KR102703144B1 - Blade fixing assembly, gas turbine comprising it and gas turbine manufacturing method - Google Patents

Abstract

The present invention relates to a blade fixing assembly capable of preventing axial movement of a blade, a gas turbine including the same, and a method for manufacturing a gas turbine.
A blade fixing assembly according to an embodiment of the present invention comprises:
A disk slot having a first groove in a first direction and a second groove in a second direction formed at an end of the first groove; a blade root member which is inserted into the disk slot and has a third groove having a shape corresponding to the first groove and a fourth groove having a shape corresponding to the second groove formed; an insertion space having an insertion hole formed by the first groove and the third groove and a contact hole formed by the second groove and the fourth groove; a key member which, after being inserted into the insertion hole, moves in the direction of the contact hole and contacts an inner wall of the insertion hole; and a spacer which is inserted in parallel with the key member into the insertion hole and restricts movement of the key member.

Description

{Blade fixing assembly, gas turbine comprising it and gas turbine manufacturing method}

The present invention relates to a blade fixing assembly capable of preventing axial movement of a blade, a gas turbine including the same, and a method for manufacturing a gas turbine.

A turbine is a mechanical device that obtains rotational power through impulse or reaction force by utilizing the flow of compressible fluid such as steam or gas. Examples include steam turbines that use steam and gas turbines that use high-temperature combustion gas.

Among these, the gas turbine is largely composed of a compressor, a combustor, and a turbine. The compressor is equipped with an air inlet for introducing air, and a plurality of compressor vanes and compressor blades are arranged alternately within the compressor casing.

The combustor supplies fuel to the compressed air compressed in the compressor and ignites it with a burner, thereby generating high-temperature, high-pressure combustion gas.

The turbine has a plurality of turbine vanes and turbine blades arranged alternately within the turbine casing. In addition, the rotor is arranged to penetrate the center of the compressor, combustor, turbine, and exhaust chamber.

The rotor is rotatably supported at both ends by bearings. Then, a plurality of disks are fixed to the rotor, and each blade is connected, and at the same time, a drive shaft for a generator or the like is connected to the end on the exhaust side.

Since these gas turbines do not have a reciprocating mechanism such as a piston in a four-stroke engine, there are no frictional parts such as pistons and cylinders, so they consume very little lubricating oil, and they have the advantage of greatly reducing the amplitude, which is a characteristic of reciprocating machines, and enabling high-speed operation.

Briefly explaining the operation of a gas turbine, compressed air from a compressor is mixed with fuel and combusted to create high-temperature combustion gas, which is then injected toward the turbine. The injected combustion gas generates rotational force as it passes through the turbine vanes and turbine blades, which in turn causes the rotor to rotate.

US Patent No. 8562301

The present invention aims to provide a blade fixing assembly capable of preventing axial movement of a blade, a gas turbine including the same, and a method for manufacturing a gas turbine.

A blade fixing assembly according to an embodiment of the present invention comprises:

A disk slot having a first groove in a first direction and a second groove in a second direction formed at an end of the first groove; a blade root member which is inserted into the disk slot and has a third groove having a shape corresponding to the first groove and a fourth groove having a shape corresponding to the second groove formed; an insertion space having an insertion hole formed by the first groove and the third groove and a contact hole formed by the second groove and the fourth groove; a key member which, after being inserted into the insertion hole, moves in the direction of the contact hole and contacts an inner wall of the insertion hole; and a spacer which is inserted in parallel with the key member into the insertion hole and restricts movement of the key member.

In a blade fixing assembly according to an embodiment of the present invention, the insertion space may be formed in an L shape.

In a blade fixing assembly according to an embodiment of the present invention, the key member may include a body portion formed in a shape that can be pressed against a sealing member, and a wing portion formed in a bar shape extending outward from one side of the body portion.

In a blade fixing assembly according to an embodiment of the present invention, a portion of the wing portion can be bent to fix at least one side of the spacer.

In a blade fixing assembly according to an embodiment of the present invention, the body portion and the spacer may be formed in a rectangular parallelepiped shape.

A blade gas turbine according to an embodiment of the present invention,

A compressor for compressing air; a combustor for receiving compressed air from the compressor, mixing it with fuel, and combusting it; and a turbine for generating power by rotating by gas combusted from the combustor. In addition, the compressor includes a disk slot having a first groove in a first direction and a second groove in a second direction formed at an end of the first groove; a blade root member inserted into the disk slot and having a third groove having a shape corresponding to the first groove and a fourth groove having a shape corresponding to the second groove; an insertion space having an insertion hole formed by the first groove and the third groove and a sealing hole formed by the second groove and the fourth groove; a key member inserted into the insertion hole and moved in the direction of the sealing hole to seal against an inner wall of the insertion hole; and a blade fixing assembly including a spacer inserted in the insertion hole in parallel with the key member to limit movement of the key member.

In a blade gas turbine according to an embodiment of the present invention, the insertion space can be formed in an L shape.

In a blade gas turbine according to an embodiment of the present invention, the key member may include a body portion formed in a shape that can be pressed against a sealing member, and a wing portion formed in a bar shape extending outward from one side of the body portion.

In a blade gas turbine according to an embodiment of the present invention, a portion of the wing portion may be bent to secure at least one surface of the spacer.

In a blade gas turbine according to an embodiment of the present invention, the body and the spacer may be formed in a rectangular parallelepiped shape.

A method for manufacturing a gas turbine according to an embodiment of the present invention,

The method comprises the steps of: forming a slot groove on the bottom surface of a disk slot; forming a root groove on the lower surface of one side of a blade root member; inserting a blade having a blade root member into the disk slot, so that the slot groove and the root groove form one insertion space having an insertion hole and a sealing hole; inserting a key member into the insertion hole and then sealing the key member with the sealing hole; and inserting a spacer in the extra space of the insertion hole into which the key member is inserted, parallel to the key member.

In a method for manufacturing a gas turbine according to an embodiment of the present invention, the slot groove includes a first groove in a first direction and a second groove extending in a second direction from an end of the first groove, and the root groove includes a third groove having a shape corresponding to the first groove and a fourth groove having a shape corresponding to the second groove.

In a method for manufacturing a gas turbine according to an embodiment of the present invention, a step of fixing at least one side of a spacer by bending a part of a key member may be further included.

In a method for manufacturing a gas turbine according to an embodiment of the present invention, a key member includes a body portion formed in a shape that can be pressed against a sealing member, and a wing portion formed in a bar shape extending outward from one side of the body portion, and a part of the wing portion can be bent to secure at least one side of a spacer.

Specific details of implementation examples according to various aspects of the present invention are included in the detailed description below.

According to an embodiment of the present invention, it is possible to prevent axial movement of the blade. Accordingly, wear due to friction between the blade and the rotor disk can be prevented, thereby improving the durability of the gas turbine.

FIG. 1 is a drawing illustrating the interior of a gas turbine according to one embodiment of the present invention.
FIG. 2 is a conceptual drawing illustrating a cross-section of a gas turbine according to one embodiment of the present invention.
FIG. 3 is a perspective view illustrating a compressor rotor disk according to one embodiment of the present invention.
FIG. 4 is a drawing showing one side of the lower surface of a blade according to one embodiment of the present invention.
FIG. 5 is a perspective view showing the blade of FIG. 4 assembled within the disk slot of the compressor rotor disk of FIG. 3.
Figure 6 is a cross-sectional view taken along the axis of area A of Figure 5.
FIG. 7 is a drawing showing a key member and a spacer, each of which constitutes a blade fixing assembly according to one embodiment of the present invention.
FIGS. 8 to 12 are drawings illustrating a process of installing a blade into a disk slot using a blade fixing assembly according to one embodiment of the present invention.

The present invention can be modified in various ways and has various embodiments, and specific embodiments are illustrated and described in detail in the detailed description. However, this is not intended to limit the present invention to specific embodiments, but should be understood to include all modifications, equivalents, or substitutes included in the spirit and technical scope of the present invention.

The terminology used herein is only used to describe specific embodiments and is not intended to limit the present invention. The singular expression includes the plural expression unless the context clearly indicates otherwise. In the present invention, it should be understood that the terms "comprise" or "have" and the like are intended to specify that a feature, number, step, operation, component, part or combination thereof described in the specification is present, but do not exclude in advance the possibility of the presence or addition of one or more other features, numbers, steps, operations, components, parts or combinations thereof.

Hereinafter, preferred embodiments of the present invention will be described in detail with reference to the attached drawings. At this time, it should be noted that the same components in the attached drawings are indicated by the same symbols as much as possible. In addition, detailed descriptions of well-known functions and configurations that may obscure the gist of the present invention will be omitted. For the same reason, some components in the attached drawings are exaggerated, omitted, or schematically illustrated.

FIG. 1 is a drawing illustrating the interior of a gas turbine according to one embodiment of the present invention, and FIG. 2 is a drawing conceptually illustrating a cross-section of a gas turbine according to one embodiment of the present invention.

As illustrated in FIGS. 1 and 2, a gas turbine (1) according to one embodiment of the present invention includes a compressor (10), a combustor (20), and a turbine (30). The compressor (10) compresses inlet and outlet air to a high pressure and transfers the compressed air to the combustor. The compressor (10) has a plurality of compressor blades installed radially, and receives a portion of the power generated from the rotation of the turbine (30) to rotate the compressor blades, and the air is compressed by the rotation of the blades and moves toward the combustor (20). The size and installation angle of the blades may vary depending on the installation location.

As illustrated in FIGS. 1 and 2, a gas turbine (1) according to one embodiment of the present invention includes a compressor (10), a combustor (20), and a turbine (30). The compressor (10) inhales and compresses outside air, the combustor (20) mixes fuel with the air compressed by the compressor (10) and combusts it, and the turbine (30) is rotated by combustion gas discharged from the combustor (20).

The compressor (10) includes a compressor rotor disc (11), a center tie rod (12), a compressor blade (100), a compressor vane (14), and a compressor housing (15).

The compressor rotor disk (11) fixes the compressor blade (100) and rotates according to the rotation of the center tie rod (12) to rotate the compressor blade (100). There may be a plurality of compressor rotor disks (11).

Compressor rotor discs (11) formed in multiple pieces are connected by a single center tie rod (12) so as not to be spaced apart in the axial direction. Each of the compressor rotor discs (11) is aligned along the axial direction while being penetrated by the center tie rod (12). A plurality of protrusions may be formed on the outer periphery of the compressor rotor disc (11), and a flange may be formed that is coupled to rotate together with an adjacent compressor rotor disc (11).

At least one of the plurality of compressor rotor disks (11) may be formed with a compressed air supply path. Through the compressed air supply path, compressed air compressed by the compressor blades (100) may be moved toward the turbine (30) to cool the turbine blades.

The center tie rod (12) is aligned by penetrating the compressor rotor disk (11). The center tie rod (12) receives torque generated from the turbine (30) and rotates the compressor rotor disk (11). To this end, a torque tube (T) may be arranged between the compressor (10) and the turbine (30) as a torque transmission member that transmits the rotational torque generated from the turbine (30) to the compressor (10).

The compressor blades (100) are radially coupled to the outer surface of the compressor rotor disk (11). The compressor blades (100) may be plural in number and may be formed in multiple stages. Each compressor blade (100) is formed with a dovetail for being fastened to the compressor rotor disk (11). In the present embodiment, the compressor blades (100) and the compressor rotor disk (11) are coupled in a dovetail manner, but are not limited thereto and may be coupled in various ways. The compressor blades (100) rotate according to the rotation of the rotor disk (11) to compress the intake air and move the compressed air to the compressor vane (14) at the rear end.

The compressor vane (14) guides the compressed air moved from the compressor blade (100) of the front end to the compressor blade (100) of the rear end.

The compressor housing (15) forms the outer shape of the compressor (10). The compressor housing (15) accommodates a compressor rotor disk (11), a center tie rod (12), a compressor blade (100), a compressor vane (14), etc., inside.

A connecting pipe may be formed in the compressor housing (15) to allow compressed air compressed in multiple stages by multi-stage compressor blades (100) to flow toward the turbine (30) to cool the turbine blades.

A diffuser for diffusing and moving compressed air is arranged at the outlet of the compressor (10). The diffuser rectifies the compressed air before it is supplied to the combustor and converts some of the kinetic energy of the compressed air into static pressure.

Meanwhile, the fit between the compressor blade (100) and the compressor rotor disk (11) is somewhat loosened in consideration of assembly and tolerance. Accordingly, the compressor blade (100) may move in the direction of the center tie rod (12) (hereinafter, also referred to as the axial direction) due to frequent stoppages of the gas turbine or vibrations occurring during operation of the gas turbine. This axial movement of the compressor blade (100) causes wear due to friction between the compressor blade (100) and the compressor rotor disk (11). Therefore, a method for preventing the axial movement of the compressor blade (100) is required. In the following description, the blade is described by exemplifying the case where the blade is the compressor blade (100), but it is not necessarily limited to the compressor blade (100). That is, it may be applied to a turbine blade depending on the design.

FIG. 3 is a perspective view illustrating a compressor rotor disk according to one embodiment of the present invention, FIG. 4 is a view illustrating one side of a lower surface of a blade according to one embodiment of the present invention, FIG. 5 is a perspective view illustrating a state in which a blade of FIG. 4 is assembled within a disk slot of the compressor rotor disk of FIG. 3, and FIG. 6 is a cross-sectional view taken along the axial direction of area A of FIG. 5.

Referring to FIG. 3, the compressor rotor disk (11) includes a disk slot (11a) into which a root member (110) of a compressor blade (100) is inserted and installed. The disk slot (11a) may be formed in, for example, a dovetail shape.

And, a slot groove (11b) of a predetermined shape is formed on the bottom surface of the disk slot (11a). The slot groove (11b) includes a first groove (11b1) formed to extend in a first direction, and a second groove (11b2) formed to extend in a second direction from an end of the first groove. The first groove (11b1) and the second groove (11b2) may be formed in an overall “ㄱ” shape.

Referring to FIG. 4, the root member (110) of the compressor blade (100) is formed in a shape corresponding to the disk slot (11a). The root member (110) may be formed in, for example, a dovetail shape.

And, a root groove (111) having a shape corresponding to the slot groove (11b) is formed on one side of the lower surface of the root member (110). The root groove (111) includes a third groove (111a1) formed to extend in the first direction, and a fourth groove (111a2) formed to extend in the second direction from an end of the third groove. The third groove (111a1) and the fourth groove (111a2) may be formed in an overall “ㄱ” shape.

Referring to FIGS. 5 and 6, the root member (110) of the compressor blade (100) is axially inserted into the disk slot (11a). At this time, the slot groove (11b) and the root groove (111) are arranged at positions corresponding to each other to form one insertion space (IS). The insertion space (IS) is formed in an overall “ㄱ” shape and has an insertion hole (IS1) formed by the first groove (11b1) and the third groove (111a1), and a sealing hole (IS2) formed by the second groove (11b2) and the fourth groove (111a2).

At this time, as shown in FIG. 6, the key member (120) and the spacer (130) are inserted and placed in one insertion space (IS) to prevent axial movement of the compressor blade (100).

Referring to Fig. 7, the key member (120) and spacer (130) constituting the blade fixing assembly are described.

Referring to (a) of Fig. 7, the key member (120) may be formed in an overall “ㄱ” shape and includes a body portion (121) and a wing portion (122). The body portion (121) is formed in a shape that can be in close contact with the sealing member (IS2). For example, the body portion (121) may be formed in a rectangular solid shape. Of course, it does not necessarily have to be in close contact, and it is sufficient if it is inserted into the sealing member (IS2) while having some space, but its movement is restricted by the spacer (130) so that it does not come off from the sealing member (IS2).

The wing portion (122) may be formed to extend outwardly in a bar shape from one side of the body portion (121). During the manufacturing process, the wing portion (122) may be bent to secure a portion of the spacer (130).

Referring to (b) of Fig. 7, the spacer (130) may be formed in a predetermined shape, for example, a rectangular parallelepiped shape. Of course, it does not necessarily have to be a rectangular parallelepiped shape, and any shape may be used as long as the movement of the key member (120) can be restricted while inserted into the insertion hole (IS1).

Next, a process of installing a blade into a disk slot will be described with reference to FIGS. 8 to 12. FIGS. 8 to 12 are drawings illustrating a process of installing a blade into a disk slot using a blade fixing assembly according to one embodiment of the present invention. Meanwhile, FIGS. 8 to 12 may be process diagrams illustrating a method of manufacturing a gas turbine according to one embodiment of the present invention.

First, a slot groove (11b) is formed on the bottom surface of the disk slot (11a), and a root groove (111) is formed on the lower surface of one side of the blade root member (110).

Next, as shown in Fig. 8, the blade (100) is inserted into the disk slot (11a). At this time, the slot groove (11b) and the root groove (111) are arranged at positions corresponding to each other to form one insertion space (IS). The insertion space (IS) has an insertion opening (IS1) and a sealing opening (IS2).

Next, as shown in FIGS. 9 and 10, after inserting the key member (120) into the insertion hole (IS1), the body part (121) of the key member (120) is pressed against the sealing hole (IS2). At this time, the wing part (122) is pressed against the inner wall of the insertion hole (IS1).

Next, as shown in Fig. 11, a spacer (130) is inserted parallel to the key member (120) into the spare space of the insertion hole (IS1) into which the key member (120) is inserted. The spacer (130) restricts the movement of the key member (120).

Next, as shown in Fig. 12, the wing part (122) of the key member (120) is bent so that a part of the wing part (122) is fixed to one side of the spacer (130). The spacer (130) is prevented from being separated from the insertion hole (IS1) to the outside by the bent wing part (122).

In this way, the blade root member (110) and the disk slot (11a) are assembled using the key member (120) and the spacer (130) inserted into one insertion space (IS) formed by the cooperation of the blade root member (110) and the disk slot (11a), thereby firmly preventing the axial movement of the blade (100). Accordingly, wear due to friction between the blade (100) and the rotor disk (11) is prevented, thereby improving the durability of the gas turbine.

Above, one embodiment of the present invention has been described, but those skilled in the art will be able to modify and change the present invention in various ways by adding, changing, deleting or adding components, etc., within the scope that does not depart from the spirit of the present invention described in the claims, and this will also be considered to be included within the scope of the rights of the present invention.

10: Compressor 11: Compressor rotor disc
11a: Disk slot 11b: Slot groove
100: Compressor blade 110: Root member
111: Root groove 120: Keyless
130 : Spacer IS : Insertion space

Claims (14)

A disk slot having a first groove in a first direction and a second groove in a second direction formed at an end of the first groove;
A blade root member having a third groove formed in direct contact with the bottom surface of the above disk slot and having a fourth groove formed in a shape corresponding to the first groove and a shape corresponding to the second groove;
An insertion space having an insertion hole formed by the first groove and the third groove and a sealing hole formed by the second groove and the fourth groove, and having a cross-sectional shape that is L-shaped when viewed cut in the axial direction;
A key member including a body part formed in a shape that can be pressed into the above-mentioned sealing port and a wing part formed in a bar shape extending outwardly from one side of the body part, wherein after being inserted into the insertion port, the body part is pressed in the direction of the sealing port and the wing part is pressed against the inner wall of the insertion port;
A blade fixing assembly including a spacer inserted parallel to the key member into the insertion port to limit movement of the key member.
delete delete In claim 1,
A blade fixing assembly, wherein a portion of the wing portion is bent to fix at least one side of the spacer.
In claim 1,
A blade fixing assembly, wherein the body portion and the spacer are formed in a rectangular parallelepiped shape.
A compressor for compressing air;
A combustor that receives compressed air from the compressor, mixes it with fuel, and combusts it;
It includes a turbine that generates power by rotating by gas combusted from the above combustor, and the compressor,
A disk slot having a first groove in a first direction and a second groove in a second direction formed at an end of the first groove;
A blade root member having a third groove formed in direct contact with the bottom surface of the above disk slot and having a fourth groove formed in a shape corresponding to the first groove and a shape corresponding to the second groove;
An insertion space having an insertion hole formed by the first groove and the third groove and a sealing hole formed by the second groove and the fourth groove, and having a cross-sectional shape that is L-shaped when viewed cut in the axial direction;
A key member including a body part formed in a shape that can be pressed into the above-mentioned sealing port and a wing part formed in a bar shape extending outwardly from one side of the body part, wherein after being inserted into the insertion port, the body part is pressed in the direction of the sealing port and the wing part is pressed against the inner wall of the insertion port;
A blade fixing assembly including a spacer inserted parallel to the key member in the insertion port to limit movement of the key member
A gas turbine including:
delete delete In claim 6,
A gas turbine, wherein a portion of the wing portion is bent to secure at least one surface of the spacer.
In claim 6,
A gas turbine, wherein the body portion and the spacer are formed in a rectangular parallelepiped shape.
A step of forming a slot groove on the bottom surface of a disk slot;
A step of forming a root groove on the lower surface of one side of the blade root member that directly contacts the bottom surface of the above disk slot;
A step of inserting a blade having the blade root member into the disk slot, so that the slot groove and the root groove have an insertion hole and a contact hole, and form an insertion space having a L-shaped cross-section when viewed by cutting in the axial direction;
A step of inserting a key member including a body part formed in a shape that can be pressed into the above-mentioned sealing port and a wing part formed in a bar shape extending outwardly from one side of the body part into the insertion port, and then pressing the body part into the sealing port and pressing the wing part into the inner wall of the insertion port;
A step of inserting a spacer parallel to the key member into the extra space of the insertion hole into which the key member is inserted;
A step of fixing at least one side of the spacer by bending a part of the wing portion;
A method for manufacturing a gas turbine, comprising:
In claim 11,
The above slot groove includes a first groove in a first direction and a second groove extending in a second direction from an end of the first groove,
A method for manufacturing a gas turbine, wherein the root groove includes a third groove having a shape corresponding to the first groove and a fourth groove having a shape corresponding to the second groove.
delete delete

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