Apparatus and method for disassembling gas turbine disk and shaft bolts

Abstract

This invention provides an apparatus and method for disassembling a gas turbine disc and shaft bolts, comprising a first disassembly mechanism and a second disassembly mechanism detachably connected to opposite ends of a power turbine shaft, the first and second disassembly mechanisms being used to disassemble different shaft bolts; the first disassembly mechanism includes a first fixing member detachably disposed at one end of the power turbine shaft, and a second fixing member sleeved on the shaft body of the power turbine shaft, the first and second fixing members being coaxially arranged and detachably connected by a plurality of first stop bolts, the first fixing member having a bearing platform arranged radially, and the second fixing member having a first stop block slidably disposed thereon, the first stop block being positioned opposite to the shaft bolt; the second disassembly mechanism is detachably disposed at the other end of the power turbine shaft, and a second stop block is disposed through it, the second stop block being positioned opposite to another shaft bolt.

Description

Technical Field

[0001] This invention belongs to the field of gas turbine processing technology, specifically relating to a device and method for disassembling gas turbine discs and shaft bolts. Background Technology

[0002] The positioning and connection of the power turbine rotor shaft and the disk assembly mainly rely on tapered bolts, which are installed on the power turbine shaft and the 3rd, 4th, 5th and 6th stage disk assemblies respectively. When assembling the power turbine rotor, these three rings of holes are combined and machined into tapered holes. The tightening torque of the tapered bolt nut is 100 N·m.

[0003] After tightening and testing, the tapered bolts and holes become an interference fit. If the disc is disassembled after the power turbine is tested, the large tightness of the fit between the tapered bolts and the bolt holes of the disc assembly makes it difficult to disassemble the disc assembly and the power turbine shaft. Traditionally, an aluminum rod is used to knock off the two tapered bolts before disassembling the disc assembly and shaft. This method carries the risk of damaging the tapered bolts. This is because when using an aluminum rod to knock, it is impossible to form accurate coaxial compression. When there is tilting force, the shaft bolt will deform and damage the retaining pin at the end of the tapered bolt. Summary of the Invention

[0004] To address the problems existing in the prior art, the present invention provides an apparatus and method for disassembling gas turbine discs and shaft bolts, thereby solving the technical problem of structural deformation that occurs when disassembling gas turbine discs and shaft bolts in the prior art.

[0005] To achieve the above objectives, the present invention provides the following technical solution:

[0006] An apparatus for disassembling gas turbine discs and shaft bolts includes a first disassembly structure and a second disassembly mechanism detachably connected to opposite ends of a power turbine shaft, wherein the first disassembly structure and the second disassembly mechanism are used to disassemble different shaft bolts.

[0007] The first disassembly mechanism includes a first fixing member detachably disposed at one end of the power turbine shaft, and a second fixing member sleeved on the shaft body of the power turbine shaft. The first fixing member and the second fixing member are coaxially disposed and a plurality of first stop bolts are detachably disposed between them. The second fixing member is provided with a bearing platform in the radial direction. The bearing platform is slidably disposed with a first stop block. The first stop block is positioned opposite to the shaft bolt. The second disassembly mechanism is detachably disposed at the other end of the power turbine shaft, and a second stop block is disposed through it. The second stop block is positioned opposite to the other shaft bolt.

[0008] Furthermore, the first fixing member is a tubular structure with its outer wall threaded to the end of the power turbine shaft. Multiple bearing platforms are provided on the outer edge of the end of the first fixing member away from the power turbine shaft. Each bearing platform is provided with a first stop bolt, and the free end of the first stop bolt abuts against the second fixing member.

[0009] Furthermore, there are five support platforms, which are evenly distributed along the outer edge of the end of the first fixing member.

[0010] Furthermore, the support platform has a plate-shaped protruding structure.

[0011] Furthermore, the first fixing member is radially perforated with a plurality of second stop bolts, the free ends of which abut against a blocking plate inside the power turbine shaft.

[0012] Furthermore, the first fixing member is threadedly connected to the second stop bolt.

[0013] Furthermore, a pressure plate is provided at the connection between the second stop bolt and the blocking plate.

[0014] Furthermore, the second disassembly mechanism is a ring-shaped structure with multiple fixing holes axially extending through its sidewalls. These fixing holes are detachably connected to the set screw holes of the power turbine shaft via fastening screws.

[0015] Furthermore, the fixing hole is axially provided with multiple positioning holes, each of which corresponds to the position of the adjacent shaft bolt, and all of the positioning holes are adapted to the structure of the second stop block.

[0016] A method for disassembling a gas turbine disc and shaft bolts includes the following steps:

[0017] The first disassembly structure and the second disassembly mechanism are respectively set at opposite ends of the power turbine shaft;

[0018] Insert the first stop block into the bearing platform, such that the abutting end of the first stop block abuts against the adjacent shaft bolt;

[0019] Hammer the first stop block to loosen it and then remove it;

[0020] The second stop block is inserted into the second disassembly mechanism, such that the abutting end of the second stop block abuts against the adjacent shaft bolt;

[0021] Hammer the second stop block to loosen it and then remove it, thus completing the disassembly.

[0022] Compared with the prior art, the present invention has the following beneficial technical effects:

[0023] This invention provides an apparatus and method for disassembling gas turbine discs and shaft bolts, comprising a first disassembly structure and a second disassembly mechanism detachably connected to opposite ends of a power turbine shaft. The first disassembly structure and the second disassembly mechanism are used to disassemble different shaft bolts. The first disassembly mechanism includes a first fixing member detachably disposed at one end of the power turbine shaft and a second fixing member sleeved on the shaft body of the power turbine shaft. The first fixing member and the second fixing member are coaxially arranged and detachably connected by multiple first stop bolts. The second fixing member has a bearing platform arranged radially, and a first stop block is slidably disposed on the bearing platform. The first stop block is positioned opposite to the shaft bolt. The second disassembly mechanism is detachably disposed at the other end of the power turbine shaft, and a second stop block is disposed through it. The second stop block is positioned opposite to another shaft bolt. This application uses the first disassembly structure and the second disassembly mechanism to specifically disassemble shaft bolts in different directions. The first stop block and the second stop block can accurately apply axial indirect impact to the shaft bolts, preventing structural deformation due to tilting forces. Attached Figure Description

[0024] Figure 1 This is a schematic diagram of the interference fit between the gas turbine disc and the shaft bolts in an embodiment of this disclosure;

[0025] Figure 2 This is a schematic diagram of the first decomposed structure in an embodiment of this disclosure;

[0026] Figure 3 This is a schematic diagram of the structure of the first fastener in an embodiment of this disclosure;

[0027] Figure 4 This is a schematic diagram of the structure of the second fastener in an embodiment of this disclosure;

[0028] Figure 5 This is an assembly diagram of the first and second fixing members in an embodiment of this disclosure;

[0029] Figure 6 This is a schematic diagram of the second decomposition structure in an embodiment of this disclosure;

[0030] Figure 7 This is a cross-sectional view of the second exploded structure in an embodiment of this disclosure.

[0031] In the attached diagram: 1. Power turbine shaft; 2. First fixing component; 3. Second fixing component; 4. First stop bolt; 5. Support platform; 6. First stop block; 7. Second stop block; 8. Annular structure; 10. Blocking plate; 21. Second stop bolt; 22. Pressure plate; 80. Fixing hole; 81. Positioning hole. Detailed Implementation

[0032] In the following description, only certain exemplary embodiments are briefly described. As those skilled in the art will recognize, the described embodiments can be modified in various ways without departing from the spirit or scope of the invention. Therefore, the drawings and description are considered to be exemplary in nature and not restrictive.

[0033] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," and "circumferential" indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are used only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this invention.

[0034] Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined as "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0035] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral part; they can refer to a mechanical connection, an electrical connection, or a communication connection; they can refer to a direct connection or an indirect connection through an intermediate medium; they can refer to the internal communication of two components or the interaction between two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0036] In this invention, unless otherwise explicitly specified and limited, "above" or "below" the second feature can include direct contact between the first and second features, or contact between the first and second features through another feature between them. Furthermore, "above," "over," and "on top" of the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a higher horizontal level than the second feature. "Below," "below," and "under" the second feature includes the first feature being directly above or diagonally above the second feature, or simply indicates that the first feature is at a lower horizontal level than the second feature.

[0037] It should be understood that, when used in this specification and the appended claims, the terms "comprising" and "including" indicate the presence of the described 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 collections thereof.

[0038] It should also be understood that the terminology used in this specification is for the purpose of describing particular embodiments only and is not intended to limit the invention. As used in this specification and the appended claims, the singular forms “a,” “an,” and “the” are intended to include the plural forms unless the context clearly indicates otherwise.

[0039] It should also be further understood that the term "and / or" as used in this specification and the appended claims refers to any combination of one or more of the associated listed items and all possible combinations, and includes such combinations.

[0040] The accompanying drawings illustrate various structural schematic diagrams according to embodiments disclosed in this invention. These drawings are not to scale, and some details have been enlarged for clarity, and some details may have been omitted. The shapes of the various regions and layers shown in the drawings, as well as their relative sizes and positional relationships, are merely exemplary and may deviate from reality due to manufacturing tolerances or technical limitations. Furthermore, those skilled in the art can design regions / layers with different shapes, sizes, and relative positions as needed.

[0041] The embodiments of the present invention will now be described in detail with reference to the accompanying drawings.

[0042] Figure 1 The diagram shows a schematic of the interference fit between the gas turbine disc and the shaft bolts in an embodiment of this disclosure. In this embodiment, the power turbine shaft 1 is provided with a third-stage disc and a fourth-stage disc located on the same connecting base, and a fifth-stage disc and a sixth-stage disc located on another base. As can be seen from the figure, the shaft bolts on the base are arranged in two opposite directions.

[0043] This invention discloses an embodiment of a device for disassembling gas turbine discs and shaft bolts, such as... Figure 2 and 3 As shown, it includes a first disassembly structure and a second disassembly mechanism that are detachably connected to opposite ends of the power turbine shaft 1, and the first disassembly structure and the second disassembly mechanism are used to disassemble different shaft bolts.

[0044] The first disassembly mechanism includes a first fixing member 2 detachably mounted on one end of the power turbine shaft 1, and a second fixing member 3 sleeved on the shaft body of the power turbine shaft 1. The first fixing member 2 and the second fixing member 3 are coaxially arranged and detachably connected by multiple first stop bolts 4. The second fixing member 3 is radially provided with a support platform 5, and a first stop block 6 is slidably mounted on the support platform 5. The first stop block 6 is positioned opposite to the shaft bolt. The second disassembly mechanism is detachably mounted on the other end of the power turbine shaft 1, and a second stop block 7 is provided through it. The second stop block 7 is positioned opposite to the other shaft bolt. It should be noted that the "opposite arrangement" mentioned in this application refers to their coaxial arrangement, that is, the first stop block 6 is coaxially arranged with the shaft bolt, and the second stop block 7 is also coaxially arranged with the other shaft bolt.

[0045] Preferred, such as Figure 3 As shown, the first fixing member 2 is a tubular structure with its outer wall threaded to the end of the power turbine shaft 1. Multiple bearing platforms 5 are provided on the outer edge of the end of the first fixing member 2 away from the power turbine shaft 1. Each bearing platform 5 is provided with a first stop bolt 4, and the free end of the first stop bolt 4 abuts against the second fixing member 3.

[0046] Specifically, there are five support platforms 5, which are evenly distributed on the outer edge of the end of the first fixing member 2. Furthermore, the support platform 5 is a plate-shaped protrusion structure.

[0047] Preferably, in the embodiments of this disclosure, such as Figure 4 and Figure 5 As shown, the first fixing member 2 is radially provided with a plurality of second stop bolts 21, the free ends of the second stop bolts 21 abutting against the blocking plate 10 inside the power turbine shaft 1; furthermore, the first fixing member 2 is threadedly connected to the second stop bolts 21.

[0048] Furthermore, a pressure plate 22 is provided at the connection between the second stop bolt 21 and the blocking plate 10. The cross-sectional area of ​​the pressure plate 22 is larger than that of the second stop bolt 21. The purpose of this is to reduce local pressure and prevent excessively concentrated force from acting on the surface of the blocking plate 10.

[0049] It should be noted that the side wall of the first fixing member 2 in the first disassembly mechanism is threadedly connected to the power turbine shaft 1, forming axial pressure on the power turbine shaft 1. Secondly, the second stop bolt 21 abuts against the blocking plate 10 inside the power turbine shaft 1, forming reverse abutting pressure, which can further tighten the connection between the first fixing member 2 and the power turbine shaft 1. In this way, the first fixing member 2 can provide more stable support to the second fixing member 4.

[0050] Preferably, in the embodiments of this disclosure, such as Figure 6 and Figure 7 As shown, the second disassembly mechanism is a ring-shaped structure 8, with multiple fixing holes 80 axially extending through its sidewall. The fixing holes 80 are detachably connected to the set screw holes of the power turbine shaft 1 by fastening screws.

[0051] Furthermore, the fixing hole 80 is axially provided with a plurality of positioning holes 81, which are provided one-to-one with the positions of adjacent shaft bolts, and the plurality of positioning holes 81 are adapted to the structure of the second stop block 7.

[0052] It should be noted that in this application, both the first stop block 6 and the second stop block 7 are metal rods, and their abutting ends are equal in cross-section to the adjacent shaft bolts, in order to provide uniform impact force; secondly, the set screw hole of the power turbine shaft 1 is an existing structure.

[0053] This disclosure also provides a method for disassembling a gas turbine disc and shaft bolts, including the following steps:

[0054] The first disassembly structure and the second disassembly mechanism are respectively set at opposite ends of the power turbine shaft 1;

[0055] Insert the first stop block 6 into the bearing platform 5, and make the abutting end of the first stop block 6 abut against the adjacent shaft bolt;

[0056] Hammer the first stop block 6 to cause it to move the adjacent shaft bolt, loosen it, and then remove it.

[0057] The second stop block 7 is inserted into the second disassembly mechanism, and the abutting end of the second stop block 7 abuts against the adjacent shaft bolt;

[0058] Hammer the second stop block 7 to cause it to move the adjacent shaft bolt, loosen it, and then remove it to complete the disassembly.

[0059] The foregoing has shown and described the basic principles, main features, and advantages of the present invention. It will be apparent to those skilled in the art that the invention is not limited to the details of the exemplary embodiments described above, and that the invention can be implemented in other specific forms without departing from its spirit or essential characteristics. Therefore, the embodiments should be considered illustrative and non-limiting in all respects, and the scope of the invention is defined by the appended claims rather than the foregoing description. Thus, all variations falling within the meaning and scope of equivalents of the claims are intended to be included within the scope of the invention. No reference numerals in the claims should be construed as limiting the scope of the claims.

[0060] Furthermore, it should be understood that although this specification describes embodiments, not every embodiment contains only one independent technical solution. This narrative style is merely for clarity. Those skilled in the art should consider the specification as a whole, and the technical solutions in each embodiment can be appropriately combined to form other embodiments that can be understood by those skilled in the art. The above content is only for illustrating the technical concept of the present invention and should not be construed as limiting the scope of protection of the present invention. Any modifications made based on the technical concept proposed in this invention shall fall within the scope of protection of the claims of this invention.

Claims

1. An apparatus for disassembling a gas turbine disk and shaft bolt, characterized by, It includes a first disassembly mechanism and a second disassembly mechanism that are detachably connected to opposite ends of the power turbine shaft (1), and the first disassembly mechanism and the second disassembly mechanism are used to disassemble different shaft bolts; The first disassembly mechanism includes a first fixing member (2) detachably disposed at one end of the power turbine shaft (1) and a second fixing member (3) sleeved on the shaft body of the power turbine shaft (1). The first fixing member (2) and the second fixing member (3) are coaxially disposed and a plurality of first stop bolts (4) are detachably disposed between them. The first fixing member (2) is provided with a bearing platform (5) in the radial direction. The second fixing member (3) is slidably provided with a first stop block (6). The first stop block (6) is disposed opposite to the shaft bolt position. The second disassembly mechanism is detachably mounted on the other end of the power turbine shaft (1), and a second stop block (7) is provided through it. The second stop block (7) is positioned opposite to the other shaft bolt. The first fixing member (2) is a tubular structure, and its outer wall is threaded to the end of the power turbine shaft (1). The outer edge of the first fixing member (2) away from the power turbine shaft (1) is provided with multiple bearing platforms (5). Each bearing platform (5) is provided with a first stop bolt (4) through it. The free end of the first stop bolt (4) abuts against the second fixing member (3). The first fixing member (2) is threadedly connected to the second stop bolt (21); A pressure plate (22) is provided at the connection between the second stop bolt (21) and the blocking plate (10); The second disassembly mechanism is a ring-shaped structure (8), with multiple fixing holes (80) axially extending through its sidewall. The fixing holes (80) are detachably connected to the set screw holes of the power turbine shaft (1) by fastening screws. The annular structure (8) is provided with multiple positioning holes (81) through the axis. The multiple positioning holes (81) are provided in a one-to-one correspondence with the positions of the adjacent shaft bolts, and the multiple positioning holes (81) are all adapted to the structure of the second stop block (7).

2. An apparatus for disassembling a gas turbine disk and shaft bolt as set forth in claim 1, wherein There are five support platforms (5), which are evenly distributed on the outer edge of the end of the first fixing member (2).

3. An apparatus for disassembling a gas turbine disk and shaft bolt as defined in claim 1 wherein, The support platform (5) is a plate-shaped protrusion structure.

4. An apparatus for disassembling gas turbine disk and shaft bolts as defined in claim 1 wherein, The first fixing member (2) is radially provided with a plurality of second stop bolts (21), and the free end of the second stop bolts (21) abuts against the blocking plate (10) inside the power turbine shaft (1).

5. A method of disassembling a gas turbine disk and shaft bolt, characterized by, An apparatus for disassembling gas turbine discs and shaft bolts according to any one of claims 1-4, comprising the following steps: The first and second disassembly mechanisms are respectively located at opposite ends of the power turbine shaft (1); Insert the first stop block (6) into the second fixing member (3) and make the abutting end of the first stop block (6) abut against the adjacent shaft bolt; Hammer the first stop block (6) and cause it to drive the adjacent shaft bolt, loosen it and then remove it; The second stop block (7) is inserted into the second disassembly mechanism, and the abutting end of the second stop block (7) abuts against the adjacent shaft bolt; Hammer the second stop block (7) and cause it to drive the adjacent shaft bolt, loosen it and remove it to complete the disassembly.

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