CN211202406U - Compressor wheel disc applied to modeled pull rod rotor of heavy gas turbine - Google Patents
Compressor wheel disc applied to modeled pull rod rotor of heavy gas turbine Download PDFInfo
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- CN211202406U CN211202406U CN201922147151.0U CN201922147151U CN211202406U CN 211202406 U CN211202406 U CN 211202406U CN 201922147151 U CN201922147151 U CN 201922147151U CN 211202406 U CN211202406 U CN 211202406U
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Abstract
The utility model relates to a be applied to compressor rim plate of heavy gas turbine modularization rotor belongs to heavy gas turbine technical field. The utility model discloses a rim plate main part, rim plate main part are circular rim plate, and the left and right sides of rim plate main part has processed first inner groovy and second inner groovy respectively, and processing has a plurality of draw rod holes in the rim plate main part, and a plurality of draw rod holes use the centre of a circle of rim plate main part to be the annular and evenly arrange as the center, the central point of rim plate main part puts and is equipped with the location boss, and the boss is arranged in first inner groovy in the location, the central point of rim plate main part puts and still is equipped with and accepts the seat, and processing has the rotor shaft mounting hole on the location boss, and the rotor shaft mounting hole link up whole rim plate main part, it. The utility model provides a be applied to compressor rim plate structural constraint of heavy gas turbine modularization rotor and easily produce crack and fracture, rim plate unstable scheduling problem of assembly between two liang, simple structure, the processing cost is low, convenient assembling.
Description
Technical Field
The utility model relates to a be applied to compressor rim plate of heavy gas turbine modularization pull rod rotor belongs to heavy gas turbine technical field.
Background
The heavy gas turbine is clean and clean power generation equipment, wherein a rotor is the most main core part, the heavy gas turbine rotor has various structural types and is mainly a pull rod type combined rotor, a rotor assembly comprises a plurality of rotor discs and a plurality of rotor blades, the pull rod combined rotor provides pretightening force through a pull rod and is transmitted by the discs or friction surfaces, so that the structure and the appearance of the discs are critical, at present, China is in a starting stage for designing and manufacturing the heavy gas turbine rotor assembly, the structures of the discs are single, mature modeling models and theories do not exist in China, and a few developed countries are in monopoly status for the technology.
The existing compressor wheel disc of the heavy-duty gas turbine has the following defects in the using process:
1. The conventional gas compressor wheel disc is installed in a pull rod tensioning mode, due to the structural limitation of the wheel disc, when the pull rod is too large in tension, the wheel disc body generates cracks, fractures and other phenomena at the position of the pull rod hole, so that the service life of the wheel disc is seriously influenced, and when the pull rod is too small in tension, the connection of two adjacent wheel discs is unstable, so that the normal use of the whole rotor is influenced;
2. The center of the wheel disc is provided with a rotor shaft mounting hole in a conventional mode, and when the wheel disc is used for a long time, the matching mounting positions of the rotor shaft and the wheel disc are stressed intensively, so that deformation and fracture of different degrees occur.
Based on the above statement, it is urgently needed to provide a compressor wheel disc of a modular rotor of a heavy-duty gas turbine, which has a simple structure, low processing cost, convenient assembly and high safety and reliability under working conditions of high speed, heavy load and the like.
SUMMERY OF THE UTILITY MODEL
The utility model provides a be applied to compressor rim plate structural constraint of heavy gas turbine modularization pull rod rotor and easily produce crack and fracture, the unstable scheduling problem of assembly between two liang of rim plate, and then provide a compressor rim plate of being applied to heavy gas turbine modularization pull rod rotor, simple structure, the processing cost is low, convenient assembling, the outline of carousel more makes things convenient for and rotor blade cooperation, through position boss and the clearance of accepting the seat, excessive or the direct complete sets installation of interference fit uses.
The technical scheme of the utility model:
The utility model provides a be applied to compressor rim plate of heavy gas turbine modularization pull rod rotor, includes the rim plate main part, and the rim plate main part is circular rim plate, and the left and right sides of rim plate main part has processed first inner groovy and second inner groovy respectively, and processing has a plurality of draw rod holes in the rim plate main part, and a plurality of draw rod holes use the centre of a circle of rim plate main part to be the annular and evenly arrange as the center, the central point of rim plate main part puts and is equipped with the location boss, and the location boss is arranged in first inner groovy, the central point of rim plate main part puts and still is equipped with accepts the seat, and processing has the rotor shaft mounting hole on the location boss, and the rotor shaft mounting hole link up whole rim.
Preferably: the cross section of the positioning boss is circular or square, the circular boss is convenient to assemble and flexible, and the square boss enables the structure to be more stable.
Preferably: the positioning boss protrudes out of the disc surface of the wheel disc main body, and the protruding positioning boss facilitates installation of two adjacent wheel discs.
Preferably: the bearing seat is provided with a bearing hole, and the inner diameter of the bearing hole is matched with the outer diameter of the positioning boss.
Preferably: the quantity of rim plate main part is a plurality of, and when two adjacent rim plate main parts were installed, the location boss card of rim plate main part was gone into in the adapting hole.
Preferably: the wheel disc main body is a conical wheel disc, the outer wall of the wheel disc main body and the central shaft form a wheel disc camber angle A, and the angle range of the wheel disc camber angle A is 0-20 degrees.
Preferably: the positioning boss, the bearing seat and the wheel disc main body are integrally cast and formed.
The utility model discloses following beneficial effect has: the utility model relates to a be applied to compressor rim plate of heavy gas turbine modularization pull rod rotor simple structure, the processing cost is low, convenient assembling, through position boss and the clearance of accepting the seat, excessive or interference fit can direct complete sets installation use to based on the mass distribution condition of actual combustion engine rim plate and additional mass blade etc. through the cone angle that changes rim plate edge structure, structural feature and its distinctive dynamic characteristic of heavy gas turbine compressor rim plate are reflected in simulation that can be better.
The utility model discloses be provided with location boss and accepting the seat respectively in the center department of rim plate main part, processing has the mounting hole of installation rotor shaft on the location boss, wraps up the rotor shaft of whole heavy gas turbine pull rod rotor through the location boss for the axial plane of rotor shaft and the inner wall of location boss laminate completely, increased the area of contact of rim plate and rotor shaft, improved rim plate body and rotor shaft life;
When a plurality of wheel discs are installed on the rotor shaft of the pull rod rotor of the heavy gas turbine, the installation positions of a group of wheel disc bodies and the rotor shaft completely cover the whole rotor shaft, and the problem that the rotor shaft cracks due to stress concentration caused by the dispersed bearing force conditions of different shaft sections of the rotor shaft is effectively solved;
When the wheel disc of the utility model is installed, the positioning lug boss of the adjacent wheel disc main body is assembled with the bearing seat of the adjacent wheel disc main body, under the action of the positioning lug boss and the bearing seat, a pull rod is inserted into the pull rod hole on the wheel disc group, the pull rod is screwed, the positioning lug boss and the bearing seat bear a supporting force at the central position of the wheel disc, and the supporting force is matched with the pull rod force to form two parallel forces, so that the adjacent wheel disc is more stably assembled;
The location boss can also play a reinforcing role, puts a location boss of design at the central point of rim plate main part, and when using, the location boss bears the atress of part rim plate quotation, and the quotation of rim plate can not produce deformation, has improved the quality of heavy gas turbine modularization pull rod rotor.
Drawings
FIG. 1 is a cross-sectional view of a compressor disk for use in a modular tie rod rotor for a heavy duty gas turbine;
FIG. 2 is a front view of a compressor disk for use in a modular tie rod rotor for a heavy duty gas turbine;
FIG. 3 is a cross-sectional view of the fourth structure 1 of the embodiment;
FIG. 4 is a front view of the fourth structure 1 of the embodiment;
FIG. 5 is a cross-sectional view of an embodiment four structure 2;
FIG. 6 is a front view of the fourth structure 2 of the embodiment;
FIG. 7 is a cross-sectional view of a fifth embodiment;
FIG. 8 is a front view of a fifth embodiment;
FIG. 9 is a schematic view of an assembled structure;
In the drawing, 1-a pull rod hole, 2-a rotor shaft mounting hole, 3-a bearing hole, 4-a wheel disc main body, 5-a positioning boss, 6-a bearing seat, 7-a first inner groove and 8-a second inner groove.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention more apparent, the present invention will be described below with reference to specific embodiments shown in the accompanying drawings. It should be understood that the description is intended to be illustrative only and is not intended to limit the scope of the present invention. Moreover, in the following description, descriptions of well-known structures and techniques are omitted so as to not unnecessarily obscure the concepts of the present invention.
The first embodiment is as follows: the embodiment is described with reference to fig. 1 to 5, and the compressor wheel disc applied to the modeled pull rod rotor of the heavy gas turbine of the embodiment includes a wheel disc main body 4, the wheel disc main body 4 is a circular wheel disc, a first inner groove 7 and a second inner groove 8 are respectively processed on the left side and the right side of the wheel disc main body 4, a plurality of pull rod holes 1 are processed on the wheel disc main body 4, and the pull rod holes 1 are uniformly arranged in an annular shape by taking the circle center of the wheel disc main body 4 as the center, and the compressor wheel disc is characterized in that: the center position of rim plate main part 4 is equipped with location boss 5, and location boss 5 arranges in first inner groovy 7, the center position of rim plate main part 4 still is equipped with accepts seat 6, and processing has rotor shaft mounting hole 2 on the boss 5 of location, and rotor shaft mounting hole 2 link up whole rim plate main part 4, it has accepts hole 3 to process on the seat 6.
The second embodiment is as follows: the embodiment is described with reference to fig. 1 to 5, and the cross section of the positioning boss 5 of the compressor wheel disk applied to the modular pull rod rotor of the heavy-duty gas turbine is circular or square, so that the circular shape is convenient to assemble, the flexibility is high, and the square shape enables the structure to be more stable.
The third concrete implementation mode: the embodiment is described with reference to fig. 1 to 5, and the positioning boss 5 of the compressor wheel disc applied to the modular pull rod rotor of the heavy-duty gas turbine of the embodiment protrudes out of the disc surface of the wheel disc main body 4, and the protruding positioning boss 5 facilitates the installation of two adjacent wheel discs.
The fourth concrete implementation mode: the embodiment is described with reference to fig. 1 to 5, and the compressor wheel disc applied to the modular pull rod rotor of the heavy-duty gas turbine of the embodiment is provided with a bearing hole 3 machined on the bearing seat 6, wherein the inner diameter of the bearing hole 3 is matched with the outer diameter of the positioning boss 5.
The fifth concrete implementation mode: the embodiment is described by combining fig. 1-5, the number of the wheel disc main bodies 4 is multiple, when two adjacent wheel disc main bodies 4 are installed, the positioning bosses 5 of the wheel disc main bodies 4 are clamped into the bearing holes 3, and the assembling mode has the advantages that the two adjacent wheel disc main bodies 4 are firmly attached, the play and the looseness cannot occur in the using process, the friction between the two adjacent wheel disc main bodies is avoided, and the service life of the whole body is prolonged. Meanwhile, the two are installed in a clamping mode, the matching is tight, and the operation stability is improved
The sixth specific implementation mode: the embodiment is described by combining fig. 1-5, and the compressor wheel disc applied to the modeled pull rod rotor of the heavy-duty gas turbine of the embodiment is based on the structural distribution condition of the actual gas turbine rotor wheel disc and rotor blades, wherein the wheel disc main body 4 is a conical wheel disc, the outer wall of the wheel disc main body 4 and a central shaft form a wheel disc camber angle a, the angle range of the wheel disc camber angle a is 0-20 degrees, and the gas turbine rotor wheel disc and the rotor blades of different models can be conveniently matched under different conditions.
The seventh embodiment: the embodiment is described with reference to fig. 1 to 5, and the positioning boss 5, the bearing seat 6 and the wheel disc main body 4 of the compressor wheel disc applied to the modeled pull rod rotor of the heavy-duty gas turbine are integrally cast and formed, so that the processing is convenient, the integral stress effect is good, and the manufacturing cost is saved.
the eighth embodiment is described with reference to fig. 1 to 5, and the outer wall of the wheel disc main body 4 of the compressor applied to the modular pull rod rotor of the heavy-duty gas turbine is fixedly connected with the inner wall of a circular tube with the diameter of R5, the inner diameter of L and the length of H4, wherein R5 is 240-300 mm, L is 230-250 mm, and H4 is 34-50 mm, the circular tube increases the radius of the overall outer contour of the wheel disc, so that the matching of different models of rotor blades under different conditions is facilitated.
It should be noted that, in the above embodiments, as long as the technical solutions can be aligned and combined without contradiction, those skilled in the art can exhaust all possibilities according to the mathematical knowledge of the alignment and combination, and therefore the present invention does not describe the technical solutions after alignment and combination one by one, but it should be understood that the technical solutions after alignment and combination have been disclosed by the present invention.
The utility model discloses the connection that mentions divide into fixed connection and can dismantle the connection, fixed connection is for the conventional fixed connection mode such as undetachable connection including but not limited to hem connection, rivet connection, adhesive connection and welded connection, can dismantle the connection including but not limited to conventional dismantlement modes such as threaded connection, buckle connection, pin joint and hinged joint, when not clearly prescribing a limit to concrete connection mode, acquiesces to always can find at least one kind of connected mode in current connected mode and can realize this function, and the technical staff in the art can select by oneself as required. For example: the fixed connection selects welding connection, and the detachable connection selects hinge connection.
This embodiment is only illustrative of the patent and does not limit the scope of protection thereof, and those skilled in the art can make modifications to its part without departing from the spirit of the patent.
Claims (7)
1. The utility model provides a be applied to compressor rim plate of heavy gas turbine modularization pull rod rotor which characterized in that: including rim plate main part (4), rim plate main part (4) are circular rim plate, and the left and right sides of rim plate main part (4) is processed respectively has first inner groovy (7) and second inner groovy (8), and processing has a plurality of draw rod hole (1) on rim plate main part (4), and a plurality of draw rod hole (1) are the annular and evenly arrange as the center with the centre of a circle of rim plate main part (4), the central point of rim plate main part (4) puts and is equipped with location boss (5), and location boss (5) are arranged in first inner groovy (7), the central point of rim plate main part (4) puts and still is equipped with and accepts seat (6), and processing has rotor shaft mounting hole (2) on location boss (5), and rotor shaft mounting hole (2) link up whole rim plate main part (4), it has accepted hole (3) to process on accepting seat (6).
2. The compressor wheel disk applied to the modeled tie rod rotor of the heavy duty gas turbine as set forth in claim 1, wherein: the cross section of the positioning boss (5) is circular or square.
3. The compressor wheel disk applied to the modeled tie rod rotor of the heavy duty gas turbine as set forth in claim 1, wherein: the positioning boss (5) protrudes out of the disc surface of the wheel disc main body (4).
4. The compressor wheel disk applied to the modeled tie rod rotor of the heavy duty gas turbine as set forth in claim 1, wherein: the bearing seat (6) is provided with a bearing hole (3), and the inner diameter of the bearing hole (3) is matched with the outer diameter of the positioning boss (5).
5. The compressor disk for a modular tie rod rotor of a heavy duty gas turbine according to any one of claims 1 to 4, wherein: the number of the wheel disc main bodies (4) is multiple, and when two adjacent wheel disc main bodies (4) are installed, the positioning bosses (5) of the wheel disc main bodies (4) are clamped into the bearing holes (3).
6. The compressor wheel disk applied to the modeled tie rod rotor of the heavy duty gas turbine as set forth in claim 1, wherein: the wheel disc main body (4) is a conical wheel disc, the outer wall of the wheel disc main body (4) and the central shaft form a wheel disc camber angle A, and the angle range of the wheel disc camber angle A is 0-20 degrees.
7. The compressor wheel disk applied to the modeled tie rod rotor of the heavy duty gas turbine as set forth in claim 1, wherein: the positioning boss (5), the bearing seat (6) and the wheel disc main body (4) are integrally cast and formed.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922147151.0U CN211202406U (en) | 2019-12-04 | 2019-12-04 | Compressor wheel disc applied to modeled pull rod rotor of heavy gas turbine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201922147151.0U CN211202406U (en) | 2019-12-04 | 2019-12-04 | Compressor wheel disc applied to modeled pull rod rotor of heavy gas turbine |
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| Publication Number | Publication Date |
|---|---|
| CN211202406U true CN211202406U (en) | 2020-08-07 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201922147151.0U Active CN211202406U (en) | 2019-12-04 | 2019-12-04 | Compressor wheel disc applied to modeled pull rod rotor of heavy gas turbine |
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Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112498944A (en) * | 2020-11-30 | 2021-03-16 | 南京汽轮电机(集团)有限责任公司 | Gas turbine rotor disk stacking device |
| CN113027534A (en) * | 2021-04-19 | 2021-06-25 | 清华大学 | Joint surface connecting structure of rotor wheel disc of disc type gas turbine |
-
2019
- 2019-12-04 CN CN201922147151.0U patent/CN211202406U/en active Active
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112498944A (en) * | 2020-11-30 | 2021-03-16 | 南京汽轮电机(集团)有限责任公司 | Gas turbine rotor disk stacking device |
| CN113027534A (en) * | 2021-04-19 | 2021-06-25 | 清华大学 | Joint surface connecting structure of rotor wheel disc of disc type gas turbine |
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