Rotor assembly with protection shim and gas turbine engine including the same

Abstract

The present invention relates to a rotor assembly having a protective core. A rotor assembly according to one embodiment of the present invention comprises a disk inserted into a rotational shaft and having a plurality of insertion grooves along a circumferential direction, a plurality of blades inserted into the insertion grooves, and a protective core disposed between the blades and the disk, having a plurality of mounting portions on one surface and a plurality of weights detachably attached to the mounting portions.

Description

Technology Field

[0001] The present invention relates to a rotor assembly and a gas turbine engine, and more specifically, to a rotor assembly having a protective core and a gas turbine engine including the same. Background Technology

[0002] Because the rotor assembly of a gas turbine engine rotates at high speeds, it features a dovetail structure to prevent the blades from detaching from the disc. Additionally, the blades are made of carbon fiber composites to reduce weight.

[0003] Blades made of composite materials are vulnerable to delamination at the tip edge due to collisions with external foreign matter and vibrations generated during operation. In particular, dovetail structures have a high risk of failure because they come into direct contact with the disc during operation. Conventionally, to solve these problems, a wear strip is attached between the blade and the disc to prevent wear. However, since the wear strip is only partially placed at the point where the blade and the disc come into contact, significant stress is concentrated in that area during operation.

[0004] In addition, balancing is generally performed to adjust the center of gravity after assembling the blades onto the disc, but damage to the disc is inevitably caused by grinding during this process.

[0005] The aforementioned background technology is technical information that the inventor possessed for the derivation of the present invention or acquired during the process of deriving the present invention, and it cannot be considered as publicly known technology disclosed to the general public prior to the filing of the present invention. Prior art literature

[0006] European Patent Publication 699824 B1 The problem to be solved

[0007] The present invention is an invention for solving the aforementioned problems, and provides a rotor assembly and a gas turbine engine including the same, which prevents damage to the blades, reduces manufacturing tolerances, and eliminates the need for unnecessary balancing work by placing a weight-adjustable protective core between the blades and the disc.

[0008] However, these problems are exemplary, and the problems to be solved by the present invention are not limited thereto. means of solving the problem

[0009] A rotor assembly according to one embodiment of the present invention comprises a disk inserted into a rotational shaft and having a plurality of insertion grooves along a circumferential direction, a plurality of blades inserted into the insertion grooves, and a protective core disposed between the blades and the disk, having a plurality of mounting portions on one surface and a plurality of weights detachably attached to the mounting portions.

[0010] In a rotor assembly according to one embodiment of the present invention, the mounting portion is formed on the bottom surface of the protective core, and the cross-sectional area may decrease toward the radial outer side of the disk.

[0011] In a rotor assembly according to one embodiment of the present invention, the mounting portion may be composed of a plurality of grooves having different outer diameters and arranged to form a step in the height direction.

[0012] In a rotor assembly according to one embodiment of the present invention, the plurality of mounting portions may be arranged at equal intervals to form a plurality of rows along the longitudinal direction.

[0013] In a rotor assembly according to one embodiment of the present invention, the plurality of mounting parts may be arranged on the longitudinal centerline and the widthline of the bottom surface of the protective core.

[0014] In a rotor assembly according to one embodiment of the present invention, the mounting portion may have a conical or pyramidal shape.

[0015] In a rotor assembly according to one embodiment of the present invention, the plurality of weights may have different weights.

[0016] In a rotor assembly according to one embodiment of the present invention, the bottom surface of the protective core contacts the inner bottom surface of the disk, and portions extending from both sides in the width direction of the bottom surface may extend between the blade and the disk.

[0017] In a rotor assembly according to one embodiment of the present invention, the blade comprises a wing portion extending in the longitudinal direction and a dovetail portion extending from the wing portion and inserted into the insertion groove, having a width greater than that of the wing portion, and the protective core comprises a pair of support surfaces extending obliquely toward the inner wall of the disk on both sides in the width direction of the bottom surface, and the lower end of the dovetail portion may be supported on the support surfaces.

[0018] In a rotor assembly according to one embodiment of the present invention, the weight may include a body and a plurality of support protrusions that protrude from the body and are coupled to the inner surface of the mounting portion.

[0019] In a rotor assembly according to one embodiment of the present invention, the mounting portion has a slit shape formed on the bottom surface of the protective core, the weight has a pair of support protrusions coupled to a pair of inner surfaces of the mounting portion, and the body may be spaced apart from the inner surface of the mounting portion.

[0020] In a rotor assembly according to one embodiment of the present invention, the weight may have a rectangular shape extending in the width direction of the disk.

[0021] In a rotor assembly according to one embodiment of the present invention, the mounting portion has a hole shape formed on the bottom surface of the protective core, the weight has a pair of support protrusions coupled to a pair of inner surfaces of the mounting portion, and the body can be spaced apart from the inner surface of the mounting portion.

[0022] In a rotor assembly according to one embodiment of the present invention, the plurality of mounting portions may gradually increase in size toward one side in the longitudinal direction of the protective core.

[0023] A gas turbine engine according to one embodiment of the present invention comprises a compressor for compressing a working fluid, a combustion chamber for burning the compressed working fluid and fuel, and a turbine that generates power through an output shaft and has a plurality of rotor assemblies, wherein the rotor assembly includes a disk that is inserted into a rotating shaft and has a plurality of insertion grooves along a circumferential direction, a plurality of blades that are inserted into the insertion grooves, and a protective core disposed between the blades and the disk, having a plurality of mounting portions on one surface and a plurality of weights that are detachably attachable to the mounting portions.

[0024] Other aspects, features, and advantages other than those described above will become clear from the specific details, claims, and drawings for implementing the invention below. Effects of the invention

[0025] A rotor assembly according to one embodiment of the present invention places a protective core between the blade and the disc, thereby minimizing damage to the disc and blade during operation. Additionally, by attaching and detaching a weight to the protective core, the rotation axis and center of gravity of the rotor assembly can be easily aligned without a process of grinding the disc. Brief explanation of the drawing

[0026] FIG. 1 shows a gas turbine engine according to one embodiment of the present invention. FIG. 2 shows a rotor assembly according to one embodiment of the present invention. FIGS. 3 and FIGS. 4 show a protective core according to one embodiment of the present invention. FIG. 5 shows a protective core according to another embodiment of the present invention. FIG. 6 shows a protective core and a weight according to one embodiment of the present invention. FIG. 7 shows a protective core and a weight according to another embodiment of the present invention. FIG. 8 shows a weight according to one embodiment of the present invention. FIG. 9 shows a weight according to another embodiment of the present invention. FIG. 10 shows a protective core and a weight according to another embodiment of the present invention. FIG. 11 shows a protective core and a weight according to another embodiment of the present invention. Specific details for implementing the invention

[0027] The present invention is capable of various modifications and may have various embodiments; specific embodiments are illustrated in the drawings and described in detail in the description of the invention. However, this is not intended to limit the present invention to specific embodiments, and it should be understood that the invention includes all modifications, equivalents, and substitutions that fall within the spirit and scope of the invention. In describing the present invention, the same identification numerals are used for identical components, even if they are illustrated in different embodiments.

[0028] Hereinafter, embodiments of the present invention will be described in detail with reference to the attached drawings. When describing with reference to the drawings, identical or corresponding components are given the same reference numerals, and redundant descriptions thereof will be omitted.

[0029] In the following embodiments, terms such as first, second, etc. are used not in a limiting sense, but for the purpose of distinguishing one component from another component.

[0030] In the following examples, singular expressions include plural expressions unless the context clearly indicates otherwise.

[0031] In the following embodiments, terms such as "include" or "have" mean that the features or components described in the specification are present, and do not preclude the possibility that one or more other features or components may be added.

[0032] In the drawings, the size of components may be exaggerated or reduced for convenience of explanation. For example, the size and thickness of each component shown in the drawings are depicted arbitrarily for convenience of explanation, so the present invention is not necessarily limited to what is illustrated.

[0033] In the following embodiments, the x-axis, y-axis, and z-axis are not limited to three axes in an orthogonal coordinate system and can be interpreted in a broader sense that includes them. For example, the x-axis, y-axis, and z-axis may be orthogonal to each other, but they may also refer to different directions that are not orthogonal to each other.

[0034] Where an embodiment can be implemented differently, a specific process sequence may be performed differently from the order described. For example, two processes described consecutively may be performed substantially simultaneously or proceed in the reverse order of the description.

[0035] The terms used in this application are used merely to describe specific embodiments and are not intended to limit the invention. In this application, terms such as “comprising” or “having” are intended to indicate the presence of the features, numbers, steps, actions, components, parts, or combinations thereof described in the specification, and should be understood as not precluding the existence or addition of one or more other features, numbers, steps, actions, components, parts, or combinations thereof.

[0037] FIG. 1 shows a gas turbine engine (1) according to one embodiment of the present invention, FIG. 2 shows a rotor assembly (100) according to one embodiment of the present invention, FIG. 3 and FIG. 4 show a protective core (130) according to one embodiment of the present invention, FIG. 5 shows a protective core (130A) according to another embodiment of the present invention, FIG. 6 shows a protective core (130) and a weight (140) according to one embodiment of the present invention, FIG. 7 shows a protective core (130B) and a weight (140A) according to another embodiment of the present invention, FIG. 8 shows a weight (140) according to one embodiment of the present invention, and FIG. 9 shows a weight (140A) according to another embodiment of the present invention.

[0038] As shown in FIG. 1, a gas turbine engine (1) according to one embodiment of the present invention may include a turbine (10), a compressor (20), an output shaft (30), a combustion chamber (40), a pump (50), and a fuel tank (60). Air introduced into the compressor (20) is compressed and then combusted in the combustion chamber (40) together with fuel introduced through the fuel tank (60) and the pump (50). The combustion gas passes through the turbine (10), generates output through the output shaft (30), and is exhausted to the outside. The gas turbine engine (1) may be used in aircraft, ships, power generation plants, etc.

[0039] A rotor assembly (100) may be included in a turbine (10). As shown in FIG. 1, a plurality of rotor assemblies (100) may be arranged in the direction of the output shaft (30) and may be arranged to rotate together with the output shaft (30). Also, as shown in FIG. 2, the rotor assembly (100) may include a disk (110), a blade (120), and a protective core (130).

[0040] The disk (110) is inserted into the output shaft (30) and rotates together with the output shaft (30). The disk (110) can be inserted into the output shaft (30) such that its center O is coaxial with the output shaft (30). The disk (110) may have a circular plate or polygonal plate shape having a predetermined thickness. The disk (110) may have a plurality of mounting grooves (111) along the circumferential direction on its outer surface. More specifically, as shown in FIG. 2, the mounting grooves (111) are arranged on the outer surface of the disk (110), and the dovetail portion (122) of the blade (120) can be inserted into the inner side. FIG. 2 shows that 11 mounting grooves (111) are arranged, but the number of mounting grooves (111) can be appropriately selected according to the number of blades (120) and the capacity of the gas turbine engine (1). For example, the number of seating grooves (111) may be 10 or fewer or 12 or more.

[0041] The mounting groove (111) is provided with a flat bottom surface to be mounted on the outer circumference of the disk (110), and the side supporting the dovetail portion (122) may extend from both sides of the bottom surface. For example, as shown in FIG. 2, the side of the mounting groove (111) may include a portion extending vertically from both sides of the bottom surface and a portion extending inward from there toward the blade (120). Accordingly, even if the blade (120) inserted into the mounting groove (111) rotates at high speed, the dovetail portion (122) is supported by the mounting groove (111) and prevents it from deviating from a fixed position.

[0042] In one embodiment, the radial end of the seating groove (111) may be positioned between the wing portion (121) and the dovetail portion (122) of the blade (120).

[0043] The blade (120) is inserted into the mounting groove (111) of the disk (110) and rotates by combustion gas to drive the output shaft (30). The blade (120) may be flat, curved, or bent in a predetermined direction. For example, the blade (120) may have a shape twisted by a predetermined angle around a central axis in the longitudinal direction.

[0044] In one embodiment, the blade (120) may include a wing portion (121) and a dovetail portion (122).

[0045] As shown in FIG. 2, the wing portion (121) may extend in the longitudinal direction of the blade (120) (or the radial direction of the disk (110). The wing portion (121) rotates the output shaft (30) by coming into direct contact with the combustion gas.

[0046] The dovetail portion (122) extends downward from the wing portion (121) and is inserted into the seating groove (111). The dovetail portion (122) may have a greater width than the wing portion (121). For example, the dovetail portion (122) may include a portion that slopes outward from the bottom of the wing portion (121) and gradually widens, a portion that extends vertically downward from there, and a bottom portion. The dovetail portion (122) may have a shape corresponding to the inner surface of the seating groove (111).

[0047] In one embodiment, the bottom surface of the dovetail portion (122) may be spaced apart from the bottom surface of the seating groove (111) while inserted into the seating groove (111). More specifically, as shown in the enlarged view of FIG. 2, a gap may be formed on the bottom surface between the seating groove (111) and the dovetail portion (122). Through this configuration, the blade (120) can be seated loosely in the seating groove (111) even if the shape and size of the dovetail portion (122) are somewhat different. In addition, while securing such a gap, when the rotor assembly (100) is operated, the blade (120) is pressed against the seating groove (111) radially outward by centrifugal force, so that the blade (120) does not shake.

[0048] The protective core (130) is positioned between the blade (120) and the disk (110) to prevent damage to the disk (110) and the blade (120) that occurs during the operation of the rotor assembly (100). For example, as shown in FIG. 2, the protective core (130) is positioned to wrap around the dovetail portion (122) of the blade (120), and in this state, it can be positioned to contact the inner surface of the disk (110).

[0049] In one embodiment, the protective core (130) may have a frontal shape that is polygonal, circular, or a combination thereof. For example, as shown in FIG. 3, the protective core (130) may include a bottom surface (131), a support surface (132) extending from the bottom surface (131), and a side surface (133).

[0050] The bottom surface (131) is seated on the bottom surface of the seating groove (111) while the protective core (130) is inserted into the seating groove (111). As shown in FIGS. 2 and 3, the bottom surface (131) may have a narrower width than the bottom surface of the seating groove (111). Also, while the blade (120) is inserted into the protective core (130), the end of the dovetail portion (122) may be spaced apart from the bottom surface (131).

[0051] The support surface (132) extends obliquely toward the inner wall of the disk (110) on both sides in the width direction of the bottom surface (131). As shown in FIGS. 2 and 3, a pair of support surfaces (132) are positioned between the bottom surface (131) and the side surface (133), and each is positioned at a predetermined angle toward the outside of the protective core (130).

[0052] In one embodiment, the support surface (132) can support the blade (120). As shown in FIG. 2, when the blade (120) and the protective core (130) are inserted into the seating groove (111), the end of the dovetail portion (122) of the blade (120) can be supported by the upper end of the support surface (132).

[0053] The side surface (133) extends vertically in the height direction from the top of the support surface (132) so as to come into contact with the side of the dovetail portion (122). Additionally, the cover surface (134) extends from the top of the side surface (133) to cover the upper surface of the dovetail portion (122). Accordingly, when the blade (120) and the protective core (130) are seated in the seating groove (111), as shown in FIG. 2, the bottom surface (131) of the protective core (130) is spaced apart from the bottom surface of the seating groove (111), and the bottom of the dovetail portion (122) is supported on the support surface (132). Furthermore, the side surface (133) and the cover surface (134) are positioned to surround the dovetail portion (122) to distribute the load applied to the disk (110), i.e., the seating groove (111), when the blade (120) rotates.

[0054] One or more mounting portions (135) may be disposed on the bottom surface (131). As shown in FIGS. 3 and 4, the mounting portions (135) may be holes or slits formed on the bottom surface (131) along the longitudinal direction L and the width direction W. For example, the mounting portions (135) may be disposed at equal intervals to form a plurality of rows along the longitudinal direction L. Additionally, the plurality of mounting portions (135) may be disposed symmetrically with respect to the center of the longitudinal direction L and / or the width direction W.

[0055] A weight (140) may be detachably disposed in the mounting portion (135). This aligns the center of rotation and the center of gravity of the protective core (130) and the rotor assembly (100) containing it, thereby allowing the rotor assembly (100) to rotate smoothly. For example, the mounting portion (135) and the weight (140) may each be provided with screw threads that can be coupled to each other. In addition, the mounting portion (135) and the weight (140) may be provided with various types of known detachable fastening means.

[0056] Alternatively, the mounting portion (135) and the weight (140) may not be provided with separate fastening means. That is, as shown in FIG. 2, the mounting portion (135) is formed on the bottom surface (131) of the protective core (130). In addition, even if the rotor assembly (100) rotates, as described later, the mounting portion (135) has a shape in which the cross-sectional area decreases radially outward from the disk (110), that is, in the height direction of the protective core (130), so the weight (140) may not detach from the mounting portion (135) even without providing separate fastening means. Through this, the total weight of the protective core (130), the weight (140), and the rotor assembly (100) including them can be reduced, and the time and cost required for manufacturing can be reduced.

[0057] In one embodiment, the mounting portion (135) may have a shape in which the cross-sectional area decreases radially outward from the disk (110), that is, in the height direction of the protective core (130). In other words, the mounting portion (135) may be formed to penetrate the bottom surface (131), and its cross-sectional area may gradually decrease from the outside to the inside of the bottom surface (131).

[0058] For example, as shown in FIG. 6, the mounting portion (135) may be composed of a plurality of grooves having different outer diameters and arranged to form a step in the height direction. Additionally, the outer diameter of the grooves arranged on the outer surface of the bottom surface (131) of the mounting portion (135) may be larger than the outer diameter of the grooves arranged on the inner surface of the bottom surface (131).

[0059] Likewise, the weight (140) may have a shape corresponding to the mounting portion (135). For example, as shown in FIG. 8, the weight (140) may include a small diameter portion (141) having a diameter D1 and a large diameter portion (142) having a diameter D2 larger than D1.

[0060] When the rotor assembly (100) rotates with the weight (140) inserted into the mounting portion (135), the weight (140) is subjected to a force directed radially outward from the rotor assembly (100) due to centrifugal force. At this time, as described above, the mounting portion (135) and the weight (140) have a shape in which the cross-sectional area decreases toward the radially outward side of the disk (110), so that the weight (140) can be prevented from detaching from the mounting portion (135) even when subjected to centrifugal force.

[0061] In one embodiment, a weight (140) is inserted into the protective core (130) to balance the weight of the protective core (130) and the rotor assembly (100). More specifically, the rotor assembly (100) rotates while inserted into the output shaft (30). If the rotation axis of the rotor assembly (100) does not align with the center of gravity, problems such as vibration or rubbing occur during rotation. Conventionally, the center of gravity and the rotation axis were aligned by inserting a blade (120) into the disk (110) and then grinding the disk (110); however, damage to the disk (110) inevitably occurs during the grinding process. Additionally, there is a problem that a new balancing operation must be performed when replacing the blade (120).

[0062] A rotor assembly (100) according to one embodiment of the present invention can align the rotation axis and the center of gravity of the rotor assembly (100) without damaging the disk (110) by attaching and detaching a weight (140) to a protective core (130). For example, if the center of gravity of the rotor assembly (100) is skewed inward in the thickness direction, the center of gravity can be corrected by attaching a weight (140) to a mounting part (135) located outward in the length direction of the protective core (130).

[0063] In one embodiment, the weights (140) may have the same or different weights.

[0064] FIG. 4 illustrates a case where six mounting portions (135) are arranged in two rows on the bottom surface of the protective core (130), but the number and position of the mounting portions (135) are not limited thereto. For example, as shown in FIG. 5, the mounting portions (135A) may be arranged in multiple numbers along the width direction centerline of the bottom surface of the protective core (130A) and in multiple numbers along the length direction centerline.

[0065] In one embodiment, the mounting portion (135A) may not be placed in the area where the width direction centerline and the length direction centerline intersect. More specifically, when any three of the plurality of mounting portions (135A) are extended to form a virtual triangle, the remaining mounting portion (135A) may be placed outside the virtual triangle. For example, as shown in FIG. 5, four mounting portions (135A) are formed and may be placed on the width direction centerline and the length direction centerline so as to be symmetrical. Through such a placement, the position of the overall center of gravity of the rotor assembly (100) can be significantly changed by attaching or detaching any one of the mounting portions (135A).

[0066] In another embodiment, the mounting portion (135A) may be replaced asymmetrically. For example, the mounting portion (135A) may be placed on only one side with respect to the width direction centerline and / or the length direction centerline, or a larger number may be placed on one side.

[0067] In another embodiment, the mounting portion (135B) may have a cone or pyramidal shape. For example, as shown in FIGS. 7 and 9, the weight (140B) may have a square pyramidal shape, and the mounting portion (135B) may have a corresponding shape. Alternatively, in another embodiment, the weight (140B) may have various pyramidal shapes, such as a triangular pyramid or a pentagonal pyramid. Alternatively, the weight (140B) may have a coneal shape.

[0068] Through such a configuration, the rotor assembly (100) according to one embodiment of the present invention places a protective core (130) between the blade (120) and the disk (110), thereby minimizing damage to the disk (110) and the blade (120) during operation. In addition, by attaching and detaching a weight (140) to the protective core (130), the rotation axis and the center of gravity of the rotor assembly (100) can be easily aligned without a process of grinding the disk (110).

[0069] FIG. 10 shows a protective core (130C) and a weight (140B) according to another embodiment of the present invention. More specifically, FIG. 10 shows the protective core (130C) as viewed from the bottom.

[0070] As shown in FIG. 10, a plurality of mounting portions (135C) may be formed on the bottom surface (131C) of the protective core (130C). Additionally, the mounting portions (135C) may have a slit shape. For example, unlike the hole-shaped mounting portions (135, 135A, 135B) according to the previously described embodiment, the mounting portions (135C) may be formed elongated in one direction on the bottom surface (131C). Additionally, the mounting portions (135C) may have a uniform width or diameter in the thickness direction of the bottom surface (131C).

[0071] In one embodiment, a plurality of mounting portions (135C) may have different sizes and / or shapes. For example, the mounting portions (135C) may have a rectangular shape that extends in the width direction of the bottom surface (131C) and may be arranged in multiple numbers along the length direction of the bottom surface (131C). Additionally, the size of the plurality of mounting portions (135C) may gradually increase or decrease along the length direction of the bottom surface (131C). Furthermore, the weight (140B) may also have a corresponding size and weight. Through such a configuration, if the center of gravity of the rotor assembly (100) is off-center, the center of gravity of the rotor assembly (100) can be adjusted more easily by attaching and detaching the largest (or heaviest) weight (140B).

[0072] The weight (140B) may include a body (141B) and a plurality of support protrusions (142B) that protrude from the body (141B) and are coupled to the inner surface of the mounting portion (135C). For example, as shown in FIG. 10, the body (141B) has a shape corresponding to that which is inserted into the mounting portion (135C), and in one embodiment, it may have a rectangular shape. Additionally, the support protrusions (142B) may protrude from both sides of the body (141B), for example, both sides in the width direction of the body (141B). A pair of support protrusions (142B) may be detachably coupled to the inner surface of the mounting portion (135C) through screw coupling, etc.

[0073] In one embodiment, the body (141B) may be positioned spaced apart from the inner surface of the mounting portion (135C). As shown in FIG. 10, when the weight (140B) is attached to the mounting portion (135C), the longitudinal surfaces of the bottom surface (131C) may be spaced apart from the inner surface of the mounting portion (135C) by a predetermined distance. Through this gap, the weight (140B) can be detached from the mounting portion (135C).

[0074] FIG. 11 shows a protective core (130D) and a weight (140C) according to another embodiment of the present invention. More specifically, FIG. 11 shows the protective core (130D) as viewed from the bottom.

[0075] As shown in FIG. 11, a plurality of mounting portions (135D) may be formed on the bottom surface (131D) of the protective core (130D). Additionally, the mounting portions (135D) may have a hole shape. Additionally, the mounting portions (135D) may have a uniform width or diameter in the thickness direction of the bottom surface (131D).

[0076] The weight (140C) may include a body (141C) and a plurality of support protrusions (142C) that protrude from the body (141C) and are coupled to the inner surface of the mounting portion (135D). For example, as shown in FIG. 11, the body (141C) may be circular so as to be inserted into the mounting portion (135D). Additionally, the support protrusions (142C) may protrude from both sides of the body (141C), for example, radially outward from the body (141C). A pair of support protrusions (142C) may be detachably coupled to the inner surface of the mounting portion (135D) through screw coupling or the like.

[0077] In one embodiment, the body (141C) may be positioned spaced apart from the inner surface of the mounting portion (135D). As shown in FIG. 11, when the weight (140C) is attached to the mounting portion (135D), the longitudinal surfaces of the bottom surface (131D) may be spaced apart from the inner surface of the mounting portion (135D) by a predetermined distance. Through this gap, the weight (140C) can be detached from the mounting portion (135D).

[0078] Although the present invention has been described with reference to the embodiments illustrated in the drawings, this is merely illustrative. Those skilled in the art will fully understand that various modifications and equivalent alternative embodiments are possible from the embodiments. Accordingly, the true technical scope of protection of the present invention should be determined based on the appended claims.

[0079] The specific technical details described in the embodiments are merely examples and do not limit the technical scope of the embodiments. To make the description of the invention concise and clear, descriptions of general prior art and configurations may be omitted. Furthermore, the connections of lines or connecting members between components depicted in the drawings are illustrative of functional connections and / or physical or circuit connections, and may be replaced or represented by various additional functional, physical, or circuit connections in actual devices. Additionally, unless specifically stated with terms such as "essential" or "importantly," a component may not be strictly necessary for the application of the present invention.

[0080] The term "the above" or similar designations in the description of the invention and claims may refer to both singular and plural forms unless specifically limited otherwise. Furthermore, where a range is described in the embodiments, it is considered to include the invention with respect to individual values ​​within said range (unless otherwise stated), and is equivalent to describing each individual value constituting said range in the description of the invention. Additionally, regarding the steps constituting the method according to the embodiments, the steps may be performed in a suitable order unless explicitly stated or otherwise stated. The embodiments are not necessarily limited by the order in which the steps are described. The use of all examples or exemplary terms (e.g., etc.) in the embodiments is merely for the purpose of describing the embodiments in detail, and the scope of the embodiments is not limited by said examples or exemplary terms unless otherwise limited by the claims. Furthermore, a person skilled in the art will understand that various modifications, combinations, and changes may be made according to design conditions and factors within the scope of the claims or equivalents to which they are added. Explanation of the symbols

[0081] 1: Gas turbine engine 10: Turbine 100: Rotor Assembly 110: Disk 120: Blade 130: Protection 140: Weight

Claims

Claim 1 A rotor assembly comprising: a disk inserted into a rotational shaft and having a plurality of insertion grooves along the circumferential direction; a plurality of blades inserted into the insertion grooves; and a protective core disposed between the blades and the disk, having a plurality of mounting portions on one surface and a plurality of weights detachably attached to the plurality of mounting portions, wherein the plurality of weights have different weights. Claim 2 A rotor assembly according to claim 1, wherein the mounting portion is formed on the bottom surface of the protective core and the cross-sectional area decreases toward the radial outer side of the disk. Claim 3 A rotor assembly according to claim 2, wherein the mounting portion comprises a plurality of grooves having different outer diameters and arranged to form a step in the height direction. Claim 4 A rotor assembly according to claim 2, wherein the plurality of mounting portions are arranged at equal intervals to form a plurality of rows along the longitudinal direction. Claim 5 In claim 2, the rotor assembly, wherein the plurality of mounting parts are arranged on the longitudinal centerline and the widthline of the bottom surface of the protective core. Claim 6 In claim 2, the above-mentioned mounting portion is a rotor assembly having a conical or pyramidal shape. Claim 7 delete Claim 8 A rotor assembly according to claim 1, wherein the protective core has a bottom surface in contact with the inner bottom surface of the disk, and portions extending from both sides in the width direction of the bottom surface extend between the blade and the disk. Claim 9 A rotor assembly according to claim 8, wherein the blade comprises a wing portion extending in the longitudinal direction and a dovetail portion extending from the wing portion and inserted into the insertion groove and having a width greater than that of the wing portion, and the protective core comprises a pair of support surfaces extending obliquely toward the inner wall of the disk on both sides in the width direction of the bottom surface, and the lower end of the dovetail portion is supported on the support surfaces. Claim 10 A rotor assembly according to claim 1, wherein the weight comprises a body and a plurality of support protrusions protruding from the body and coupled to the inner surface of the mounting portion. Claim 11 A rotor assembly according to claim 10, wherein the mounting portion has a slit shape formed on the bottom surface of the protective core, the weight has a pair of support protrusions coupled to a pair of inner surfaces of the mounting portion, and the body is spaced apart from the inner surface of the mounting portion. Claim 12 In claim 11, the rotor assembly, wherein the weight has a rectangular shape extending in the width direction of the disk. Claim 13 A rotor assembly according to claim 10, wherein the mounting portion has a hole shape formed on the bottom surface of the protective core, the weight has a pair of support protrusions coupled to a pair of inner surfaces of the mounting portion, and the body is spaced apart from the inner surface of the mounting portion. Claim 14 In claim 10, the rotor assembly wherein the plurality of mounting portions gradually increase in size toward one side in the longitudinal direction of the protective core. Claim 15 A gas turbine engine comprising a compressor for compressing a working fluid, a combustion chamber for burning the compressed working fluid and fuel, and a turbine that generates power through an output shaft and has a plurality of rotor assemblies, wherein the rotor assembly comprises: a disk inserted into a rotating shaft and having a plurality of insertion grooves along a circumferential direction; a plurality of blades inserted into the insertion grooves; and a protective core disposed between the blades and the disk, having a plurality of mounting portions on one surface and having a plurality of weights detachably attached to the plurality of mounting portions; wherein the plurality of weights have different weights.

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