CN205387960U - Radial seal structure suitable for cantilever rotor - Google Patents
Radial seal structure suitable for cantilever rotor Download PDFInfo
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- CN205387960U CN205387960U CN201620142359.7U CN201620142359U CN205387960U CN 205387960 U CN205387960 U CN 205387960U CN 201620142359 U CN201620142359 U CN 201620142359U CN 205387960 U CN205387960 U CN 205387960U
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- seal
- seal structure
- radial seal
- movable vane
- main shaft
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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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- Turbine Rotor Nozzle Sealing (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The utility model relates to a radial seal structure suitable for cantilever rotor. Concrete content does: a turbomachine that adopts the cantilever to support the rotor moves, sets up along radial distribution's seal structure in the leakage cavity between the quiet leaf at it, and the seal is fixed on static, and the high -pressure fluid to the leakage of sound interface seals through the cooperation between seal and the movable vane rim plate. The utility model discloses when accomplishing sealed effect, show the axial space who reduces the seal and take the main shaft for the rotordynamics design of equipment is more nimble, and the structure is compacter, has also reduced axial thrust that the rim plate received and footstep bearing's friction wasted work simultaneously, has improved the energy conversion efficiency of equipment, is applicable to all kinds of turbomachines that adopt cantilever rotor structure.
Description
Technical field
This utility model relates to the sealing structure of turbomachine, specifically a kind of radial seal structure suitable in cantilever rotor.
Background technology
The sealing structure species of turbomachine is more, and the working media type that is suitable for, pressure, temperature etc. are different, but general all axially disposed at main shaft near surface for the sealing of leakage chamber between dynamic and static leaf.
When sealing pressure and being higher, the structures such as carbocyclic ring, labyrinth, honeycomb or brush seal take axial space bigger on main shaft, affect the design of rotor dynamics scheme and the compactedness of device structure, and although the mechanically-sealing apparatus of the excellent performances such as dry gas seals can utilize shorter axial length to complete the sealing to high-pressure working medium, but also having operating temperature and the restriction of smallest radial size, application scenario is limited.In addition, when the axially disposed sealing structure of main shaft near surface, it is filled with high-pressure working medium from wheel disc hub positions (i.e. leakage chamber import) to the import sealing structure, make the axial thrust that rotor bears bigger, and then the friction wasted work of increase thrust bearing, or extra labyrinth must be adopted to offset excessive axial thrust.
In order to reduce the axial thrust that axial seal body takies the axial space of main shaft and rotor bears, the utility model proposes a kind of radial seal structure suitable in cantilever rotor.
Utility model content
The utility model discloses a kind of radial seal structure suitable in cantilever rotor, relate to the sealing structure of turbomachine, the axial thrust that seal takies the axial space of main shaft and rotor bears can be reduced by the application of this structure, the structural design making equipment is more flexible, and the stability of its efficiency and operation can be improved, have broad application prospects.
For reaching above-mentioned purpose, technical solution of the present utility model is as follows:
A kind of radial seal structure suitable in cantilever rotor, described radial seal structure is arranged at the turbomachine adopting cantilever rotor structure, described turbomachine includes housing and cantilever rotor, described cantilever rotor includes the movable vane wheel disc being arranged on main shaft, described housing is fixed with the stator blade and ring seat thereof that are coaxially disposed with described movable vane wheel disc, it is characterized in that, moving at described turbomachine, radially distributed seal is set in the leakage chamber between stator blade, described seal is fixed on static element, sealed by the high-pressure fluid to the leakage of sound interface that coordinates between seal with movable vane wheel disc.
Preferably, the moment of torsion of described movable vane wheel disc and main shaft passes through end-tooth, Axis Tripod, singly-bound or double bond and completes, movable vane wheel disc and main shaft by axis head nut or on the basis of axis head nut outfit pull bar fix.
Preferably, described seal is by seam or be bolted on the static elements such as housing, stator blade ring seat or bearing housing, it is ensured that main packing accurate positioning, firmly, and deformation quantity is little.
Preferably, described radial seal structure can be single labyrinth seal (interdigitated electrode structure, vertical tree type or J type), carbon ring seal, honeycomb seal or brush seal, it is also possible to for multiple combination forms of above-mentioned sealing structure.
Preferably, described movable vane wheel disc can arrange groove, projection near the side of seal, it is also possible to is set to plane, inclined-plane or curved surface, in order to have coordinated sealing function with radial seal body.
Sealed by the high-pressure fluid to the leakage of sound interface that coordinates between seal with movable vane wheel disc, only take up axial length only small on main shaft.Impeller couples with main shaft in the axial direction, it is simple to the coordinating of radial seal body, installation and clearance measurement.
Use due to radial seal structure so that the leakage chamber between dynamic and static leaf is from the import of leakage chamber to main shaft surface location, and fluid pressure is in being gradually reduced trend, and compared with axial seal structure, the axial thrust suffered by rotor is substantially reduced.Under the premise ensureing sealing effectiveness, the mean radius that seal is installed is more big, and the effect that axial thrust reduces is more obvious.
Preferably, axial oil sealing or auxiliary sealing structure it are further provided with between described housing and the main shaft of cantilever rotor.Radial seal structure can be integrated with axial oil sealing or auxiliary sealing structure, namely has the seal of radial and axial sealing function simultaneously.
Preferably, described turbomachine is for compression or expands class turbomachine, and the impeller type of described turbomachine can be radial inflow, mixed-flow and axial-flow type, and working media can be gas, liquid or multiphase flow, and impeller can be single-stage or multistage.
Foregoing is ensureing while device structure design rationality, reduces the axial length of seal and axial thrust that rotor bears, it is possible to improve its operation stability and energy utilization efficiency.
Compared with the existing technology, advantage of the present utility model with have the beneficial effect that
1. the employing of radial seal structure reduces seal and takies the axial length of main shaft so that the rotor dynamics conceptual design of equipment is more flexible, and structure is compacter；
2. radial seal structure reduces the average pressure of sound handing-over leakage chamber, so that the axial thrust that rotor bears is significantly less than axial gland seal structure commonly used at present, also reduces the friction wasted work of thrust bearing simultaneously；
3. radial seal structure can play all or part of sealing function, can coaxial seal combination use according to actual needs.
Accompanying drawing explanation
Fig. 1 is the cantilever rotor structure schematic diagram with radial seal structure；
Fig. 2 is the partial enlarged drawing of I in Fig. 1；
Fig. 3 be in leakage chamber power pressure with the change curve of the radius of gyration.
Detailed description of the invention
Below in conjunction with accompanying drawing, structure of the present utility model, technical scheme are further described specifically, provide an embodiment of the present utility model.
As an embodiment of the present utility model, as shown in Figure 1, 2, one axial-flow turbine adopting cantilever rotor structure, this axial-flow turbine includes air inlet volute 2 and cantilever rotor, cantilever rotor includes the movable vane wheel disc 6 being arranged on main shaft 5, air inlet volute 2 is fixed with the stator blade and ring seat 8 thereof that are coaxially disposed with movable vane wheel disc 6, the outer circumference surface of movable vane wheel disc 6 is provided with movable vane 9.Movable vane wheel disc 6 is coupled by end-tooth, pull bar and spindle nose locking nut 7 with main shaft 5.The import department of air inlet volute 2 is provided with inlet flange 1, and exit is provided with exhaust flange 3, and main shaft 5 is supported by spring bearing 4.
The radial seal body 11 being made up of stage teeth is fixed on by seam on air inlet volute 2 and fixed blade ring, movable vane wheel disc 6 is provided with groove near the side of radial seal body 11 and coordinates with stage teeth, gap between tooth top and movable vane wheel disc 6 surface is 0.15～0.35mm, is completed the sealing of the high-pressure fluid of leakage between dynamic and static leaf by this radial labyrinth.
Oil sealing (or secondary sealing structure) 10 is in order to isolation lubricating oil or auxiliary seal, it is possible to chooses whether as required to adopt, and can be integrated with radial seal structure, namely has the seal of radial and axial sealing function simultaneously.
Radial seal structure, while completing sealing function, has only taken up axial length only small on main shaft.
First ensure the relative position of air inlet volute 2, bearing 4, main shaft 5, oil sealing 10, fixed blade ring 8 and radial seal body 11 during equipment assembling, then adopt pull bar and axis head nut 7 leaf dish (6 and 9) and main shaft 5 to be locked.
For this radial seal structure, owing between comb and sheave surface, the flow area in gap diminishes with the reduction of the radius of gyration, during radially uniform layout comb, leakage chamber fluid pressure is general as shown in Figure 3 with the change curve of the radius of gyration, the pressure drop effect of minor radius position becomes apparent from, it is assumed that it substantially meets logarithmic function rule.It is further assumed that the import stagnation pressure of this axial-flow turbine is 75bar (absolute pressure, lower same), expansion ratio is 3.5, seal structure outlet (i.e. b position, close to main shaft surface, radius of gyration 40mm) pressure is 1bar, so leakage chamber entrance (i.e. a position, radius of gyration 160mm) static pressure is 27bar, after movable vane, the static pressure of leakage chamber is 21bar, axial thrust suffered by movable vane is about 51kN, if during the axial seal structure calculating only with main shaft near surface according to above-mentioned parameter, axial thrust suffered by rotor is about 85.5kN, during according to the sealing of the complete high-pressure flow working medium of the radial seal shown in embodiment, axial thrust suffered by rotor is about 57.3kN, thrust decline 28.2kN (ratio is 33%), effect is notable.
In addition, under the premise ensureing sealing effectiveness, the average radius of gyration that radial seal body is installed is more big, the effect that axial thrust reduces is more obvious, if the sealing effectiveness of large radius position (i.e. the speed of pressure reduction and amplitude) is better than rule shown in Fig. 3, the reduction of axial thrust will be more significant.
Foregoing completes a radial seal structure with cantilever rotor axial-flow turbine and arranges, seal has only taken up the axial length that main shaft is less, being substantially reduced while rotor bears axial thrust, also reduces the friction power loss of thrust bearing.This utility model embodiment is applicable for use with all kinds of turbomachines of cantilever support.
By above-described embodiment, effectively achieve the purpose of this utility model.Person skilled in art is appreciated that this utility model includes but not limited to the content described in accompanying drawing and above detailed description of the invention.Although this utility model is just it is now recognized that practicality and preferred embodiment illustrate the most, but it should be recognized that, this utility model is not limited to the disclosed embodiments, and any amendment not necessarily departing from function of the present utility model and structural principle is intended to be included in the scope of claims.
Claims (7)
1. the radial seal structure being applicable to cantilever rotor, described radial seal structure is arranged at the turbomachine adopting cantilever rotor structure, described turbomachine includes housing and cantilever rotor, described cantilever rotor includes the movable vane wheel disc being arranged on main shaft, described housing is fixed with the stator blade and ring seat thereof that are coaxially disposed with described movable vane wheel disc, it is characterized in that: moving at described turbomachine, radially distributed seal is set in the leakage chamber between stator blade, described seal is fixed on static element, sealed by the high-pressure fluid to the leakage of sound interface that coordinates between seal with movable vane wheel disc.
2. radial seal structure according to claim 1, it is characterised in that: described seal is by seam or is bolted on the bearing housing of housing, stator blade ring seat or cantilever rotor.
3. radial seal structure according to claim 1, it is characterised in that: described radial seal structure is labyrinth seal, carbon ring seal, honeycomb seal or brush seal structure, or the combination of above-mentioned sealing structure.
4. radial seal structure according to claim 1, it is characterised in that: described movable vane wheel disc is provided with groove or projection near the side of seal, or is set to plane, inclined-plane or curved surface, in order to have coordinated sealing function with described seal.
5. radial seal structure according to claim 1, it is characterised in that: it is further provided with axial oil sealing or auxiliary sealing structure between described housing and the main shaft of cantilever rotor.
6. radial seal structure according to claim 1, it is characterised in that: the sealing medium of described radial seal structure is gas, liquid or multiphase flow, and impeller progression is single-stage or multistage.
7. radial seal structure according to claim 1, it is characterized in that: the moment of torsion of described movable vane wheel disc and main shaft passes through end-tooth, Axis Tripod, singly-bound or double bond and completes, movable vane wheel disc and main shaft by axis head nut or on the basis of axis head nut outfit pull bar fix.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620142359.7U CN205387960U (en) | 2016-02-25 | 2016-02-25 | Radial seal structure suitable for cantilever rotor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201620142359.7U CN205387960U (en) | 2016-02-25 | 2016-02-25 | Radial seal structure suitable for cantilever rotor |
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| Publication Number | Publication Date |
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| CN205387960U true CN205387960U (en) | 2016-07-20 |
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| CN201620142359.7U Active CN205387960U (en) | 2016-02-25 | 2016-02-25 | Radial seal structure suitable for cantilever rotor |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109026761A (en) * | 2018-10-18 | 2018-12-18 | 毕森机械（上海）有限公司 | A kind of compressor host |
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2016
- 2016-02-25 CN CN201620142359.7U patent/CN205387960U/en active Active
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN109026761A (en) * | 2018-10-18 | 2018-12-18 | 毕森机械（上海）有限公司 | A kind of compressor host |
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| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant |