CN209444375U - A kind of heavy duty gas turbine modelling rotor - Google Patents
A kind of heavy duty gas turbine modelling rotor Download PDFInfo
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- CN209444375U CN209444375U CN201920211610.4U CN201920211610U CN209444375U CN 209444375 U CN209444375 U CN 209444375U CN 201920211610 U CN201920211610 U CN 201920211610U CN 209444375 U CN209444375 U CN 209444375U
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Abstract
A kind of heavy duty gas turbine modelling rotor, belongs to heavy duty gas turbine technical field.The utility model solves the problems, such as that existing heavy duty gas turbine rotor is not able to achieve modelling.Compressor front end axis, compressor first order impeller, compressor second level impeller, compressor third level impeller, compressor fourth stage impeller, compressor level V impeller, compressor the 6th grade of impeller, compressor rear axle of the utility model are successively interference fitted connection；And it is linked together by pull rod and bolt synergy.The axillare of turbine front end axis, turbine first order impeller, the first telophragma of turbine, turbine second level impeller, the second telophragma of turbine, turbine third level impeller and turbine rear axle axillare be sequentially connected from front to back；Compressor rear axle and turbine front end axis are coaxially connected；The utility model structure is simple, easy to assembly, the high safety and reliability under the operating conditions such as high speed, heavy duty.
Description
Technical field
The utility model relates to a kind of gas turbine rotors, and in particular to a kind of heavy duty gas turbine modelling rotor belongs to
Heavy duty gas turbine technical field.
Background technique
Heavy duty gas turbine is to imitate noble and unsullied generating equipment clearly, and wherein rotor is most important core component, due to work
Under high temperature, high pressure, high revolving speed and heavily loaded environment, heavy duty gas turbine rotor axial, radial symmetry gradient are big, compressor and thoroughly
It is different to equal high temperature resistants and strength characteristics at different levels, and rod fastening rotor can be very good to meet the demand.Heavy duty gas turbine rotor
Design difficulty it is very big, China is in the starting stage for the design and manufacture of heavy duty gas turbine rotor at present, it is domestic not at
Ripe modelling and theory, a small number of developed countries are in monopoly position for this technology.
Utility model content
The brief overview about the utility model is given below, in order to provide certain sides about the utility model
The basic comprehension in face.It should be appreciated that this general introduction is not the exhaustive general introduction about the utility model.It is not intended to really
The key or pith of the utility model are determined, nor intended limitation the scope of the utility model.Its purpose is only with letter
The form of change provides certain concepts, taking this as a prelude to a more detailed description discussed later.
In consideration of it, the utility model is to solve the problems, such as that existing heavy duty gas turbine rotor is not able to achieve modelling, in turn
A kind of heavy duty gas turbine modelling rotor is provided.
Scheme: a kind of heavy duty gas turbine modelling rotor, including compressor section and turbine section, wherein compressor section includes pressure
Mechanism of qi front end axis, compressor first order impeller, compressor second level impeller, compressor third level impeller, compressor fourth stage leaf
Wheel, compressor level V impeller, the 6th grade of impeller of compressor, compressor rear axle and pull rod, turbine section include turbine front end axis,
Turbine first order impeller, the first telophragma of turbine, turbine second level impeller, the second telophragma of turbine, turbine third level impeller and
Turbine rear axle；
Wherein, compressor front end axis, compressor rear axle, turbine front end axis and turbine rear axle include axis and with
The axillare that axis is fixedly connected, the axillare trailing flank of compressor front end axis are provided centrally with the first protrusion, compressor rear axle
Axillare leading flank be provided centrally with the first groove, the compressor first order impeller, compressor second level impeller, compressor
The leading flank center setting of three-level impeller, the 6th grade of compressor fourth stage impeller, compressor level V impeller and compressor impeller
There are the second groove, compressor first order impeller, compressor second level impeller, compressor third level impeller, compressor fourth stage leaf
Wheel, compressor level V impeller, the 6th grade of impeller of compressor trailing flank be provided centrally with second protrusion；
First protrusion is connect with the second groove on compressor first order impeller by interference fit type, compressor
First order impeller, compressor second level impeller, compressor third level impeller, compressor fourth stage impeller, compressor level V leaf
Wheel and the 6th grade of impeller of compressor are successively arranged from front to back, are realized between adjacent fan-wheel by the second protrusion and the second groove
The fit system that is full of connects, and the second protrusion on the 6th grade of impeller of compressor is interference fitted with the first groove；
Axillare, compressor first order impeller, the compressor second level impeller, the compressor third level of compressor front end axis
Impeller, compressor fourth stage impeller, compressor level V impeller, compressor the 6th grade of impeller, compressor rear axle axillare
Circumference edge portion annular is evenly equipped with multiple round tie rod holes, and pull rod gap is threaded through in round tie rod hole, and pull rod and bolt join
Cooperation with by compressor front end axis, compressor first order impeller, compressor second level impeller, compressor third level impeller, calm the anger
Machine fourth stage impeller, compressor level V impeller, compressor the 6th grade of impeller, compressor rear axle link together；
The axillare of turbine front end axis, turbine first order impeller, the first telophragma of turbine, turbine second level impeller, thoroughly
The axillare of flat second telophragma, turbine third level impeller and turbine rear axle is connected in turn from front to back；
Compressor rear axle and turbine front end axis are coaxially connected together.
Further: the outer circle of the compressor first order impeller, compressor second level impeller, compressor third level impeller
Multiple trapezoidal grooves are circumferentially uniformly arranged along the respective center of circle on week, trapezoidal groove is used to installation quality block.It is dynamic flat to realize
Weighing apparatus or mass unbalance experimental test.
Further: second protrusion is cylindrical protrusions；Second groove is cylinder shape groove.So set, being convenient for
Processing realizes interference fit convenient for assembly.
The utility model effect achieved are as follows:
The utility model structure is simple, and processing cost is low, easy to assembly, the security reliability under the operating conditions such as high speed, heavy duty
Height can preferably simulate the structure feature for reflecting heavy duty gas turbine and its distinctive kinetic characteristics.Realize Heavy duty gas
The modelling of turbine wheel.
Detailed description of the invention
Fig. 1 is a kind of structure chart of heavy duty gas turbine modelling rotor of the utility model；
Fig. 2 is compressor first order blade wheel structure figure；
Fig. 3 is drawbar structure diagram.
In figure: 1, compressor front end axis；2, compressor first order impeller；3, compressor second level impeller；4, compressor
Three-level impeller；5, compressor fourth stage impeller nut；6, compressor level V impeller；7, the 6th grade of impeller of compressor；8, it calms the anger
Machine rear axle；9, turbine front end axis；10, turbine first order impeller；11, the first telophragma of turbine；12, turbine second level impeller；
13, the second telophragma of turbine；14, turbine third level impeller；15, turbine rear axle；16, pull rod；17, fastening bolt；21, trapezoidal
Groove；22, round tie rod hole；23, the second protrusion；24, the second groove 23；31, the end of thread；32, cylindrical end；51, second
Protrusion；52, the second groove.
Specific embodiment
For clarity and conciseness, all features of actual implementation mode are not described in the description.However, should
Understand, much decisions specific to embodiment must be made, during developing any this practical embodiments so as to reality
The objectives of existing developer, for example, meeting restrictive condition those of related to system and business, and these restrictive conditions
It may be changed with the difference of embodiment.In addition, it will also be appreciated that although development is likely to be very multiple
It is miscellaneous and time-consuming, but for the those skilled in the art for having benefited from the utility model disclosure, this development is only
It is routine task.
Here, and also it should be noted is that, in order to avoid having obscured the utility model because of unnecessary details, in Shen
It please illustrate only the apparatus structure and/or processing step closely related with scheme according to the present utility model in file, and save
The other details little with the utility model relationship are omited.
Embodiment: referring to Fig. 1 to Fig. 3, a kind of heavy duty gas turbine modelling rotor (referring to Fig. 1) of present embodiment, packet
Compressor section and turbine section are included, wherein compressor section includes compressor front end axis 1, compressor first order impeller 2, compressor second
Grade impeller 3, compressor third level impeller 4, compressor fourth stage impeller 5, the 6th grade of compressor level V impeller 6, compressor leaf
Wheel 7, compressor rear axle 8 and pull rod 16, turbine section include turbine front end axis 9, turbine first order impeller 10, among turbine first
Disk 11, turbine second level impeller 12, the second telophragma of turbine 13, turbine third level impeller 14 and turbine rear axle 15；
Wherein, compressor front end axis 1, compressor rear axle 8, turbine front end axis 9 and turbine rear axle 15 include
Axis and the axillare being fixedly connected with axis, the axillare trailing flank of compressor front end axis 1 is provided centrally with the first protrusion 51, described
First protrusion 51 is cylindrical protrusions, and diameter is 80~100mm, and the axillare leading flank of compressor rear axle 8 is provided centrally with the
One groove 52, the first groove are cylinder shape groove, and outer diameter is 120~150mm, and internal diameter is 80~100mm, the compressor first
Grade impeller 2, compressor second level impeller 3, compressor third level impeller 4, compressor fourth stage impeller 5, compressor level V leaf
The leading flank of wheel 6 and the 6th grade of impeller 7 of compressor is provided centrally with the second groove 24, compressor first order impeller 2, compressor the
Sencond stage impeller 3, compressor third level impeller 4, compressor fourth stage impeller 5, compressor level V impeller 6, the 6th grade of compressor
The trailing flank of impeller 7 is provided centrally with the second protrusion 23；Second protrusion 23 is cylindrical protrusions, and diameter is 80~100mm,
Second groove 24 is cylinder shape groove, and outer diameter is 120~150mm, and internal diameter is 80~100mm；
First protrusion 51 is connect with the second groove 24 on compressor first order impeller 2 by interference fit type,
Compressor first order impeller 2, compressor third level impeller 4, compressor fourth stage impeller 5, is calmed the anger at compressor second level impeller 3
The 6th grade of impeller 7 of machine level V impeller 6 and compressor is successively arranged from front to back, passes through the second raised 23 Hes between adjacent fan-wheel
Second groove 24 realizes interference fit type connection, the second protrusion 23 and 52 mistake of the first groove on the 6th grade of impeller 7 of compressor
It is full of cooperation；
The compressor first order impeller 2, compressor second level impeller 3, compressor third level impeller 4 excircle on edge
Respectively the center of circle be circumferentially uniformly arranged 6~8 trapezoidal grooves 21, trapezoidal groove 21 is used to installation quality block；It is dynamic flat to realize
Weighing apparatus or mass unbalance experimental test；Referring to fig. 2.
Axillare, compressor first order impeller 2, compressor second level impeller 3, the compressor of compressor front end axis 1
Three-level impeller 4, compressor fourth stage impeller 5, compressor level V impeller 6, compressor the 6th grade of impeller 7, compressor rear axle 8
The circumference edge portion annular of axillare be evenly equipped with 6~10 round tie rod holes 22, the diameter of round tie rod hole 22 is 10~
20mm；16 gap of pull rod is threaded through in round tie rod hole 22, and pull rod and bolt synergy are by compressor front end axis 1, compressor
First order impeller 2, compressor second level impeller 3, compressor third level impeller 4, compressor fourth stage impeller 5, compressor the 5th
Grade impeller 6, compressor the 6th grade of impeller 7, compressor rear axle 8 link together；Drawbar structure diagram is referring to Fig. 3, before pull rod
End is the end of thread 31, and rear end is cylindrical end 32.The pretightning force of pull rod by torque spanner adjust, single pretightning force be 8 ×
106N or so, and the tightening force that simulation heavy duty gas turbine rod fastening rotor can be adjusted by torque spanner is distributed, and then is carried out not
With tightening force distribution Imitating rotor dynamics attribute testing.
Axillare, turbine first order impeller 10, the first telophragma of turbine 11, the turbine second level leaf of turbine front end axis 9
The axillare of 12, the second telophragma of turbine 13, turbine third level impeller 14 and turbine rear axle 15 is taken turns from front to back successively using company
Connecting bolt links together；Specifically: the axillare and turbine first order impeller 10, the first telophragma of turbine 11 of turbine front end axis 9
Left side is attached by confining bolt, 11 right side of the first telophragma of turbine and turbine second level impeller 12, turbine second
13 left side of telophragma is bolted by confining, after 13 right end of the second telophragma of turbine and turbine third level impeller 14, turbine
The axillare of axis 15 is held to be attached by confining bolt, it is final to realize heavy combustion engine modelling rotor；
Compressor rear axle 8 and turbine front end axis 9 are coaxially connected together by fastening bolt 17 and boss.
Although the revealed embodiment of the utility model is as above, its content is only to facilitate understand the utility model
Technical solution and the embodiment that uses, be not intended to limit the utility model.Any the utility model technical field
Interior technical staff can be in the form of implementation under the premise of not departing from the utility model revealed core technology scheme
With any modification and variation are made in details, but protection scope defined by the utility model still must be with appended claims
Subject to the range of restriction.
Claims (3)
1. a kind of heavy duty gas turbine modelling rotor, it is characterised in that: including compressor section and turbine section, wherein compressor section packet
Include compressor front end axis (1), compressor first order impeller (2), compressor second level impeller (3), compressor third level impeller
(4), compressor fourth stage impeller (5), compressor level V impeller (6), compressor the 6th grade of impeller (7), compressor rear axle
(8) and pull rod (16), turbine section include turbine front end axis (9), turbine first order impeller (10), the first telophragma of turbine (11),
Turbine second level impeller (12), the second telophragma of turbine (13), turbine third level impeller (14) and turbine rear axle (15)；
Wherein, compressor front end axis (1), compressor rear axle (8), turbine front end axis (9) and turbine rear axle (15) are equal
Including axis and the axillare being fixedly connected with axis, the axillare trailing flank of compressor front end axis (1) is provided centrally with the first protrusion
(51), the axillare leading flank of compressor rear axle (8) is provided centrally with the first groove (52), the compressor first order impeller
(2), compressor second level impeller (3), compressor third level impeller (4), compressor fourth stage impeller (5), compressor level V
The leading flank of the 6th grade of impeller (7) of impeller (6) and compressor is provided centrally with the second groove (24), compressor first order impeller
(2), compressor second level impeller (3), compressor third level impeller (4), compressor fourth stage impeller (5), compressor level V
Impeller (6), the 6th grade of impeller (7) of compressor trailing flank be provided centrally with second raised (23)；
The second groove (24) on described first raised (51) and compressor first order impeller (2) is connected by interference fit type
It connects, compressor first order impeller (2), compressor second level impeller (3), compressor third level impeller (4), compressor fourth stage leaf
The 6th grade of wheel (5), compressor level V impeller (6) and compressor impeller (7) are successively arranged from front to back, lead between adjacent fan-wheel
It crosses second raised (23) and realizes that interference fit type connects with the second groove (24), second on the 6th grade of impeller (7) of compressor
Raised (23) and the first groove (52) are interference fitted；
Axillare, compressor first order impeller (2), the compressor second level impeller (3), compressor of compressor front end axis (1)
Third level impeller (4), compressor fourth stage impeller (5), compressor level V impeller (6), the 6th grade of impeller (7) of compressor, pressure
The circumference edge portion annular of the axillare of mechanism of qi rear axle (8) is evenly equipped with multiple round tie rod holes (22), and pull rod (16) gap is worn
Be located in round tie rod hole (22), pull rod and bolt synergy by compressor front end axis (1), compressor first order impeller (2),
Compressor second level impeller (3), compressor third level impeller (4), compressor fourth stage impeller (5), compressor level V impeller
(6), the 6th grade of impeller (7) of compressor, compressor rear axle (8) link together；
Axillare, turbine first order impeller (10), the first telophragma of turbine (11), the turbine second level of turbine front end axis (9)
Impeller (12), the second telophragma of turbine (13), turbine third level impeller (14) and turbine rear axle (15) axillare from front to back
It is connected in turn；
Compressor rear axle (8) and turbine front end axis (9) are coaxially connected together.
2. a kind of heavy duty gas turbine modelling rotor according to claim 1, it is characterised in that: the compressor first order
Impeller (2), compressor second level impeller (3), compressor third level impeller (4) excircle on it is circumferentially uniform along the respective center of circle
It is arranged multiple trapezoidal grooves (21), trapezoidal groove (21) is used to installation quality block.
3. a kind of heavy duty gas turbine modelling rotor according to claim 1 or 2, it is characterised in that: second protrusion
It (23) is cylindrical protrusions；Second groove (24) is cylinder shape groove.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920211610.4U CN209444375U (en) | 2019-02-19 | 2019-02-19 | A kind of heavy duty gas turbine modelling rotor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201920211610.4U CN209444375U (en) | 2019-02-19 | 2019-02-19 | A kind of heavy duty gas turbine modelling rotor |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN209444375U true CN209444375U (en) | 2019-09-27 |
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ID=68033379
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201920211610.4U Active CN209444375U (en) | 2019-02-19 | 2019-02-19 | A kind of heavy duty gas turbine modelling rotor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN209444375U (en) |
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2019
- 2019-02-19 CN CN201920211610.4U patent/CN209444375U/en active Active
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