CN207609607U - Centrifugal turbine tool with back vane structure - Google Patents
Centrifugal turbine tool with back vane structure Download PDFInfo
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- CN207609607U CN207609607U CN201720824501.0U CN201720824501U CN207609607U CN 207609607 U CN207609607 U CN 207609607U CN 201720824501 U CN201720824501 U CN 201720824501U CN 207609607 U CN207609607 U CN 207609607U
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- impeller
- compressor
- turbomachinery
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- expanding machine
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Abstract
The utility model discloses a kind of centrifugal turbine tools with back vane structure, including：Impeller；And back blade, it is set to impeller back, is used for balancing axial thrust.By after impeller back increases back vane structure, when rotary blade is during pressurizeing to working medium, back blade generates the fluid at impeller back and pushes acceleration, back blade can push impeller back working medium to generate centrifugal force, working medium is reversely pushed to vane edge, to reduce impeller back static pressure, to have the function that balancing axial thrust, the centrifugal turbine tool can effectively reduce the sealing difficulty of rotor-support-foundation system, additional seal problem when being not in the scheme as used balancing frame, back vane structure is simple simultaneously, it is processed with together with impeller, the constructive difficulty of system can be reduced.
Description
Technical field
The disclosure belongs to fluid machinery, energy source and power equipment and electricity generation system field, is related to a kind of with back vane structure
Centrifugal turbine tool.
Background technology
Turbomachinery (Turbomachinery) is the general designation for having vaned rotary type fluid machine.As turbomachinery
One kind, compressor is a kind of machine increasing compressible fluid pressure by using mechanical energy, can be divided into axial-flow type pressure
Contracting machine and centrifugal compressor, wherein centrifugal compressor are a kind of blade rotary compressor, i.e. turbo-compressor, working medium
When passing through compressor, is driven by high-speed rotating blade on impeller, vane edge is circulated under the influence of centrifugal force, through diffusion
Device realizes that pressurization, centrifugal compressor can be divided into single step arrangement and multilevel hierarchy, and wherein single-stage compressor is equipped with individually
Rotor, compound compressor carry concatenated multiple rotors.
While working medium increases pressure by centrifugal compressor, the pressure difference imported and exported in compressor due to working medium and by
Horizontal direction goes to the momentum change of vertical direction, can generate axial thrust to impeller, the axial thrust usually by balancing frame and
Axial thrust bearing compensates.Under normal conditions, axial thrust bearing cannot carry the whole thrusts being applied to by working medium on rotor,
Therefore the mode for mostly using balancing frame in the prior art compensates most of thrust, and thrust bearing is only used for undertaking remaining push away
Power.Balancing frame is a kind of rotating disk being assembled on rotor-support-foundation system, and structure is shown in shown in Figure of description Fig. 1, including main shaft
100, balancing frame 200, impeller 300, sealing structure 400 and connection structure 500, the diameter by adjusting balancing frame and two side pressures
Difference makes balancing frame achieve the purpose that balance rotor axial power.
However, it is too big in certain such as axial forces and cannot achieve effective sealing of balancing frame, or since structure limits
It when balancing axial thrust, can not need to find a kind of mode of new balancing axial thrust by the way of balancing frame, if
A kind of new centrifugal turbine tool is counted, can both overcome existing balance disc system that complicated or even appearance sealing difficulty etc. is made to lack
Point, and the centrifugal turbine tool can be made still to be applicable in the case where balancing frame isoequilibrium axial force method can not be used.
Utility model content
(1) technical problems to be solved
It is set forth above at least partly to solve present disclose provides a kind of centrifugal turbine tool with back vane structure
The technical issues of.
(2) technical solution
According to one aspect of the disclosure, a kind of centrifugal turbine tool with back vane structure is provided, including：Impeller
300；And back blade 600, it is set to 300 back of impeller, is used for balancing axial thrust.
In some embodiments of the present disclosure, back blade 600 is set on the circumference at 300 back of impeller.
In some embodiments of the present disclosure, the size of back blade 600 includes back blade outer radius Re, half outside the back blade
Diameter ReMeet：
Wherein, FmaxThe maximum axial force that can be balanced for back blade；ρ is fluid density；ω is impeller rotation angle speed
Degree；ReFor back blade outer radius；RhFor impeller hub radius.
In some embodiments of the present disclosure, the shape of back blade 600 is following one or more：It is rectangular section, straight
Blade profile or bending-type shape.
In some embodiments of the present disclosure, the number of back blade 600 is between 4~8.
In some embodiments of the present disclosure, the centrifugal turbine tool with back vane structure further includes：Main shaft 100, leaf
Wheel 300 is set to one end of main shaft 100；Connection structure 500 is attached between impeller 300 and main shaft 100；And at least
The component that two Bearning mechanisms 700, supporting spindle 100 and main shaft 100 connect.
In some embodiments of the present disclosure, with back vane structure centrifugal turbine tool be active turbomachinery or
Slave mode turbomachinery and combinations thereof；Wherein, active turbomachinery or slave mode turbomachinery include：Compressor, steam turbine,
Expanding machine, turbine；The combination of active turbomachinery and slave mode turbomachinery includes：The turbine being arranged symmetrically for runner
Machinery, compressor-expander back-to-back system (CCC-0) or compressor-turbine back-to-back system (CCC-0).
In some embodiments of the present disclosure, the combination of active turbomachinery and slave mode turbomachinery, for a compression
Machine-expanding machine one axis connection system, wherein：100 connect compressor of main shaft and expanding machine；Impeller 300 includes：Compressor impeller
310 and expanding machine impeller 320；Wherein, compressor impeller 310 are set to one end of main shaft 100；Expanding machine impeller 320, setting
In the other end of main shaft 100.
In some embodiments of the present disclosure, the back blade 600 in compressor-expander one axis connection system includes：
Compressor back blade 610 and expanding machine back blade 620；Wherein, compressor back blade 610 is set to 310 back of compressor impeller
On circumference；Expanding machine back blade 620 is set on 320 back perimeter of expanding machine impeller.
In some embodiments of the present disclosure, the centrifugal turbine tool with back vane structure is a compressor-expander
Integrated axis connection system, wherein connection structure 500 includes：Compressor connector 510 and expanding machine connector 520；Compressor connects
Fitting 510 is attached between compressor impeller 310 and main shaft 100；The expanding machine connector 520, in expanding machine impeller
It is attached between 320 and main shaft 100.
(3) advantageous effect
It can be seen from the above technical proposal that the centrifugal turbine tool with back vane structure that the disclosure provides, has
Following advantageous effect：
By after impeller back increases back vane structure, when rotary blade is during pressurizeing to working medium, back blade
The fluid at impeller back is generated and pushes acceleration, back blade can push impeller back working medium to generate centrifugal force, and working medium is anti-
To vane edge is pushed to, to reduce impeller back static pressure, to have the function that balancing axial thrust, the centrifugal turbine tool
The sealing difficulty that rotor-support-foundation system can effectively be reduced, additional seal problem when being not in the scheme as used balancing frame, together
When back vane structure it is simple, processed together with impeller, the constructive difficulty of system can be reduced.
Description of the drawings
Fig. 1 is the structural schematic diagram of balancing frame in the prior art.
Fig. 2 is the rotor-support-foundation system structural representation for the centrifugal turbine tool for having back vane structure according to the embodiment of the present disclosure
Figure.
Fig. 3 is the back vane structure schematic diagram that balancing axial thrust is used for according to the embodiment of the present disclosure.
Fig. 4 is the compressor-expander system schematic for having back vane structure according to the embodiment of the present disclosure.
【Symbol description】
100- main shafts；200- balancing frames；
300- impellers；400- sealing structures；
500- connection structures；600- back blades；
700- Bearning mechanisms；
310- compressor impellers；320- expanding machine impellers；
510- compressor connectors；520- expanding machine connectors；
610- compressor back blades；620- expanding machine back blades.
Specific implementation mode
Present disclose provides a kind of centrifugal turbine tool with back vane structure, which can effectively drop
The sealing difficulty of low rotor system, additional seal problem when being not in the scheme as used balancing frame, while back blade knot
Structure is simple, is processed together with impeller, can reduce the constructive difficulty of system.
To make the purpose, technical scheme and advantage of the disclosure be more clearly understood, below in conjunction with specific embodiment, and reference
The disclosure is further described in attached drawing.
In first exemplary embodiment of the disclosure, a kind of centrifugal turbine with back vane structure is provided
Tool.Fig. 2 is the rotor-support-foundation system structural schematic diagram for the centrifugal turbine tool for having back vane structure according to the embodiment of the present disclosure.Such as figure
Shown in 2, centrifugal turbine tool of the disclosure with back vane structure includes：Main shaft 100；Impeller 300 is set to main shaft 100
One end；Connection structure 500 is attached between impeller 300 and main shaft 100；At least two Bearning mechanisms 700, supporting spindle
100 and main shaft 100 connect component；And back blade 600, it is set to 300 back of impeller, is used for balancing axial thrust.
In the present embodiment, the centrifugal turbine tool with back vane structure is centrifugal compressor, including an impeller and two
A bearing, middle (center) bearing are used to provide supporting role to rotor assembly；Further include stator and the back blade for axial force balance,
Back blade is arranged at impeller back.The load that the centrifugal compressor is born by being placed on the sensor measurement bearing at bearing
Lotus keeps the power pressure at impeller back by control system, its axial force generated is made to ensure the bearing not overburden limit.
There are the various pieces of the centrifugal turbine tool of back vane structure to be specifically introduced the disclosure below.
Fig. 3 is the back vane structure schematic diagram that balancing axial thrust is used for according to the embodiment of the present disclosure, as shown in figure 3, notopodium
Piece 600 is set in the whole circumference at 300 back of impeller, and the number of blade is generally 4~8, generally takes 4 leaves or 6 leaves；Notopodium
The thickness of piece 600 and blade number are little to the influential effect of axial force balance, as long as the selection of vane thickness meets machinery by force
Degree；
In the present embodiment, back blade 600 uses rectangular section, straight blade profile；It is underground to be confined to such cross sectional shape, also
It can be various bending-type shapes, as long as thrust can be applied to working medium and so that working medium is generated centrifugation force effect by rotation, rise
Blade shape to same effect is all met the requirements.
The size of back blade 600 is related with the axial force size of required balance, and it is public that design follows equilibrant force theoretical calculation
Formula (Oleg Stepanov formula), the expression formula of Oleg Stepanov formula is as follows：
Wherein, FmaxThe maximum axial force that can be balanced for back blade；ρ is fluid density；ω is impeller rotation angle speed
Degree；ReFor back blade outer radius；RhFor impeller hub radius；
By formula (1) it is found that the axial force and known parameter that balance according to actual needs, including：Fluid density, impeller
Angular velocity of rotation and impeller hub radius, can obtain back blade outer radius：
It should be noted that carrying out that there is certain estimation error to the estimation of notopodium chip size based on formula (2), also need
Consider other influences factor；There can be gap between back blade and casing, which can also deposit the counterbalance effect of axial force
It is influencing, therefore back blade axial force balance effect major influence factors include mainly：S/t, back blade outer radius and impeller wheel
Hub diameter；Wherein s is back shroud of impeller to the gap of housing wall, and t is back blade height.
The present embodiment has the principle of the centrifugal turbine tool balancing axial thrust of back vane structure as follows：It is normal in compressor
When operating, impeller drives rotor-support-foundation system work, but since the pressure of impeller back working medium is higher than the pressure of incoming so that impeller needs
The axial force opposite with the direction of flow of air-flow is born, after impeller back increases back vane structure, when rotary blade is to work
During matter is pressurizeed, back blade, which generates the fluid at impeller back, pushes acceleration, back blade that can push impeller back work
Matter generates centrifugal force, working medium is reversely pushed to vane edge, to reduce impeller back static pressure, to reach balancing axial thrust
Effect.By the way that following parameter is arranged：Back shroud of impeller is to the gap of housing wall, back blade height, back blade outer radius, impeller
Hub diameter, impeller angular velocity of rotation and for fluid density etc., can have back vane structure provided in this embodiment
Centrifugal turbine tool in realize balancing axial thrust.
In the present embodiment, back blade is set in the whole circumference at impeller back, and the number of blade is generally 4~8, packet
Containing endpoint value, 4 leaves or 6 leaves are generally taken, shown in Figure 3, lobe numbers take 4 leaves, and are uniformly distributed in impeller back, but need
It is noted that the disclosure is not limited to the lobe numbers of range above, and blade can not be and be uniformly distributed, here back blade
Being uniformly distributed is from the point of view of, size design simple for moulding process is easy, is preferably embodiment；Back blade 600
Thickness and blade number are little to the influential effect of axial force balance, as long as the selection of vane thickness meets mechanical strength.
As shown in figure 3, when impeller is rotated according to direction shown in Fig. 3, pressure effect will produce to working medium, back blade can be right at this time
The fluid at impeller back, which generates, pushes acceleration, then back blade can push impeller back working medium to generate centrifugal force, by working medium
It reversely is pushed to vane edge, to reduce impeller back static pressure, to have the function that balancing axial thrust.
It should be noted that back blade has apparent decompression and axial force for the working medium that density is big, compressibility is low
Counterbalance effect, such as supercritical carbon dioxide (SCO2) working medium.SCO2Working medium density is close to liquid, and viscosity is close to gas, SCO2
At blower outlet pressure up to 20MPa even more than, its impeller back arrangement back vane structure can not only play balancing axial
The effect of power, moreover it is possible to play the role of reducing sealed pressure, there is important practical engineering value.
In second exemplary embodiment of the disclosure, additionally provide it is a kind of can be used for that runner is arranged symmetrically there is the back of the body
The turbomachinery of blade construction, basic structure and one embodiment are essentially identical, and difference place is：It is to be had by two
The turbomachinery of back vane structure symmetrically connects.
Fig. 4 is the compressor-expander system schematic for having back vane structure according to the embodiment of the present disclosure.Such as Fig. 4 institutes
Show, the structure in the present embodiment in the compressor-expander one axis connection system with back vane structure includes：Main shaft 100；
Compressor impeller 310 is set to one end of main shaft 100；Expanding machine impeller 320 is set to the other end of main shaft 100；Compressor
Connector 510 is attached between compressor impeller 310 and main shaft 100；Expanding machine connector 520, in expanding machine impeller
It is attached between 320 and main shaft 100；Compressor back blade 610 is set on 310 back perimeter of compressor impeller；And it is swollen
Swollen machine back blade 620 is set on 320 back perimeter of expanding machine impeller.
With reference to Fig. 4 it is found that in the compressor-expander one axis connection system with back vane structure, the compressor-
Expanding machine one axis connection system is with supercritical carbon dioxide (SCO2) it is working medium, in the back of compressor impeller 310 and expansion
The back of machine impeller 320 devises compressor back blade 610 and expanding machine back blade 620 respectively, can be in the compressor-expansion
The effect that respective position pressure is reduced in the operation process of machine one axis connection service system is conducive to compressor and expanding machine
Sealing.Under this kind of symmetrical structure form, axial force has basically reached balance, after back blade, can make the axial direction of system
Force balance effect is more preferable.
It should be added that Fig. 2 of attached drawing and embodiment shown in Fig. 3 are to have notopodium by taking compressor as an example
The turbomachinery of chip architecture can also be the active turbomachinery such as steam turbine, expanding machine, turbine；In addition, having back blade knot
The centrifugal turbine tool of structure can also be active turbomachinery and driven other than compressor shown in one embodiment
The combination of formula turbomachinery, including turbomachinery that runner is arranged symmetrically, as shown in third embodiment or mover with from
Motivation is leaning closely against turbomachinery system together, for example compressor-expander back-to-back system (CCC-0) or compressor-turbine lean against
Back of the body system etc.；
In conclusion the embodiment of the present disclosure provides a kind of centrifugal turbine tool with back vane structure, the centrifugation is saturating
Flat machinery can effectively reduce the difficult sealing of rotor-support-foundation system by the way that back vane structure is arranged at impeller back with balancing axial thrust
Degree, additional seal problem when being not in the scheme as used balancing frame, while back vane structure is simple, adds together with impeller
Work can reduce the constructive difficulty of system；The centrifugal turbine tool with back vane structure can be active turbomachinery,
Passive type turbomachinery and combinations thereof, it is applied widely.
Similarly, it should be understood that in order to simplify the disclosure and help to understand one or more of each open aspect,
Above in the description of the exemplary embodiment of the disclosure, each feature of the disclosure is grouped together into single implementation sometimes
In example, figure or descriptions thereof.However, the method for the disclosure should be construed to reflect following intention：It is i.e. required to protect
The disclosure of shield requires features more more than the feature being expressly recited in each claim.More precisely, such as right
As claim reflects, open aspect is all features less than single embodiment disclosed above.Therefore, it then follows tool
Thus claims of body embodiment are expressly incorporated in the specific implementation mode, wherein each claim conduct itself
The separate embodiments of the disclosure.
The disclosure is limited it should be noted that above-described embodiment illustrates rather than the disclosure, and ability
Field technique personnel can design alternative embodiment without departing from the scope of the appended claims.In the claims,
Any reference mark between bracket should not be configured to limitations on claims.Word " comprising " does not exclude the presence of not
Element or step listed in the claims.Word "a" or "an" before element does not exclude the presence of multiple such
Element.It should also be noted that, the direction term mentioned in embodiment, such as "upper", "lower", "front", "rear", "left", "right"
Deng being only the direction of refer to the attached drawing, be not used for limiting the protection domain of the disclosure.
Particular embodiments described above has carried out further in detail the purpose, technical solution and advantageous effect of the disclosure
It describes in detail bright, it should be understood that the foregoing is merely the specific embodiment of the disclosure, is not limited to the disclosure, it is all
Within the spirit and principle of the disclosure, any modification, equivalent substitution, improvement and etc. done should be included in the guarantor of the disclosure
Within the scope of shield.
Claims (9)
1. a kind of centrifugal turbine tool with back vane structure, including：
Impeller (300)；And
Back blade (600) is set to impeller (300) back, is used for balancing axial thrust；
The size of the back blade (600) includes back blade outer radius Re, the back blade outer radius ReMeet：
Wherein, FmaxThe maximum axial force that can be balanced for back blade；ρ is fluid density；ω is impeller angular velocity of rotation；Re
For back blade outer radius；RhFor impeller hub radius.
2. centrifugal turbine tool according to claim 1, wherein the back blade (600) is set to impeller (300) back
Circumference on.
3. centrifugal turbine tool according to claim 1, wherein the shape of the back blade (600) be it is following a kind of or
It is several：Rectangular section, straight blade profile or bending-type shape.
4. centrifugal turbine tool according to claim 1, wherein the number of the back blade (600) between 4~8 it
Between.
5. centrifugal turbine tool according to claim 1, further includes：
Main shaft (100), the impeller (300) are set to one end of main shaft (100)；
Connection structure (500) is attached between impeller (300) and main shaft (100)；And
At least two Bearning mechanisms (700), the component of supporting spindle (100) and main shaft (100) connection.
6. centrifugal turbine tool according to any one of claim 1 to 5, the centrifugal turbine tool is active turbine
Machinery or slave mode turbomachinery and combinations thereof；
The active turbomachinery or slave mode turbomachinery include：Compressor, steam turbine, expanding machine, turbine；
The combination of the active turbomachinery and slave mode turbomachinery includes：The turbomachinery that is arranged symmetrically for runner,
Compressor-expander back-to-back system (CCC-0) or compressor-turbine back-to-back system (CCC-0).
7. centrifugal turbine tool according to claim 5, wherein the centrifugal turbine tool be active turbomachinery or
Slave mode turbomachinery and combinations thereof；
The active turbomachinery or slave mode turbomachinery include：Compressor, steam turbine, expanding machine, turbine；
The combination of the active turbomachinery and slave mode turbomachinery is a compressor-expander one axis connection system,
Wherein：
Main shaft (100) connect compressor and expanding machine；
The impeller (300) includes：Compressor impeller (310) and expanding machine impeller (320)；
Wherein, the compressor impeller (310), is set to one end of main shaft (100)；
The expanding machine impeller (320), is set to the other end of main shaft (100).
8. centrifugal turbine tool according to claim 7, wherein：
The back blade (600) includes：Compressor back blade (610) and expanding machine back blade (620)；
The compressor back blade (610) is set on compressor impeller (310) back perimeter；
The expanding machine back blade (620) is set on expanding machine impeller (320) back perimeter.
9. centrifugal turbine tool according to claim 5, the centrifugal turbine tool is a compressor-expander shaft
Connection system, wherein：
The connection structure (500) includes：Compressor connector (510) and expanding machine connector (520)；
The compressor connector (510) is attached between compressor impeller (310) and main shaft (100)；
The expanding machine connector (520) is attached between expanding machine impeller (320) and main shaft (100).
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| Application Number | Priority Date | Filing Date | Title |
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| CN201720824501.0U CN207609607U (en) | 2017-07-07 | 2017-07-07 | Centrifugal turbine tool with back vane structure |
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| CN201720824501.0U CN207609607U (en) | 2017-07-07 | 2017-07-07 | Centrifugal turbine tool with back vane structure |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107178522A (en) * | 2017-07-07 | 2017-09-19 | 中国科学院工程热物理研究所 | Centrifugal turbine tool, the method for balancing axial thrust with back vane structure |
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2017
- 2017-07-07 CN CN201720824501.0U patent/CN207609607U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107178522A (en) * | 2017-07-07 | 2017-09-19 | 中国科学院工程热物理研究所 | Centrifugal turbine tool, the method for balancing axial thrust with back vane structure |
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| GR01 | Patent grant | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20181219 Address after: 053000 North New District of Hengshui Development Zone, Hebei Province, West Side of Zhenhua New Road Patentee after: Hengshui Keheng Power Equipment Co., Ltd. Address before: 100190 North Fourth Ring Road, Haidian District, Beijing, 11 Patentee before: Institute of Engineering Thermophysics, Chinese Academy of Sciences |
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| TR01 | Transfer of patent right |