CN115519513B - Method and tool structure for decomposing interference fit structure of turbine rotor - Google Patents
Method and tool structure for decomposing interference fit structure of turbine rotor Download PDFInfo
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- CN115519513B CN115519513B CN202211470839.2A CN202211470839A CN115519513B CN 115519513 B CN115519513 B CN 115519513B CN 202211470839 A CN202211470839 A CN 202211470839A CN 115519513 B CN115519513 B CN 115519513B
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B25—HAND TOOLS; PORTABLE POWER-DRIVEN TOOLS; MANIPULATORS
- B25B—TOOLS OR BENCH DEVICES NOT OTHERWISE PROVIDED FOR, FOR FASTENING, CONNECTING, DISENGAGING OR HOLDING
- B25B27/00—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for
- B25B27/02—Hand tools, specially adapted for fitting together or separating parts or objects whether or not involving some deformation, not otherwise provided for for connecting objects by press fit or detaching same
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- Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
- Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
- Y02E—REDUCTION OF GREENHOUSE GAS [GHG] EMISSIONS, RELATED TO ENERGY GENERATION, TRANSMISSION OR DISTRIBUTION
- Y02E10/00—Energy generation through renewable energy sources
- Y02E10/20—Hydro energy
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Abstract
The invention belongs to the technical field of disassembly tools of gas turbine engines, and particularly relates to a method and a tool structure for disassembling a turbine rotor interference fit structure; the tool structure comprises a hard cushion piece, an arc-shaped abutting piece and an ejection screw; the flange part of the arc-shaped abutting piece can abut against the outer edge of the shaft neck disc part of the turbine shaft; the ejection screw can be abutted against the front cushion surface of the hard cushion piece; a flange disc part is arranged on the front side of the disc surface of the turbine disc, and a back groove of the flange disc is formed between the flange disc part and the disc surface of the turbine disc; the ejection screw is in threaded fit with the arc abutting piece and can push the arc abutting piece away from the hard cushion piece. The tool structure and the disassembling method have the advantages of simplicity, good manufacturability, low cost, good replaceability and the like; the purpose of disassembling the turbine rotor is effectively achieved, the situation that the top thread holes are formed in the turbine disc and the turbine shaft is avoided, and the disassembling work can be completed only by matching the original structures of the turbine disc and the turbine shaft with the tool structure.
Description
Technical Field
The invention belongs to the technical field of disassembly tools of gas turbine engines, and particularly relates to a method and a tool structure for disassembling a turbine rotor interference fit structure.
Background
The turbine rotor is an important component of a gas turbine as a power component of the turbine. The turbine rotor is mainly formed by combining parts or assembly structures such as turbine working blades, a turbine disc, a turbine shaft and the like. In order to achieve the purposes of convenient maintenance and fault removal, the turbine rotor of the modern gas turbine usually adopts a split structural design. Therefore, when disassembling the turbine rotor, it is usually necessary to disassemble the turbine rotor into two main unit body parts, i.e., the turbine disk assembly and the turbine shaft. Because the turbine rotor needs to be tightly connected when in use and the stability of the turbine rotor in the rotating process is ensured, and in order to ensure the tightness and the stability of the connection, the turbine disc and the turbine shaft are in interference fit, but how to disassemble the turbine disc and the turbine shaft under the condition of no damage or low damage is always a problem which is difficult to handle.
In traditional mechanical structure field, in order to realize the dismantlement to interference fit's spare part combination, can design the jackscrew hole on the part that needs were dismantled usually, when needs are dismantled, can utilize the screw rod to penetrate in the jackscrew hole to will push up rather than interference fit's spare part. However, in consideration of the specificity of the extreme environment in which the turbine rotor works, the operation requirement on the disassembly process, the safety of the turbine rotor and other problems, the method for disassembling the interference fit structure by using the jackscrew hole has the following great defects:
1) When each part of the gas turbine engine is tested or applied on the machine, the defect-free inspection of structures such as screw holes, screw threads and the like is often required, but the operation difficulty of the operation is high, so that the operation is inconvenient to realize, and particularly if a jackscrew hole is additionally arranged on a turbine rotor, not only is more inspection work brought, but also more uncertainty is added for the safe operation of the turbine rotor.
2) By utilizing the jackscrew hole, in the process of disassembling the turbine disc and the turbine shaft, as the thread screw in the jackscrew hole needs to bear huge acceptance, the thread screw in the jackscrew hole can be damaged, and any thread damage on the turbine rotor can cause the turbine rotor to be no longer in line with the process requirements or form the defect of not being allowed, and the turbine shaft or the turbine disc is scrapped in severe cases, thereby causing huge economic loss.
3) In addition, if the threaded hole is added to the turbine shaft for easy detachment, stress concentration may occur during high-speed operation of the turbine rotor, which may affect the safety of the operation of the turbine rotor.
These problems, if not solved well, can also lead to other serious consequences, such as cracks in the turbine shaft, etc.; therefore, it is necessary to design a method or a tooling structure that can be disassembled in a state that the turbine rotor is in an interference fit state to separate the turbine disk from the turbine shaft.
Disclosure of Invention
In order to solve the problem that an interference fit structure formed by a turbine disc and a turbine shaft of a turbine rotor is difficult to disassemble, the scheme provides a method and a tool structure for disassembling the interference fit structure of the turbine rotor.
The technical scheme adopted by the invention is as follows:
a method for disassembling a turbine rotor interference fit structure, comprising the steps of:
step A: a plurality of hard cushion pieces and a plurality of arc-shaped abutting pieces are respectively arranged on the periphery of the flange plate back groove; a flange disc part is arranged on the front side of the disc surface of the turbine disc, and a back groove of the flange disc is formed between the flange disc part and the disc surface of the turbine disc; the notch of the flange plate back groove faces to the radial outer side of the flange plate back groove, and the hard cushion pieces correspond to the arc abutting pieces one by one and are arranged in the flange plate back groove;
and B, step B: the hard cushion piece is abutted against the disc surface of the turbine disc, the arc abutting piece is abutted against a shaft neck ring buckling part of the turbine shaft, and the shaft neck ring buckling part is arranged on the outer edge of a shaft neck disc part of the turbine shaft and exceeds a flange disc part;
and C: and controlling each arc abutting piece to be far away from the corresponding hard cushion piece, so that the arc abutting pieces push the turbine shaft to be far away from the turbine disc, and the decomposition of the turbine rotor is realized. In the above steps, when the turbine rotor is in a horizontal state, a hard pad and an arc abutting piece can be respectively placed at the positions of the flange back groove in four directions, namely up, down, left and right, when the wedge-shaped part or the ejection screw is used for controlling the corresponding arc abutting piece to be away from the hard pad, the arc abutting piece can push the turbine shaft to be away from the turbine disc, so that the turbine disc and the turbine shaft of the turbine rotor are decomposed into a disassembly state from an interference fit state, in the above processes, because the pressure applied to the turbine shaft by the arc abutting piece and the pressure applied to the turbine disc by the hard pad are parallel to the axial direction of the turbine rotating shaft, the stress area is large, the turbine disc and the turbine bearing cannot be damaged due to overlarge pressure, the turbine disc and the turbine shaft can be protected to a large extent, and non-damage or low-damage disassembly is realized.
In addition to or as an alternative to the above-described method for disassembling a turbine rotor interference fit structure: an internal thread hole is formed in the arc-shaped abutting piece, and an ejecting screw in threaded fit with the internal thread hole is arranged in the internal thread hole; when the ejection screw is rotated, the screw-in end of the ejection screw can tightly abut against the hard pad piece, and the arc abutting piece is pushed away from the hard pad piece. The ejecting screws are matched with the threaded connection structure of the internal threaded holes, so that the rotary displacement of the ejecting screws can be converted into the axial thrust of the ejecting screws, and the turbine disc and the turbine shaft can be disassembled from the interference fit state only by using small force; in addition, because the position bearing larger pressure is arranged on the inner threaded hole of the arc-shaped abutting piece in the rotation process of the ejection screw, even if the thread structure in the inner threaded hole is damaged in the disassembly process, only the arc-shaped abutting piece needs to be replaced, and the damage to the turbine shaft is avoided; in addition, the hard pad piece can be made of copper materials, the pressure applied to the disc surface of the turbine disc by the nail-in end of the ejection screw is replaced by the hard pad piece to bear, and when the ejection screw rotates, the hard pad piece is only abraded without damaging the turbine disc, so that the effective protection of the turbine disc structure is realized.
In addition to or as an alternative to the above-described method for disassembling a turbine rotor interference fit structure: the outer arc edge of the arc-shaped abutting piece extends forwards along the axis direction of the outer circle of the arc-shaped abutting piece, and a flange part protruding out of the surface of the arc-shaped abutting piece is formed. The structure of flange portion can carry out the adaptation with the epaxial journal ring knot portion of turbine to this journal ring knot portion belongs to the original structure of turbine shaft, can realize the utilization to the original structure of turbine dish at the dismantlement in-process of interference fit structure through flange portion, and need not to reequip in order to realize the dismantlement of interference fit structure, the effectual application degree of difficulty and the application cost that has reduced the technique that this scheme designed.
In addition to or as an alternative to the above-described method for disassembling a turbine rotor interference fit structure: a first connecting hole without threads is arranged on the flange disc part, a second connecting hole without threads is arranged on the journal disc part, and the second connecting hole is opposite to the first connecting hole; when the turbine disc is connected with the turbine shaft, the turbine disc is fixed by bolts penetrating into the second connecting hole and the first connecting hole; when the turbine disc and the turbine shaft are disassembled, the ejection screw penetrates through the second connecting hole, the first connecting hole and the internal threaded hole to tightly abut against the hard cushion piece. In turbine rotor's original structure, when turbine disc is connected with turbine shaft, except utilizing grafting axial region and turbine disc hole to realize interference fit's connection, still need to penetrate second connecting hole and first connecting hole through the bolt, be used for being connected the axle journal portion of turbine shaft and the flange dish portion of turbine disc, be promptly that second connecting hole and first connecting hole all belong to original turbine rotor's original structure, this scheme utilizes through the hole structure of original such as second connecting hole and first connecting hole, realize penetrating of ejecting screw and turbine rotor's dismantlement operation.
In addition to or as an alternative to the above-described method for disassembling a turbine rotor interference fit structure: the journal ring buckling part extends backwards along the axial direction of the journal disc part and covers the outer peripheral surface of the flange disc part.
A frock structure for decomposing turbine rotor interference fit structure: comprises a hard cushion part, an arc-shaped abutting part and an ejection screw;
the back cushion surface of the hard cushion piece is provided with an inclination angle matched with the disc surface of the turbine disc, so that when the hard cushion piece is abutted against the disc surface of the turbine disc, the front cushion surface of the hard cushion piece is vertical to the axis of the turbine disc.
The outer arc edge of the arc-shaped abutting piece extends forwards along the axis direction of the outer circle of the arc-shaped abutting piece and forms a flange part protruding out of the surface of the arc-shaped abutting piece; the flange part can be abutted against the outer edge of a shaft neck disc part of the turbine shaft;
the ejection screw can penetrate through the journal disc part, the flange disc part and the arc-shaped abutting part and abuts against the front cushion surface of the hard cushion part;
the sum of the thicknesses of the hard cushion piece and the arc-shaped abutting piece is smaller than the width of a flange plate back groove of the turbine disc, a flange plate part is arranged on the front side of the disc surface of the turbine disc, and the flange plate back groove is formed between the flange plate part and the disc surface of the turbine disc; the ejection screw is in threaded fit with the arc abutting piece and can push the arc abutting piece away from the hard cushion piece.
In addition to or as an alternative to the tooling structure for disassembling the turbine rotor interference fit structure described above: the hard pad piece and the arc abutting piece are arc-shaped, and the radian of the hard pad piece and the arc abutting piece is equivalent to that of the back groove of the flange plate.
In addition to or as an alternative to the tooling structure for disassembling the turbine rotor interference fit structure described above: the arc piece of propping has multiple different models, and the protruding height of the flange portion of every model is all inequality.
In addition to or as an alternative to the tooling structure for disassembling the turbine rotor interference fit structure described above: a plurality of first connecting holes without threads are distributed on the flange disc part, a plurality of second connecting holes without threads are distributed on the journal disc part, and the second connecting holes are opposite to the first connecting holes; when the turbine disc is connected with the turbine shaft, the turbine disc is fixed by bolts penetrating into the second connecting hole and the first connecting hole; when the turbine disc and the turbine shaft are disassembled, the ejection screw is parallel to the axial direction of the turbine shaft and penetrates into the second connecting hole and the first connecting hole.
In addition to or as an alternative to the tooling structure for disassembling the turbine rotor interference fit structure described above: a turbine disc inner hole is formed in the center of the turbine disc, and an insertion shaft part is arranged at the end part of the turbine shaft; when the turbine disc is connected with the turbine shaft, the inserting shaft part is inserted into the inner hole of the turbine disc and is in interference fit in the radial direction.
The invention has the beneficial effects that:
1. the tool structure of the scheme has the advantages of simplicity, good manufacturability, low cost, good replaceability and the like; the purpose of disassembling the turbine rotor can be effectively achieved through the tool structure, the situation that screw holes are formed in the turbine disc and the turbine shaft is avoided, and the disassembling work can be completed only by matching the original structures of the turbine disc and the turbine shaft with the tool structure.
2. The frock structure of this scheme not only can be applicable to high-pressure turbine rotor, can also be applicable to low-pressure turbine rotor, and the size of a dimension of stereoplasm pad spare and arc retaining member is decided according to the actual dimensions of specific turbine dish and turbine shaft, ejecting screw also select for use the standard part according to the size demand can, the manufacturability and the convertibility of frock are good like this. Because the thread structures are all arranged on the tool, the loss is also all arranged on the tool, and the effect of no damage caused by the disassembly of the turbine disc and the turbine shaft is achieved.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below.
FIG. 1 is a schematic view of a use state of a tool structure in the scheme;
FIG. 2 is a side axial view of the turbine rotor with the tooling structure of the present version installed;
FIG. 3 is a block diagram of a hard shim;
FIG. 4 is a schematic view of an arcuate abutment member;
FIG. 5 is a perspective view of the turbine rotor with the tooling structure installed.
In the figure: 1-a turbine disk; 11-flange portion; 12-inner hole of turbine disc; 2-a grate disc; 3-a turbine shaft; 31-collar ring snap; 32-a plug shaft portion; 33-journal disk portion; 4-ejecting screws; 5-arc-shaped abutting pieces; 51-flange portion; 52-outer arc edge; 53-inner arc edge; 54-an internally threaded hole; 6-hard padding pieces; 61-pad outer arc edge; 62-pad inner arc edge; 63-rear cushion surface; 64-front pad surface.
Detailed Description
The technical solutions in the embodiments will be described clearly and completely with reference to the accompanying drawings, and the described embodiments are only a part of the embodiments, but not all embodiments, and all other embodiments obtained by those skilled in the art without creative efforts will belong to the protection scope of the present solution based on the embodiments in the present solution.
The turbine rotor is an important component of the gas turbine, and the turbine rotor is used as a power component and is composed of parts such as turbine working blades, a turbine disc 1 and a turbine shaft 3. Because the turbine rotor rotates at a high rotating speed when in use and bears high stress, the turbine disc 1 and the turbine shaft 3 are closely connected in an interference fit manner, so that the stability of the turbine rotor in the rotating process is ensured, but the turbine disc 1 and the turbine shaft 3 are difficult to disassemble under the condition of no damage or low damage after the turbine disc 1 and the turbine shaft 3 are connected; if a jackscrew hole is designed on the turbine shaft 3 and a screw rod penetrates into the jackscrew hole, the turbine disc 1 in interference fit with the jackscrew hole is disassembled in a jacking mode, and irreversible damage to the turbine shaft 3 and the turbine disc 1 is possibly caused.
Example 1
As shown in fig. 1 to 5, the present embodiment designs a tooling structure for disassembling a turbine rotor, which includes an ejection screw 4, an arc-shaped abutting member 5, a hard pad member 6, and the like.
Wherein, the hard pad member 6 can adopt an integrated structure made of copper material, and the hard pad member 6 is in an arc segment shape; this stereoplasm backing member 6 has arc faces such as backing member outer arc edge 61, back face 63 and backing member inner arc edge 62, still has planes such as preceding face 64, and the back face 63 of stereoplasm backing member 6 has inclination and the radian of the quotation that matches in turbine disc 1 to when making stereoplasm backing member 6 support on the quotation of turbine disc 1, the preceding face 64 of stereoplasm backing member 6 can be perpendicular to the axis of turbine disc 1. Therefore, the pressure applied by the ejection screw 4 on the hard pad 6 can be prevented from being vertical to the front pad surface 64 of the hard pad 6, so as to prevent the contact position of the ejection screw and the hard pad 6 from generating component force radial to the ejection screw 4, thereby saving labor while achieving security and avoiding damage to the turbine disc 1 and the turbine shaft 3.
The outer arc edge 52 of the arc-shaped abutting piece 5 extends forwards along the axial direction of the external circle thereof and forms a flange part 51 protruding out of the surface of the arc-shaped abutting piece 5, the flange part 51 is arranged at the outer arc edge 52 of the arc-shaped abutting piece 5, and the inner arc edge 53 of the arc-shaped abutting piece 5 is in a circular arc shape; the flange part 51 can be abutted against the outer edge of the journal disc part 33 of the turbine shaft 3; the arc abutting pieces 5 may have different alternative models, and the flange portions 51 of the arc abutting pieces 5 of different models have different projection heights. Because the limit liftout distance of arc abutting piece 5 is equivalent to the protruding height of flange portion 51, consequently, can guarantee that arc abutting piece 5 can be with turbine disk 1 and turbine shaft 3 complete separation for the dismantlement state through the mode of changing different arc abutting piece 5, for example: if the insertion shaft part 32 of the turbine rotor and the inner hole 12 of the turbine disc have an interference fit range of more than 6mm, and the flange back groove can only be filled with one arc-shaped abutting part 5 with the flange part 51 having a height of only 6mm, the arc-shaped abutting part 5 can only push the turbine shaft 3 and the turbine disc 1 away by 6mm, and needs to be pushed away again, other tools are needed to disassemble the turbine shaft 3 and the turbine disc 1, or the arc-shaped abutting part 5 with the other flange part 51 having a height of more than 6mm is used to realize the disassembly, so that the turbine shaft 3 and the turbine disc 1 are completely disassembled.
The ejection screw is a part for pushing the arc-shaped abutting member 5 away from the hard pad member 6, and other parts (such as a wedge) can be used to control the movement of the arc-shaped abutting member 5 and the hard pad member 6 away from each other, and the ejection screw can pass through the journal disc portion 33, the flange disc portion 11 and the arc-shaped abutting member 5 and abut against the front pad surface 64 of the hard pad member 6 when in use. The arc supports the piece 5 and is the arc, and the radian that the piece 5 was supported to stereoplasm pad 6 and arc is equivalent with the radian in the ring flange back of the body groove.
The tool structure of the embodiment can be used for disassembling the high-pressure turbine rotor and the low-pressure turbine rotor, and the original structures of the high-pressure turbine rotor and the low-pressure turbine rotor comprise a turbine disc 1, a turbine shaft 3, a grate disc 2 and the like.
The end of the turbine shaft 3 has a journal disc 33, and the outer side of the journal disc 33 has an annular journal ring fastening portion 31, and the journal ring fastening portion 31 protrudes beyond the flange disc 11. A plurality of second connection holes without screw threads are arranged around the journal disk 33. A shaft journal disk part 33 insertion shaft part 32 is further arranged at the end part of the turbine shaft 3, and the insertion shaft part 32 is arranged at the end part of the turbine shaft 3; when the turbine disk 1 is connected to the turbine shaft 3, the insertion shaft portion 32 is inserted into the turbine disk inner hole 12 at the center of the turbine disk 1 and is interference-fitted in the radial direction.
A flange disc part 11 is arranged on the front side of the disc surface of the turbine disc 1, and a flange disc back groove is formed between the flange disc part 11 and the disc surface of the turbine disc 1; the sum of the thicknesses of the hard cushion piece 6 and the arc-shaped abutting piece 5 is smaller than the width of a flange plate back groove of the turbine disc 1. In the original structure of the turbine rotor, a plurality of first connecting holes without threads are distributed on the flange disc part 11, and the first connecting holes are opposite to the second connecting holes; when the turbine disk 1 is connected to the turbine shaft 3, in addition to the interference fit connection by the insertion shaft portion 32 and the turbine disk inner hole 12, bolts are required to penetrate into the second connection hole and the first connection hole to connect the journal disk portion 33 of the turbine shaft 3 with the flange disk portion 11 of the turbine disk 1. When the turbine disc 1 and the turbine shaft 3 are disassembled, the ejection screw 4 is parallel to the axial direction of the turbine shaft 3 and penetrates into the second connecting hole and the first connecting hole; the ejection screw is in threaded engagement with the arc-shaped abutting piece 5 and can push the arc-shaped abutting piece 5 away from the hard pad piece 6. This scheme utilizes through original pore structure such as second connecting hole and first connecting hole, realizes penetrating and turbine rotor's dismantlement operation of ejecting screw 4.
Example 2
On the basis of the structure of embodiment 1, the present embodiment designs a method for disassembling a turbine rotor interference fit structure, including the steps of:
step A: a plurality of hard cushion pieces 6 and a plurality of arc-shaped abutting pieces 5 are respectively arranged on the periphery of the back groove of the flange plate; a flange disc part 11 is arranged on the front side of the disc surface of the turbine disc 1, and a flange disc back groove is formed between the flange disc part 11 and the disc surface of the turbine disc 1; the notch of the flange plate back groove faces to the radial outer side of the flange plate back groove, and the hard pad pieces 6 correspond to the arc-shaped abutting pieces 5 one by one and are arranged in the flange plate back groove; when the turbine rotor is in a lying state, a hard cushion piece 6 and an arc-shaped abutting piece 5 can be respectively placed at the positions of the flange back groove in the upper direction, the lower direction, the left direction and the right direction.
And B: the hard cushion piece 6 is abutted against the disc surface of the turbine disc 1, and the arc-shaped abutting piece 5 is abutted against the neck ring buckling part 31 of the turbine shaft 3; the outer arc edge 52 of the arc abutting piece 5 extends forwards along the axial direction of the external circle thereof and forms a flange part 51 protruding out of the surface of the arc abutting piece 5, and the journal ring buckling part 31 extends backwards along the axial direction of the journal disc part 33 and covers the outer peripheral surface of the flange disc part 11. This neck ring buckle portion 31 belongs to the original structure of turbine shaft 3, can realize the utilization to the original structure of turbine dish 1 at the dismantlement in-process of interference fit structure through flange portion 51, has reduced frock structure and has used the degree of difficulty and application cost.
And C: and controlling each arc-shaped abutting piece 5 to be far away from the corresponding hard cushion piece 6, so that the arc-shaped abutting pieces 5 push the turbine shaft 3 to be far away from the turbine disc 1, and the disassembly of the turbine rotor is realized. When the wedge-shaped part or the ejection screw 4 is used for controlling the corresponding arc-shaped abutting piece 5 to be far away from the hard cushion piece 6, the arc-shaped abutting piece 5 can push the turbine shaft 3 to be far away from the turbine disc 1, and therefore the turbine disc 1 and the turbine shaft 3 of the turbine rotor are disassembled from the interference fit state to the disassembly state.
In the steps of the method, the pressure exerted by the arc-shaped abutting piece 5 on the turbine shaft 3 and the pressure exerted by the hard cushion piece 6 on the turbine disc 1 are parallel to the axial direction of the turbine rotating shaft, and meanwhile, the stress area is large, so that the turbine disc 1 and the turbine shaft 3 cannot be damaged due to overlarge pressure, the turbine disc 1 and the turbine shaft 3 can be protected to a large extent, and non-damage or low-damage disassembly is realized. In addition, because the ejecting screw 4 is matched with the threaded connection structure of the internal threaded hole 54, the turbine disc 1 and the turbine shaft 3 can be disassembled from the interference fit state only by using a small force; the position bearing larger pressure is arranged on the internal thread hole 54 of the arc-shaped abutting piece 5, even if the thread structure in the internal thread hole 54 is damaged in the dismounting process, only the arc-shaped abutting piece 5 needs to be replaced, and the damage to the turbine shaft 3 cannot be caused; the pressure applied to the disc surface of the turbine disc 1 by the driving end of the ejection screw 4 is also born by the hard pad piece 6, and when the ejection screw 4 rotates, only the hard pad piece 6 is abraded without damaging the turbine disc 1, so that the structure of the turbine disc 1 is effectively protected.
The above examples are merely for clearly illustrating the examples and are not intended to limit the embodiments; and are neither required nor exhaustive of all embodiments. And obvious variations or modifications of this technology may be resorted to while remaining within the scope of the technology.
Claims (6)
1. A method for disassembling a turbine rotor interference fit structure, characterized by: the method comprises the following steps:
step A: a plurality of hard cushion pieces (6) and a plurality of arc-shaped abutting pieces (5) are respectively arranged on the periphery of the back groove of the flange plate; a flange disc part (11) is arranged on the front side of the disc surface of the turbine disc (1), and a flange disc back groove is formed between the flange disc part (11) and the disc surface of the turbine disc (1); the notch of the flange plate back groove faces to the radial outer side of the flange plate back groove, and the hard pad pieces (6) and the arc-shaped abutting pieces (5) are in one-to-one correspondence and are arranged in the flange plate back groove;
and B, step B: the method comprises the following steps that a hard cushion piece (6) is abutted against the disc surface of a turbine disc (1), an arc-shaped abutting piece (5) is abutted against a shaft neck ring buckling part (31) of a turbine shaft (3), and the shaft neck ring buckling part (31) is arranged on the outer edge of a shaft neck disc part (33) of the turbine shaft (3) and exceeds a flange disc part (11);
and C: each arc-shaped abutting piece (5) is controlled to be far away from the corresponding hard pad piece (6), so that the arc-shaped abutting pieces (5) push the turbine shaft (3) to be far away from the turbine disc (1), and the decomposition of the turbine rotor is realized;
an internal thread hole (54) is formed in the arc-shaped abutting piece (5), and an ejection screw (4) in threaded fit with the internal thread hole (54) is arranged in the internal thread hole; when the ejection screw (4) is rotated, the driving end of the ejection screw (4) can tightly abut against the hard pad (6) and push the arc-shaped abutting piece (5) away from the hard pad (6);
the outer arc edge (52) of the arc-shaped abutting piece (5) extends forwards along the axial direction of the external circle of the arc-shaped abutting piece and is provided with a flange part (51) protruding out of the surface of the arc-shaped abutting piece (5);
a first connecting hole without threads is arranged on the flange disc part (11), a second connecting hole without threads is arranged on the journal disc part (33), and the second connecting hole is opposite to the first connecting hole; when the turbine disc (1) is connected with the turbine shaft (3), the turbine disc is fixed by bolts penetrating into the second connecting hole and the first connecting hole; when the turbine disc (1) and the turbine shaft (3) are disassembled, the ejection screw (4) penetrates through the second connecting hole, the first connecting hole and the internal threaded hole (54) to tightly abut against the hard cushion piece (6).
2. The method for disassembling a turbine rotor interference fit structure of claim 1, wherein: the journal ring buckling part (31) extends backwards along the axial direction of the journal disc part (33) and covers the outer peripheral surface of the flange disc part (11).
3. The utility model provides a frock structure for decomposing turbine rotor interference fit structure which characterized in that: comprises a hard pad (6), an arc-shaped abutting piece (5) and an ejection screw (4);
the rear padding surface (63) of the hard padding piece (6) has an inclination angle matched with the disk surface of the turbine disk (1), so that when the hard padding piece (6) is abutted against the disk surface of the turbine disk (1), the front padding surface (64) of the hard padding piece (6) is vertical to the axis of the turbine disk (1);
the outer arc edge (52) of the arc-shaped abutting piece (5) extends forwards along the axial direction of the external circle of the arc-shaped abutting piece and is provided with a flange part (51) protruding out of the surface of the arc-shaped abutting piece (5); the flange part (51) can be abutted against the outer edge of a shaft neck disc part (33) of the turbine shaft (3);
the ejection screw can penetrate through the journal disc part (33), the flange disc part (11) and the arc-shaped abutting part (5) and abuts against the front cushion surface (64) of the hard cushion part (6);
the sum of the thicknesses of the hard pad piece (6) and the arc-shaped abutting piece (5) is smaller than the width of a flange plate back groove of the turbine disc (1), a flange disc part (11) is arranged on the front side of the disc surface of the turbine disc (1), and the flange plate back groove is formed between the flange disc part (11) and the disc surface of the turbine disc (1); the ejection screw is in threaded fit with the arc-shaped abutting piece (5) and can push the arc-shaped abutting piece (5) away from the hard pad piece (6);
a plurality of first connecting holes without threads are distributed on the flange disc part (11), a plurality of second connecting holes without threads are distributed on the journal disc part (33), and the second connecting holes are opposite to the first connecting holes; when the turbine disc (1) is connected with the turbine shaft (3), the turbine disc is fixed by bolts penetrating into the second connecting hole and the first connecting hole; when the turbine disc (1) and the turbine shaft (3) are disassembled, the ejection screw (4) is parallel to the axial direction of the turbine shaft (3) and penetrates into the second connecting hole and the first connecting hole.
4. The tool structure for disassembling the interference fit structure of the turbine rotor of claim 3, wherein: hard pad spare (6) and arc are supported the piece (5) and are the arc, and the radian of both is equivalent with the radian in ring flange back of the body groove.
5. The tool structure for disassembling the interference fit structure of the turbine rotor of claim 3, wherein: the arc-shaped abutting piece (5) has different models, and the protruding height of the flange part (51) of each model is different.
6. The tool structure for disassembling the interference fit structure of the turbine rotor according to claim 3, characterized in that: a turbine disc inner hole (12) is formed in the center of the turbine disc (1), and an insertion shaft part (32) is arranged at the end part of the turbine shaft (3); when the turbine disc (1) is connected with the turbine shaft (3), the insertion shaft part (32) is inserted into the inner hole (12) of the turbine disc and is in interference fit in the radial direction.
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| CN202211470839.2A CN115519513B (en) | 2022-11-22 | 2022-11-22 | Method and tool structure for decomposing interference fit structure of turbine rotor |
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| CN202211470839.2A CN115519513B (en) | 2022-11-22 | 2022-11-22 | Method and tool structure for decomposing interference fit structure of turbine rotor |
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| CN115519513B true CN115519513B (en) | 2023-03-21 |
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| CA2103531A1 (en) * | 1993-08-06 | 1995-02-07 | Clement O. Hart | Bearing and race remover |
| CN101602200A (en) * | 2008-06-11 | 2009-12-16 | 上海宝钢设备检修有限公司 | The method for dismounting of sealing opening of rotor vane of low-pressure coal press machine of power plant |
| EP2275218A1 (en) * | 2009-07-14 | 2011-01-19 | Alstom Technology Ltd | Method for processing the rotor of a turbine and device for implementing the method |
| CN103580392A (en) * | 2012-07-23 | 2014-02-12 | 珠海格力电器股份有限公司 | Stop device of motor rotor and method for mounting and disassembling motor rotor |
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| JPH10205602A (en) * | 1997-01-22 | 1998-08-04 | Amada Co Ltd | Ball screw feed mechanism |
| CN205438400U (en) * | 2015-12-31 | 2016-08-10 | 株洲中航动科南方燃气轮机成套制造安装有限公司 | A frock clamp for turbine disc decomposes |
| US20170356338A1 (en) * | 2016-06-08 | 2017-12-14 | General Electric Company | Installation tool and system for assembling a gas turbine combustor |
| CN113814697B (en) * | 2020-06-18 | 2022-10-28 | 中国航发商用航空发动机有限责任公司 | Method for decomposing low-pressure turbine shaft |
| CN214394030U (en) * | 2021-02-02 | 2021-10-15 | 中国航发商用航空发动机有限责任公司 | Disassembling tool for rotor sealing ring of aircraft engine |
| CN114833763A (en) * | 2021-02-02 | 2022-08-02 | 中国航发商用航空发动机有限责任公司 | Sealing ring dismounting device and sealing ring dismounting method |
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Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CA2103531A1 (en) * | 1993-08-06 | 1995-02-07 | Clement O. Hart | Bearing and race remover |
| CN101602200A (en) * | 2008-06-11 | 2009-12-16 | 上海宝钢设备检修有限公司 | The method for dismounting of sealing opening of rotor vane of low-pressure coal press machine of power plant |
| EP2275218A1 (en) * | 2009-07-14 | 2011-01-19 | Alstom Technology Ltd | Method for processing the rotor of a turbine and device for implementing the method |
| CN103580392A (en) * | 2012-07-23 | 2014-02-12 | 珠海格力电器股份有限公司 | Stop device of motor rotor and method for mounting and disassembling motor rotor |
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| CN115519513A (en) | 2022-12-27 |
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