; The turbine engine shroud and the sacrificial ring are configured to form a brush seal for the turbine engine; and The turbine engine shroud and the second sacrificial ring are configured to form the outer portion of the labyrinth seal of the turbine engine.

9. A method comprising the following steps: Producing a seal, said seal being formed as a single piece comprising a hard ring and a sacrificial ring, wherein: The seal is configured to reduce airflow along the surface of the turbine engine; The sacrificial ring and the hard ring are circularly symmetrical; and The sacrificial ring is formed on the inner surface of the hard ring.

10. The method according to claim 9, further comprising: The turbine engine cover, including the seal, is printed using a 3D printer.

11. The method according to claim 9, wherein: The seal is configured to form a brush seal for the turbine engine, which includes a turbine rotor that includes a plurality of turbine blades. as well as The brush seal is configured to surround the turbine rotor and be impacted by the turbine blades without damaging them.

12. The method according to claim 9, wherein, The seal is a non-rotating component of the turbine engine.

13. The method according to claim 9, further comprising: The seal is printed as a single piece, including the hard ring and the sacrificial ring, using a 3D printer.

14. The method according to claim 9, wherein: The seal is configured to form the outer portion of the labyrinth seal of the turbine engine; and The sacrificial ring is an abrasive liner configured to be worn by the labyrinth seal's multiple labyrinth seal teeth. in: The labyrinth seal teeth are attached to the rotor of the turbine engine; and The sacrificial ring is a non-rotating element of the turbine engine.

15. The method according to claim 9, wherein, The turbine engine shroud includes the rigid ring.

16. The method according to claim 9, further comprising: A turbine engine shroud is printed using a 3D printer. The turbine engine shroud includes the rigid ring and a second sacrificial ring attached to the inner surface of the turbine engine shroud. in: The turbine engine shroud, the sacrificial ring, and the second sacrificial ring are formed as a single integral part; The turbine engine shroud, the sacrificial ring, and the second sacrificial ring are circularly symmetrical about a common axis; The turbine engine shroud and the sacrificial ring are configured to form a brush seal for the turbine engine; and The turbine engine shroud and the second sacrificial ring are configured to form the outer portion of the labyrinth seal of the turbine engine.

17. A system comprising: A turbine engine shroud, wherein the turbine engine shroud is formed as an integral part including a first sacrificial ring and a second sacrificial ring. in: The turbine engine shroud and the first sacrificial ring are configured to form a brush seal for the turbine engine; and The turbine engine shroud and the second sacrificial ring are configured to form the outer portion of the labyrinth seal of the turbine engine.

18. The system according to claim 17, wherein, The turbine engine shroud is additively manufactured into the integral part.

19. The system according to claim 17, wherein, The turbine engine shroud, the first sacrificial ring, and the second sacrificial ring are circularly symmetrical about a common axis.

20. The system according to claim 17, wherein, The first sacrificial ring comprises honeycomb material.

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