Suspender beam for a gas turbine rotor

Abstract

This invention discloses a lifting beam for a gas turbine rotor, comprising: a main body extending along a first horizontal direction; and two connecting arms fixed to the main body and spaced apart from each other along the first horizontal direction, the two connecting arms being removably connected to the gas turbine rotor. The main body includes a crossbeam portion and an extension portion extending downward from the crossbeam portion. In the lifting state of the gas turbine rotor, the extension portion extends into a circumferential recess of the gas turbine rotor, such that the lowest point of the main body is lower in the vertical direction than the highest point of the gas turbine rotor. Accordingly, the lifting beam can withstand greater bending moments while providing more space for placing a crane.

Description

Technical Field

[0001] This utility model relates to a lifting beam for a gas turbine rotor. Background Technology

[0002] The hoisting process of a gas turbine rotor requires the use of a lifting beam. Lifting beams are typically designed as straight beams due to their simple geometry. Furthermore, to obtain sufficient operating space, the building's roof and the crane's hook must be high enough for hoisting the gas turbine rotor, which increases construction costs. For example, in some plants, to save costs, the building and crane hook are built very low, resulting in a rather cramped operating space. In other plants, the building's roof is built too low to provide sufficient height for hoisting the gas turbine rotor, necessitating the removal of the building's roof to allow access for an external mobile crane. The increased costs are due to the expense of renting a mobile crane and the extended maintenance time resulting from roof removal / reconstruction.

[0003] Therefore, the design of the lifting beam determines the minimum building and crane height required for hoisting the gas turbine rotor. Every reduction in crane height translates to cost savings, a point that current lifting beam designs do not adequately consider. Utility Model Content

[0004] To overcome the aforementioned deficiencies in the prior art, this utility model proposes a lifting beam for a gas turbine rotor. The gas turbine rotor includes a compressor section, a turbine section, and an intermediate section sleeved on a rotor shaft. The intermediate section is located between the compressor section and the turbine section, and the diameter of the intermediate section is smaller than the diameters of the compressor section and the turbine section, such that the gas turbine rotor forms a circumferential recess on the outer side of the intermediate section. The lifting beam includes: a lifting beam body extending along a first horizontal direction; and two connecting arms fixed to the lifting beam body and spaced apart from each other along the first horizontal direction, and the two connecting arms are removably connected to the gas turbine rotor. The lifting beam body includes a crossbeam portion and an extension portion extending downward from the crossbeam portion. In the lifting state of the gas turbine rotor, the extension portion extends into the circumferential recess of the gas turbine rotor, such that the lowest point of the lifting beam body in the vertical direction is lower than the highest point of the gas turbine rotor in the vertical direction. Accordingly, the presence of the extension results in a lifting beam that is thicker in the middle and thinner at both ends. Since the bending moment borne by the lifting beam in the middle is greater than that at the ends, this arrangement allows the lifting beam to withstand a greater bending moment. Moreover, since the extension occupies the space of the circumferential recess of the gas turbine rotor, which is usually left unused in existing designs, this arrangement also reduces the overall height required for lifting, leaving more space for placing the crane.

[0005] Furthermore, the extension has two opposite ends, and the two ends of the extension are adjacent to the two ends of the crossbeam. The height of the extension in the vertical direction is greatest at the lowest point of the main body of the lifting beam and decreases towards the two ends of the extension, giving the main body of the lifting beam a fish-belly shape. This facilitates the manufacture of the lifting beam and allows it to be adapted to the shape of the gas turbine rotor.

[0006] Furthermore, the main body of the lifting beam defines an internal space, and the lifting beam also includes hooks fixed within the internal space for hooking by a crane hook. This allows for a further reduction in the overall height required for lifting.

[0007] Furthermore, the height of the hook in the vertical direction is lower than the height of the highest point of the gas turbine rotor in the vertical direction. This allows for a further reduction in the overall height required for hoisting.

[0008] Furthermore, the main body of the suspension beam includes: two vertical plates arranged parallel to each other and spaced apart in a second horizontal direction perpendicular to the first horizontal direction to form two side walls of the main body of the suspension beam; and a horizontal plate fixed between the two vertical plates to form the top wall of the main body of the suspension beam. Accordingly, the manufacturing of the suspension beam can be facilitated while ensuring structural stability.

[0009] Furthermore, the hook is at least one rod extending along the second horizontal direction and fixed to the two vertical plates. This facilitates the manufacture of the lifting beam and the attachment of the hook.

[0010] Furthermore, the crossbar includes an opening to allow the crane's hook to pass through. This facilitates hook positioning while ensuring structural stability.

[0011] Furthermore, each of the two vertical plates includes a crossbeam segment and an extension segment connected to each other. The crossbeam segment forms the crossbeam portion, and the extension segment forms the extension portion. The extension segment is positioned below the crossbeam segment and has an inverted triangular shape, with the apex of the inverted triangle being the lowest point of the main body of the lifting beam. The slope of the first inclined side from the apex of the inverted triangle to the end of the extension segment adjacent to the turbine section is greater than the slope of the second inclined side from the apex of the inverted triangle to the end of the extension segment adjacent to the compressor section. This facilitates the manufacture of the lifting beam and allows it to be adapted to the shape of the gas turbine rotor.

[0012] Furthermore, each of the two connecting arms extends along the vertical direction and includes a collar for fitting onto the rotor shaft of the gas turbine rotor. This facilitates the hoisting of the gas turbine rotor onto the lifting beam.

[0013] Furthermore, in the hoisted state of the gas turbine rotor, the compressor section, the intermediate section, and the turbine section of the gas turbine rotor are positioned between the two connecting arms. This improves the hoisting stability of the gas turbine rotor. Attached Figure Description

[0014] The accompanying drawings are provided to further illustrate the present invention and constitute a part of the present invention. The illustrative embodiments and descriptions of the present invention are used to explain the present invention and do not constitute an undue limitation of the present invention. In the drawings:

[0015] Figure 1 The diagram shows a schematic perspective view of the lifting beam of this utility model, in which the gas turbine rotor is suspended on the lifting beam, i.e., in a suspended state;

[0016] Figure 2 It is shown schematically. Figure 1 The side view of the lifting beam and gas turbine rotor shown;

[0017] Figure 3 This is a schematic perspective view of the lifting beam of this utility model;

[0018] Figure 4 It is shown schematically. Figure 3 The side view of the lifting beam shown; and

[0019] Figure 5 It is shown schematically. Figure 3 The top view of the lifting beam shown.

[0020] List of reference numerals

[0021] 100 lifting beam

[0022] 1. Main body of the lifting beam

[0023] 1a Crossbeam

[0024] 1b extension

[0025] 11 vertical boards

[0026] 11a crossbeam slab segment

[0027] 11b extension section

[0028] 12 horizontal boards

[0029] 121 opening

[0030] 2 connecting arms

[0031] 21 rings

[0032] 3-Hook Hanging Item

[0033] 200 gas turbine rotor

[0034] 201 Compressor Section

[0035] 202 Turbine Section

[0036] 203 Intermediate Section

[0037] S rotor shaft

[0038] C circumferential recessed part

[0039] X First horizontal direction

[0040] Y second horizontal direction

[0041] Z vertical direction

[0042] The apex of an inverted triangle

[0043] a First hypotenuse

[0044] b Second hypotenuse Detailed Implementation

[0045] The technical solutions of the embodiments of this utility model will be described in detail below with reference to the accompanying drawings. It should be noted that, unless otherwise specified, the embodiments and features described in these embodiments can be combined with each other.

[0046] In the following detailed description, reference is made to the accompanying drawings, which form a part of this specification, in which specific embodiments of the present invention are illustrated by way of example. Regarding the drawings, directional terms such as “top,” “bottom,” “inner,” “outer,” “upper,” “lower,” “front,” and “rear” are used with reference to the orientation of the drawings described. Since the components of the embodiments of the present invention can be positioned in many different orientations, the directional terms are for illustrative purposes only and are not intended to be limiting. It should be understood that other embodiments can be used, and structural or logical changes can be made without departing from the scope of the present invention. Therefore, the following detailed description should not be construed as limiting, and the present invention is defined by the appended claims.

[0047] refer to Figures 1 to 5 This utility model proposes a lifting beam 100 for a gas turbine rotor 200. The lifting beam 100 is used to lift the gas turbine rotor 200. During the lifting process, the lifting beam 100 and the gas turbine rotor 200 are usually kept in a basically horizontal position, thereby enabling safe and stable lifting.

[0048] The gas turbine rotor 200 includes a compressor section 201, a turbine section 202, and an intermediate section 203 mounted on the rotor shaft S. The intermediate section 203 is located between the compressor section 201 and the turbine section 202, and the diameter of the intermediate section 203 is smaller than the diameters of the compressor section 201 and the turbine section 202, such that the gas turbine rotor 200 has a circumferentially recessed portion C on the outer side of the intermediate section 203. Typically, as... Figure 1 and Figure 2 As shown, the diameter of each stage of the blades in the compressor section 201 and the turbine section 202 gradually increases in the direction away from the intermediate section 203 along the axis of the rotor shaft S, so that the compressor section 201 and the turbine section 202 generally have a roughly truncated conical shape, thereby forming a circumferential recess C on the outside of the intermediate section 203.

[0049] The lifting beam 100 of this utility model generally includes a lifting beam body 1 and two connecting arms 2. The lifting beam body 1 can extend along a first horizontal direction X. The two connecting arms 2 can be fixed to the lifting beam body 1 and spaced apart from each other along the first horizontal direction X, and the two connecting arms 2 can be removably connected to the gas turbine rotor 200.

[0050] In this invention, the main body 1 of the lifting beam may include a crossbeam portion 1a and an extension portion 1b extending downward from the crossbeam portion 1a. The crossbeam portion 1a and the extension portion 1b may be integrally formed for integral manufacturing; alternatively, the crossbeam portion 1a and the extension portion 1b may be independently manufactured and then connected together. In the hoisted state of the gas turbine rotor 200, the extension portion 1b can extend into the circumferential recess C of the gas turbine rotor 200, such that the lowest point of the lifting beam main body 1 in the vertical direction Z is lower than the highest point of the gas turbine rotor 200 in the vertical direction Z. Accordingly, the lifting beam 100 of this invention fully utilizes the space of the circumferential recess C of the gas turbine rotor 200, while simultaneously strengthening the structural strength of the lifting beam 100 itself through the presence of the extension portion 1b.

[0051] Furthermore, the extension 1b has two opposite ends, and the two ends of the extension 1b are adjacent to the two ends of the crossbeam 1a. The height of the extension 1b in the vertical direction Z is greatest at the lowest point of the beam body 1 and decreases towards the two ends of the extension 1b, giving the beam body 1 a fish-belly shape. In particular, for example, the extension 1b can be arranged to transition linearly, curvilinearly, or even irregularly from the lowest point of the beam body 1 to the two ends of the extension 1b, in order to adapt to the shape of different types of gas turbine rotors 200.

[0052] Furthermore, the main body 1 of the lifting beam can define an internal space, and the lifting beam 100 can also include a hook 3 fixed in the internal space for hooking by a crane hook. Accordingly, the hook point can be designed inside the main body 1 of the lifting beam (preferably inside the extension 1b, but it can also be inside the crossbeam 1a) to save height space. Of course, the present invention is not limited to this; for example, the hook can also be provided outside the lifting beam 100 so that the hook point is located above the lifting beam 100.

[0053] Preferably, the height of the hook 3 in the vertical direction Z can be lower than the height of the highest point of the gas turbine rotor 200 in the vertical direction Z. However, this invention is not limited to this; the height of the hook 3 in the vertical direction Z can also be higher than or equal to the height of the highest point of the gas turbine rotor 200 in the vertical direction Z. Under the overall arrangement of the lifting beam 100 mentioned above, this arrangement can also reduce the overall height required for lifting to a certain extent.

[0054] In one embodiment, the main body 1 of the suspension beam may include two vertical plates 11 and a horizontal plate 12. The two vertical plates 11 may be arranged parallel to each other and spaced apart in a second horizontal direction Y perpendicular to the first horizontal direction X to form two side walls of the main body 1. The horizontal plate 12 may be fixed between the two vertical plates 11 to form the top wall of the main body 1. Of course, the present invention is not limited to this, and the main body 1 may have other structural forms, such as an integrally formed structure.

[0055] Furthermore, the hook 3 can be at least one rod extending along the second horizontal direction Y and fixed to the two vertical plates 11, for example, the two rods shown in the figure. Of course, the present invention is not limited to this, and the hook 3 can have any other suitable form.

[0056] Specifically, the cross plate 12 may include an opening 121 to allow the crane hook to pass through, thereby enabling it to enter the interior space of the beam body 1 to hook onto the hook 3 disposed in the interior space.

[0057] Furthermore, each of the two vertical plates 11 may include a crossbeam segment 11a and an extension segment 11b connected to each other. The crossbeam segment 11a forms the crossbeam portion 1a, and the extension segment 11b forms the extension portion 1b. The extension segment 11b is positioned below the crossbeam segment 11a and may have an inverted triangular shape, with the apex A of the inverted triangle being the lowest point of the beam body 1. The slope of the first inclined side a, from the apex A of the inverted triangle to the end of the extension segment 11b adjacent to the turbine section 202, is greater than the slope of the second inclined side b, from the apex A of the inverted triangle to the end of the extension segment 11b adjacent to the compressor section 201. Of course, the shape of the vertical plate 11 is not limited to this; for example, the extension segment 11b of the vertical plate 11 may be semi-circular, etc.

[0058] When the extension segment 11b has an inverted triangular shape, the extension direction of the first inclined side a can match the shape of the turbine section 202 of the gas turbine rotor 200, and the first inclined side a extends adjacent to the outer contour of the turbine section 202; similarly, the extension direction of the second inclined side b can match the shape of the compressor section 201 of the gas turbine rotor 200, and the second inclined side b extends adjacent to the outer contour of the compressor section 201, wherein the first inclined side a and the second inclined side b intersect at the tip A in the circumferential recess C of the gas turbine rotor 200, that is, the lowest point of the lifting beam body 1. Accordingly, the extension 1b can extend further into the circumferential recess C so that the crane hook can be closer to the gas turbine rotor 200.

[0059] Furthermore, each of the two connecting arms 2 may extend along the vertical direction Z and include a collar 21 for fitting onto the rotor shaft S of the gas turbine rotor 200. Of course, the form of the connecting arm 2 is not limited to this; for example, a structure such as a chain or rope may be used as the connecting arm 2 for connection to the gas turbine rotor 200.

[0060] Specifically, in the hoisted state of the gas turbine rotor 200, the compressor section 201, intermediate section 203, and turbine section 202 of the gas turbine rotor 200 are positioned between the two connecting arms 2. Of course, this invention is not limited to this; for example, the two connecting arms 2 can be connected to the compressor section 201 and the turbine section 202.

[0061] The above description is merely a preferred embodiment of this utility model and is not intended to limit the scope of this utility model. Various modifications and variations can be made to this utility model by those skilled in the art. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of this utility model should be included within the protection scope of this utility model.

Claims

1. A lifting beam for a gas turbine rotor, the gas turbine rotor (200) comprising a compressor section (201), a turbine section (202), and an intermediate section (203) sleeved on a rotor shaft (S), the intermediate section (203) being located between the compressor section (201) and the turbine section (202), and the diameter of the intermediate section (203) being smaller than the diameters of the compressor section (201) and the turbine section (202), such that the gas turbine rotor (200) forms a circumferential recess (C) on the outer side of the intermediate section (203), the lifting beam (100) comprising: The main body of the lifting beam (1) extends along the first horizontal direction (X); as well as Two connecting arms (2) are fixed to the main body of the lifting beam (1) and spaced apart from each other along the first horizontal direction (X), and the two connecting arms (2) are removably connected to the gas turbine rotor (200). The feature is that the main body of the lifting beam (1) includes a crossbeam portion (1a) and an extension portion (1b) extending downward from the crossbeam portion (1a). In the hoisting state of the gas turbine rotor (200), the extension portion (1b) extends into the circumferential recess (C) of the gas turbine rotor (200), such that the lowest point of the main body of the lifting beam (1) is lower in the vertical direction (Z) than the highest point of the gas turbine rotor (200) is lower in the vertical direction (Z).

2. The lifting beam for a gas turbine rotor according to claim 1, characterized in that, The extension (1b) has two ends opposite to each other, and the two ends of the extension (1b) are adjacent to the two ends of the crossbeam (1a). The height of the extension (1b) in the vertical direction (Z) is the greatest at the lowest point of the main body of the beam (1) and decreases toward the two ends of the extension (1b), so that the main body of the beam (1) has a fish belly shape.

3. The lifting beam for a gas turbine rotor according to claim 2, characterized in that, The main body (1) of the lifting beam defines an internal space, and the lifting beam (100) also includes a hook (3) fixed in the internal space for being hooked by the hook of a crane.

4. The lifting beam for a gas turbine rotor according to claim 3, characterized in that, The height of the hook (3) in the vertical direction (Z) is lower than the height of the highest point of the gas turbine rotor (200) in the vertical direction (Z).

5. The lifting beam for a gas turbine rotor according to claim 3, characterized in that, The main body of the lifting beam (1) includes: Two vertical plates (11) are arranged parallel to each other and spaced apart in a second horizontal direction (Y) perpendicular to the first horizontal direction (X) to form two side walls of the main body of the suspension beam (1); and A horizontal plate (12) is fixed between the two vertical plates (11) to form the top wall of the main body of the hanging beam (1).

6. The lifting beam for a gas turbine rotor according to claim 5, characterized in that, The hook (3) is at least one rod that extends along the second horizontal direction (Y) and is fixed to the two vertical plates (11).

7. The lifting beam for a gas turbine rotor according to claim 6, characterized in that, The cross plate (12) includes an opening (121) to allow the crane's hook to pass through.

8. The lifting beam for a gas turbine rotor according to claim 5, characterized in that, Each of the two vertical plates (11) includes a beam section (11a) and an extension section (11b) connected to each other. The beam section (11a) forms the beam portion (1a) and the extension section (11b) forms the extension portion (1b). The extension section (11b) is positioned below the beam section (11a) and has an inverted triangular shape. The apex (A) of the inverted triangle is the lowest point of the main body of the lifting beam (1). The slope of the first inclined side (a) from the apex (A) of the inverted triangle to the end of the extension section (11b) adjacent to the turbine section (202) is greater than the slope of the second inclined side (b) from the apex (A) of the inverted triangle to the end of the extension section (11b) adjacent to the compressor section (201).

9. The lifting beam for a gas turbine rotor according to claim 1, characterized in that, Each of the two connecting arms (2) extends along the vertical direction (Z) and includes a collar (21) for fitting onto the rotor shaft (S) of the gas turbine rotor (200).

10. The lifting beam for a gas turbine rotor according to claim 9, characterized in that, In the hoisted state of the gas turbine rotor (200), the compressor section (201), the intermediate section (203) and the turbine section (202) of the gas turbine rotor (200) are positioned between the two connecting arms (2).

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