CN115070665B - Mounting tool and mounting method for turbine disk baffle ring - Google Patents

Abstract

The application provides a mounting tool and a mounting method of a turbine disc baffle ring, wherein the mounting tool comprises the following components: the annular supporting seat is suitable for being installed on the turbine disk; the rotating block is arranged on the supporting seat in a circumferential rotation manner and is provided with a first shaft hole at the radial outer side of the supporting seat; the folding pry bar is provided with a pry bar first part and a pry bar second part, a second shaft hole is formed in the turning part of the pry bar, and the pry bar is arranged on the rotating block in a mode that the second shaft hole is aligned with the first shaft hole; and a rotating shaft adapted to pass through the first shaft hole and the second shaft hole so that the pry bar is adapted to rotate about the rotating shaft, wherein when the support base is mounted on the turbine disk, the pry bar first portion is adapted to extend beyond a stop ring located outside a groove of the turbine disk, and when the pry bar second portion is manipulated to rotate the pry bar, the pry bar first portion presses the stop ring into the groove. By using the installation tool and the installation method, the assembly efficiency of the turbine disc baffle ring can be improved, and the damage of parts is avoided.

Description

Mounting tool and mounting method for turbine disk baffle ring

Technical Field

The application mainly relates to the field of engine assembly, in particular to a mounting tool and a mounting method of a turbine disc baffle ring.

Background

FIG. 1a is a schematic view of a prior art blade stop ring configuration. The turbine disk assembly 10 consists of a turbine disk 11 and blades 12, wherein the blades 12 are arranged in mortises of the turbine disk 11, and axial limiting is realized through a baffle ring 13. The assembled turbine disk assembly 10 is shown in FIG. 1 b.

As shown in fig. 1a, the blade 12 is connected with a dovetail groove or a fir tree type tenon tooth in the circumferential direction of the disk drum, so that the freedom of movement (non-rotation) in the circumferential direction of the blade 12 is limited, and the limitation is performed by a resilient baffle ring 13 in the axial direction. As shown in fig. 1c, the baffle ring 13 has a baffle ring opening 130, and the baffle ring 13 has a certain elasticity due to an opening structure, and can be plugged into a groove formed by a claw of the blade 12 and the turbine disc 11, and the blade 12 is pressed from the rear end, so that the axial limit of the blade 12 is realized.

However, the baffle ring 13 is located in the non-open space 14 where the annular recess formed by the annular flange 110 and the blade edge plate 120 at the rear end of the turbine disk 11 is located, and this annular bandwidth section is narrow and difficult to assemble. Fig. 2 is a schematic view illustrating the installation of the blade retainer ring structure shown in fig. 1 in a conventional assembly manner.

As shown in fig. 2, the open baffle ring 13 needs to be punched into the mounting groove of the baffle ring 13 by a punch 21 (such as a core rod or a screwdriver) matched with a hand hammer 22, as shown in fig. 2, the inner side of the baffle ring 13 is closer to the radial distance of the outer wall of the annular flange 110, when in knocking, the inclination degree of the punch 21 (such as the core rod or the screwdriver) is larger, and the component force in the vertical direction is far greater than the component force in the horizontal direction in the knocking process, so that the baffle ring 13 is subjected to larger vertical component force, and the baffle ring is easy to deform locally. Therefore, stress concentration is easy to occur at the deformation part in the working process of the turbine, and the failure of the baffle ring 13 is caused.

In addition, because the annular band between the blade rim plate 120 and the annular flange 110 is narrower, the blade rim plate 120 or the annular flange 110 is easy to strike when the operation is lost, the thickness of the annular flange 110 and the blade rim plate 120 of the turbine disc 11 is smaller, and once the operation is lost, the damage to parts is also easy to cause.

In view of this, the traditional blade baffle ring structure is simple and easy to install, but the installation difficulty is high, and damage to parts (such as the baffle ring, the annular flange of the turbine disk and the blade edge plate) is easily caused.

Disclosure of Invention

The application aims to solve the technical problem of providing a mounting tool and a mounting method for a turbine disc baffle ring, which can improve the assembly efficiency of the turbine disc baffle ring and avoid deformation failure of the baffle ring and damage of other parts.

In order to solve the technical problem, the application provides an installation tool of a turbine disc baffle ring, which is characterized by comprising the following components: the annular supporting seat is suitable for being installed on the turbine disk; the rotating block can be circumferentially and rotatably arranged on the supporting seat, and a first shaft hole is formed in the radial outer side of the supporting seat; the folding pry bar is provided with a pry bar first part and a pry bar second part, a second shaft hole is formed in the turning part of the pry bar, and the pry bar is arranged on the rotating block in a mode that the second shaft hole is aligned with the first shaft hole; and a rotating shaft adapted to pass through the first shaft hole and the second shaft hole, so that the pry bar is adapted to rotate with the rotating shaft as an axis, wherein when the supporting seat is installed on the turbine disk, the pry bar first portion is adapted to extend towards a baffle ring positioned outside a groove of the turbine disk, and when the pry bar second portion is operated to rotate the pry bar, the pry bar first portion presses the baffle ring into the groove.

In one embodiment of the application, the installation tool further comprises a nut adapted to be tightened on the spindle to fixedly mount the spindle to the rotating block.

In an embodiment of the application, the support base is in a circular ring shape, and the circular ring shape is matched with the shape of the annular flange of the turbine disc, so that the support base is suitable for being mounted on the annular flange.

In an embodiment of the application, a support groove is formed at the bottom of the rotating block, and the support groove is suitable for being inserted on the support seat so that the rotating block is mounted on the support seat.

In an embodiment of the application, the support base has a first ring and a second ring in a stepped manner, the first ring having a diameter greater than that of the second ring, and the support groove is adapted to be inserted into the second ring so that the rotating block is mounted on the support base.

In an embodiment of the application, the mounting tool further includes a pin, and the first ring is provided with a pin hole, and the pin is adapted to pass through the pin hole, so that the support seat is fixedly mounted on the annular flange.

In an embodiment of the application, the supporting groove is provided with a first groove wall located on the radial inner side of the supporting seat and a second groove wall located on the radial outer side of the supporting seat, wherein the length of the first groove wall in the vertical direction is larger than that of the second groove wall in the vertical direction.

In one embodiment of the present application, the included angle between the first portion of the pry bar and the second portion of the pry bar is 10 ° to 170 °.

In order to solve the technical problems, the application also provides a method for installing the turbine disc baffle ring, which is applicable to the tool for installing the turbine disc baffle ring, and is characterized by comprising the following steps:

s1: placing the annular supporting seat on the annular flange mounting edge of the turbine disc;

s2: inserting a pry bar into the rotating block, and screwing the rotating shaft by using a nut so that the pry bar is fixedly arranged in the rotating block;

s3: placing a rotating block on a second ring of the annular support base;

s4: pulling a second part of the pry bar inwards along the radial direction of the annular supporting seat so as to enable the pry bar to rotate around the rotating shaft, and pressing the baffle ring into a groove of the turbine disc by the first part of the pry bar; and

s5: and (4) rotating the rotating block to the position of the next baffle ring along the second ring, and repeating the step (S4) until all the baffle rings to be installed are pressed into grooves of the turbine disc at the corresponding positions.

In an embodiment of the present application, in step S1, the method further includes inserting a bolt into the turbine disc through a bolt hole in the annular support base, so that the annular support base is fixedly mounted on an annular flange mounting edge of the turbine disc.

Compared with the prior art, the application provides the prying bar capable of rotating circumferentially, and the prying bar has the advantages that the opening elastic baffle ring is pried into the groove formed by the blade claw and the turbine disc, and the prying bar has the following advantages:

the mounting tool is used for fixing the supporting seat through the annular flange of the turbine disc, the rotating block is fixed on the stepped annular boss of the supporting seat through the supporting groove and can rotate along the stepped annular boss, so that 360-degree rotation of the pry bar along the circumferential direction of the turbine disc is realized, and any position can be reached;

when the pry bar rotates along the axis of the fixed rotating shaft in the installation process, the baffle ring is extruded outwards, and the baffle ring is extruded into the groove; and

the tool is simple to operate and high in efficiency, and reduces the cost while improving the installation efficiency of the baffle ring.

Drawings

The accompanying drawings, which are included to provide a further understanding of the application and are incorporated in and constitute a part of this specification, illustrate embodiments of the application and together with the description serve to explain the principles of the application. In the accompanying drawings:

FIGS. 1a-1c are schematic illustrations of blade baffle ring structures;

FIG. 2 is a schematic view of the installation of a blade stop ring structure in a conventional assembly manner;

FIG. 3 is an effect diagram of a turbine disk stop ring installation tool of the present application on a turbine disk;

FIG. 4 is a cross-sectional view of an installation tool for a turbine disk stop ring of the present application on a turbine disk in the direction A-A as shown in FIG. 3;

FIG. 5a is a schematic view of the construction of an installation tool for a turbine disc stop ring of the present application; and

FIG. 5B is a cross-sectional view of an installation tool for a turbine disk stop ring of the present application taken along the direction B-B as shown in FIG. 5 a;

FIG. 6 is a flow chart of a method of installing a turbine disk stop ring of the present application.

Detailed Description

In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings that are used in the description of the embodiments will be briefly described below. It is apparent that the drawings in the following description are only some examples or embodiments of the present application, and it is apparent to those of ordinary skill in the art that the present application may be applied to other similar situations according to the drawings without inventive effort. Unless otherwise apparent from the context of the language or otherwise specified, like reference numerals in the figures refer to like structures or operations.

As used in the specification and in the claims, the terms "a," "an," "the," and/or "the" are not specific to a singular, but may include a plurality, unless the context clearly dictates otherwise. In general, the terms "comprises" and "comprising" merely indicate that the steps and elements are explicitly identified, and they do not constitute an exclusive list, as other steps or elements may be included in a method or apparatus.

The relative arrangement of the components and steps, numerical expressions and numerical values set forth in these embodiments do not limit the scope of the present application unless it is specifically stated otherwise. Meanwhile, it should be understood that the sizes of the respective parts shown in the drawings are not drawn in actual scale for convenience of description. Techniques, methods, and apparatus known to one of ordinary skill in the relevant art may not be discussed in detail, but should be considered part of the specification where appropriate. In all examples shown and discussed herein, any specific values should be construed as merely illustrative, and not a limitation. Thus, other examples of the exemplary embodiments may have different values. It should be noted that: like reference numerals and letters denote like items in the following figures, and thus once an item is defined in one figure, no further discussion thereof is necessary in subsequent figures.

In the description of the present application, it should be understood that the azimuth or positional relationships indicated by the azimuth terms such as "front, rear, upper, lower, left, right", "lateral, vertical, horizontal", and "top, bottom", etc., are generally based on the azimuth or positional relationships shown in the drawings, merely to facilitate description of the present application and simplify the description, and these azimuth terms do not indicate and imply that the apparatus or elements referred to must have a specific azimuth or be constructed and operated in a specific azimuth, and thus should not be construed as limiting the scope of protection of the present application; the orientation word "inner and outer" refers to inner and outer relative to the contour of the respective component itself.

Spatially relative terms, such as "above … …," "above … …," "upper surface at … …," "above," and the like, may be used herein for ease of description to describe one device or feature's spatial location relative to another device or feature as illustrated in the figures. It will be understood that the spatially relative terms are intended to encompass different orientations in use or operation in addition to the orientation depicted in the figures. For example, if the device in the figures is turned over, elements described as "above" or "over" other devices or structures would then be oriented "below" or "beneath" the other devices or structures. Thus, the exemplary term "above … …" may include both orientations of "above … …" and "below … …". The device may also be positioned in other different ways (rotated 90 degrees or at other orientations) and the spatially relative descriptors used herein interpreted accordingly.

In addition, the terms "first", "second", etc. are used to define the components, and are only for convenience of distinguishing the corresponding components, and the terms have no special meaning unless otherwise stated, and therefore should not be construed as limiting the scope of the present application. Furthermore, although terms used in the present application are selected from publicly known and commonly used terms, some terms mentioned in the present specification may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein. Furthermore, it is required that the present application is understood, not simply by the actual terms used but by the meaning of each term lying within.

It will be understood that when an element is referred to as being "on," "connected to," or "contacting" another element, it can be directly on, connected or coupled to, or contacting the other element or intervening elements may be present. In contrast, when an element is referred to as being "directly on," "directly connected to," or "directly contacting" another element, there are no intervening elements present.

The embodiment of the application provides a mounting tool for a turbine disc baffle ring, which can improve the assembly efficiency of the turbine disc baffle ring and avoid deformation failure of the baffle ring and damage of other parts.

Fig. 3 and 4 are an effect view of a mounting tool for a turbine disk stop ring of the present application on a turbine disk and a sectional view taken along A-A in fig. 3, respectively. Fig. 5a and 5B are a schematic structural view of an installation tool of a turbine disc retaining ring of the present application and a sectional view taken along the direction B-B as shown in fig. 5a, respectively. The following description is made with reference to fig. 3 to 5b of the structure of an installation tool of a turbine disc stop ring of the present application,

in the drawings, the same reference numerals are used for the same corresponding parts. Further, the structural parts relating to the turbine disk and the baffle ring of the engine in fig. 3 to 5b are also given the same reference numerals as in fig. 1 and 2 to more clearly illustrate the differences in the installation tool and installation method of the present application from the conventional assembly method of the prior art.

First, as shown in fig. 5a, an installation tool 50 for a turbine disk retainer ring of the present application includes an annular supporting seat 51, a rotating block 52, a folding pry bar 53 and a rotating shaft 54.

In particular, the annular support seat 51 is adapted to be mounted on the turbine disk 11 as shown in fig. 3.

In the embodiment of the application shown in fig. 5a, the support seat 51 is in the shape of a ring matching the shape of the annular flange of the turbine disk of the engine. Illustratively, the annular flange 110 as shown in FIG. 1a is annular in shape, so the support seat 51 is also designed to match the annular flange 110 in an annular shape, such that the support seat 51 is adapted to be mounted on the annular flange 110 and thus on the turbine disk 11.

As further shown in fig. 5a, the rotating block 52 is circumferentially rotatably mounted on the support base 51, and the rotating block 52 is provided with a first shaft hole (the shaft hole is not explicitly shown in the figure due to shielding of the other mounted part) radially outside the support base 51.

Further, the folding pry bar 53 has a pry bar first portion 531 and a pry bar second portion 532, and the turning portion of the pry bar 53 has a second axial hole (as above, the blind axial hole due to the other mounted portions is not shown explicitly), and the pry bar 53 is mounted on the rotating block 52 in such a manner that the second axial hole is aligned with the first axial hole of the rotating block 52.

Finally, the shaft 54 is adapted to pass through the first shaft hole of the rotating block 52 and the second shaft hole of the folding-shaped pry bar 53, so that the pry bar 53 is adapted to rotate about the shaft 54.

A cross-sectional view of the installed installation tool 50 along the B-B direction as shown in fig. 5a is shown in fig. 5B. Referring again to fig. 5b and 4, which are cross-sectional views of the installation tool 50 on the turbine disk 11 taken along the direction A-A as shown in fig. 3, it is clear how the installation tool 50 is mounted on the turbine disk 11 for mounting the turbine disk stop ring. Specifically, as shown in fig. 4, when the support base 51 is mounted on the turbine disk 11, the pry bar first portion 531 is adapted to extend the stop ring 13 located outside the groove of the turbine disk 11, and when the pry bar second portion 532 is manipulated to rotate the pry bar 53 in the direction a, the pry bar first portion 531 presses the stop ring 13 into the groove in the direction b.

With continued reference to fig. 5a, in the embodiment of the present application shown in fig. 5a, the installation tool 50 further includes a nut 533, the nut 533 being adapted to be tightened onto the spindle 54 to fixedly mount the spindle 54 to the rotating block 52.

In the embodiment of the present application shown in fig. 5a, a supporting groove 520 (shown by a dashed line in fig. 5 b) is further provided at the bottom of the rotating block 52, and the supporting groove 520 is adapted to be inserted into the supporting seat 51, so that the rotating block 52 is mounted on the supporting seat 51, but the present application is not limited thereto.

Further, as shown in fig. 5b, in the embodiment of the present application shown in fig. 5a and 5b, the support base 51 has a stepped first ring 511 and a second ring 512, the diameter of the first ring 511 is larger than that of the second ring 512, and the support groove 520 is adapted to be inserted into the second ring 512, so that the rotating block 52 is mounted on the support base 51.

Still further, in the embodiment of the present application shown in fig. 5a, the installation tool 50 further includes a plurality of pins 513, and a plurality of corresponding pin holes are formed on the first ring 511 (the position of the second ring 511 into which the pins are inserted is the position of the pin holes), and the pins 513 are adapted to pass through the pin holes, so that the support base 51 is fixedly installed on the annular flange 110 shown in fig. 1a, but the present application is not limited thereto.

Specifically, in the embodiment of the present application shown in fig. 5a, the supporting groove 520 has a first groove wall 5201 located radially inward of the supporting seat 51 and a second groove wall 5202 located radially outward of the supporting seat 51, wherein the length of the first groove wall 5201 in the vertical direction is greater than the length of the second groove wall 5202 in the vertical direction. The supporting groove 520 has a shape design with low outside and high inside, so that the installation tool can bear larger radial force, the stability is good, and the self-positioning of the rotating block 52 on the supporting seat 51 can be realized without other fasteners.

In one embodiment of the present application, the angle between first portion 531 and second portion 532 includes 10 to 170.

The mounting tool provided by the application can be used for replacing the traditional mode of using a punch to be matched with a hand hammer to mount the turbine disc baffle ring as shown in fig. 2, and the annular supporting seat matched with the annular flange shape of the turbine disc is used, so that the baffle rings at different positions of the turbine disc can be quickly and conveniently mounted by only using one mounting tool, and the assembly efficiency of the turbine disc baffle ring is improved. Meanwhile, the mounting tool disclosed by the application skillfully uses the structure of the folding pry bar, so that the turbine disc baffle ring is conveniently and laborsaving to mount in a narrow gap, and deformation failure of the baffle ring and damage of other parts are avoided.

Another aspect of the present application provides a method for installing a turbine disc retaining ring, which may be applied to the above-mentioned installation tool for a turbine disc retaining ring, including the installation tool 50 shown in fig. 5 a. A method of installing a turbine disk stop ring of the present application will be described with reference to fig. 4, 5a and 6.

As shown in fig. 6, a method 60 for installing a turbine disk stop ring of the present application includes the steps of:

s1: placing the annular support seat 51 on the annular flange mounting edge of the turbine disk 11 as shown in fig. 4;

s2: inserting the pry bar 53 into the rotating block 52, and screwing the rotating shaft 54 by using the nut 533 so that the pry bar 53 is fixedly installed in the rotating block 52;

s3: placing the rotating block 52 on the second ring 512 of the annular support 51;

s4: pulling the second portion 532 radially inward of the annular support 51 to rotate the pry bar 53 about the rotational axis 54, and the first portion 531 pressing the retainer ring 13 shown in fig. 4 into the groove of the turbine disk 11; and

s5: the rotating block 52 is rotated along the second ring 512 to the position of the next baffle ring 13, and step S4 is repeated until all baffle rings 13 to be installed are pressed into grooves of the turbine disk in the corresponding positions.

In an embodiment of the present application, in step S1, the bolts 513 shown in fig. 5a are inserted into the turbine disk 11 through the bolt holes in the annular supporting seat 51 (the effect of the inserted bolts is shown in fig. 4), so that the annular supporting seat 51 is fixedly mounted on the annular flange mounting edge of the turbine disk 11.

Fig. 6 of the present application uses a flowchart to illustrate operations performed by a system according to an embodiment of the present application. It should be understood that the preceding or following operations are not necessarily performed in order precisely. Rather, the various steps may be processed in reverse order or simultaneously. At the same time, other operations are added to or removed from these processes.

For further details regarding the method for installing a turbine disc stop ring according to the present application, reference may be made to the above description regarding the tool for installing a turbine disc stop ring according to the present application, which is not repeated herein.

The installation tool and the installation method for the turbine disc baffle ring can pry the baffle ring into the installation groove through the pry bar capable of rotating circumferentially, so that the non-damage installation of the baffle ring is realized. In the installation, the supporting groove of rotatory piece cooperatees with the cascaded annular boss of annular supporting seat, realizes rotatory piece quick installation location, and rotatory piece drives the pinch bar and rotates along the circumference, realizes that the backing ring optional position sled is gone into, easy operation, safety and high efficiency.

On the basis, the supporting groove on the rotating block can adopt a design with low outside and high inside, so that the rotating block bears larger radial force, has good stability, and can realize the self-positioning of the rotating block without other fasteners. In general, the mounting tool and the mounting method of the turbine disc baffle ring utilize the lever principle, the pry bar can rotate along the fixed rotating shaft, the baffle ring is extruded outwards, the baffle ring is easily extruded into the groove, and deformation failure of the baffle ring and damage to other parts are avoided while the assembly efficiency of the turbine disc baffle ring is improved.

While the basic concepts have been described above, it will be apparent to those skilled in the art that the foregoing disclosure is by way of example only and is not intended to be limiting. Although not explicitly described herein, various modifications, improvements and adaptations of the application may occur to one skilled in the art. Such modifications, improvements, and modifications are intended to be suggested within the present disclosure, and therefore, such modifications, improvements, and adaptations are intended to be within the spirit and scope of the exemplary embodiments of the present disclosure.

Meanwhile, the present application uses specific words to describe embodiments of the present application. Reference to "one embodiment," "an embodiment," and/or "some embodiments" means that a particular feature, structure, or characteristic is associated with at least one embodiment of the application. Thus, it should be emphasized and should be appreciated that two or more references to "an embodiment" or "one embodiment" or "an alternative embodiment" in various positions in this specification are not necessarily referring to the same embodiment. Furthermore, certain features, structures, or characteristics of one or more embodiments of the application may be combined as suitable.

Aspects of the application may be implemented entirely in hardware, entirely in software (including firmware, often times

Similarly, it should be noted that in order to simplify the description of the present disclosure and thereby aid in understanding one or more inventive embodiments, various features are sometimes grouped together in a single embodiment, figure, or description thereof. This method of disclosure, however, is not intended to imply that more features than are required by the subject application. Indeed, less than all of the features of a single embodiment disclosed above.

In some embodiments, numbers describing the components, number of attributes are used, it being understood that such numbers being used in the description of embodiments are modified in some examples by the modifier "about," approximately, "or" substantially. Unless otherwise indicated, "about," "approximately," or "substantially" indicate that the number allows for a 20% variation. Accordingly, in some embodiments, numerical parameters set forth in the specification and claims are approximations that may vary depending upon the desired properties sought to be obtained by the individual embodiments. In some embodiments, the numerical parameters should take into account the specified significant digits and employ a method for preserving the general number of digits. Although the numerical ranges and parameters set forth herein are approximations in some embodiments for use in determining the breadth of the range, in particular embodiments, the numerical values set forth herein are as precisely as possible.

While the application has been described with reference to the specific embodiments presently, it will be appreciated by those skilled in the art that the foregoing embodiments are merely illustrative of the application, and various equivalent changes and substitutions may be made without departing from the spirit of the application, and therefore, all changes and modifications to the embodiments are intended to be within the scope of the appended claims.

Claims (10)

1. An installation tool for a turbine disk stop ring, comprising:

the annular supporting seat is suitable for being installed on the turbine disk;

the rotating block can be circumferentially and rotatably arranged on the supporting seat, and a first shaft hole is formed in the radial outer side of the supporting seat;

the folding pry bar is provided with a pry bar first part and a pry bar second part, a second shaft hole is formed in the turning part of the pry bar, and the pry bar is arranged on the rotating block in a mode that the second shaft hole is aligned with the first shaft hole; and

a rotating shaft which is suitable for penetrating through the first shaft hole and the second shaft hole so that the pry bar is suitable for rotating by taking the rotating shaft as an axis,

wherein the first portion of the pry bar is adapted to extend toward a stop ring located outside of a groove of the turbine disk when the support base is mounted on the turbine disk, and to press the stop ring into the groove when the pry bar is rotated by manipulating the second portion of the pry bar.

2. The installation tool of claim 1, further comprising a nut adapted to be tightened onto the shaft to fixedly mount the shaft to the rotating block.

3. The installation tool of claim 1, wherein the support base is annular in shape that matches the shape of the annular flange of the turbine disk such that the support base is adapted to be mounted on the annular flange.

4. A mounting tool according to claim 3, wherein the bottom of the rotating block is provided with a support slot adapted to be inserted into the support seat so that the rotating block is mounted to the support seat.

5. The installation tool of claim 4, wherein the support base has a stepped first ring and a second ring, the first ring having a diameter greater than a diameter of the second ring, the support slot being adapted to be inserted over the second ring to mount the rotating block to the support base.

6. The installation tool of claim 5, further comprising a pin, wherein the first ring has a pin hole, and wherein the pin is adapted to pass through the pin hole to fixedly mount the support base to the annular flange.

7. The installation tool of claim 4, wherein the support groove has a first groove wall located radially inward of the support seat and a second groove wall located radially outward of the support seat, wherein a length of the first groove wall in a vertical direction is greater than a length of the second groove wall in a vertical direction.

8. The installation tool of claim 1, wherein the included angle of the first portion of the pry bar and the second portion of the pry bar comprises 10 ° to 170 °.

9. A method for installing a turbine disk stop ring, adapted to the turbine disk stop ring installation tool according to claim 1, comprising the steps of:

s1: placing the annular supporting seat on the annular flange mounting edge of the turbine disc;

s2: inserting a pry bar into the rotating block, and screwing the rotating shaft by using a nut so that the pry bar is fixedly arranged in the rotating block;

s3: placing a rotating block on a second ring of the annular support base;

s4: pulling a second part of the pry bar inwards along the radial direction of the annular supporting seat so as to enable the pry bar to rotate around the rotating shaft, and pressing the baffle ring into a groove of the turbine disc by the first part of the pry bar; and

s5: and (4) rotating the rotating block to the position of the next baffle ring along the second ring, and repeating the step (S4) until all the baffle rings to be installed are pressed into grooves of the turbine disc at the corresponding positions.

10. The method of installation of claim 9, further comprising inserting a pin through a pin hole in the annular support base onto the turbine disk such that the annular support base is fixedly mounted on an annular flange mounting edge of the turbine disk in step S1.