CN102828884B - Jet flow groove structure for inhibiting turbine draft tube cavitation vortex strip - Google Patents
Jet flow groove structure for inhibiting turbine draft tube cavitation vortex strip Download PDFInfo
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- CN102828884B CN102828884B CN201210276351.6A CN201210276351A CN102828884B CN 102828884 B CN102828884 B CN 102828884B CN 201210276351 A CN201210276351 A CN 201210276351A CN 102828884 B CN102828884 B CN 102828884B
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- cone section
- jet
- draft
- groove structure
- draft cone
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- 230000002401 inhibitory effect Effects 0.000 title abstract 2
- 230000000149 penetrating effect Effects 0.000 claims description 17
- XLYOFNOQVPJJNP-UHFFFAOYSA-N water Substances O XLYOFNOQVPJJNP-UHFFFAOYSA-N 0.000 claims description 12
- 230000008676 import Effects 0.000 claims description 10
- 230000002411 adverse Effects 0.000 abstract description 4
- 238000000034 method Methods 0.000 abstract description 4
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 230000002093 peripheral effect Effects 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 6
- 230000015572 biosynthetic process Effects 0.000 description 5
- 230000006378 damage Effects 0.000 description 2
- 208000037656 Respiratory Sounds Diseases 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
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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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- 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
- Y02P—CLIMATE CHANGE MITIGATION TECHNOLOGIES IN THE PRODUCTION OR PROCESSING OF GOODS
- Y02P70/00—Climate change mitigation technologies in the production process for final industrial or consumer products
- Y02P70/50—Manufacturing or production processes characterised by the final manufactured product
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- Hydraulic Turbines (AREA)
Abstract
The invention relates to the technical field of turbines, and in particular relates to a jet flow groove structure for inhibiting a turbine draft tube cavitation vortex strip. The jet flow groove structure is characterized in that a jet flow groove is uniformly distributed along the circumferential direction of the inner wall of a taper tube section of a turbine draft tube, the length direction of the jet flow groove is parallel to the generatrix of the taper tube section of the draft tube, and the shape of the cross section of the jet flow groove, which is vertical to the axis of the taper tube section of the draft tube, is rectangular. The jet flow groove structure utilizes the adverse pressure gradient in the taper tube section of the draft tube to generate microjet, the microjet is mixed with main flow in the taper tube section of the draft tube, so the peripheral speed and strength of the draft tube cavitation vortex strip are reduced, the development of the turbine draft tube cavitation vortex strip is inhibited, the operation stability of the turbine is improved, moreover, the influence of the microjet on main flow in the taper tube section of the draft tube is limited, and the operation efficiency of the turbine is slightly influenced. The jet flow groove is simple in structure, easy to process and manufacture, and suitable for any types of turbines.
Description
Technical field
The present invention relates to turbine technology field, particularly a kind of groove structure of penetrating that suppresses turbine draft tube cavitation whirlpool band.
Background technique
As clean reproducible energy, water power is subject to the great attention of countries in the world always.2008,26 700MW generator set of Three Gorges Projects of attracting attention in the world were all gone into operation, and indicated that Chinese construction of hydropower facilities stepped into brand-new period.Cut-off is to 2011, more than big-and-middle-sized Hydropower Unit more than 500 platforms that China has gone into operation.
Before the nineties in 20th century, people often more pay close attention to the energy response of hydraulic machinery.In recent years, along with unit is to large scale development, particularly the energy response of unit and Cavitation Characteristics reach after a new height, at present the requirement of set steady are grown with each passing day.In recent years, there is the phenomenons relevant with hydraulic instability such as vibration in various degree and crackle in go into operation some Large Hydropower Station of operation of China, Ru Yantan, Li Jiaxia, two beaches, the last five small stream, all there is Hydraulic Power Unit vibration problem in various degree every river rock, Xiao Langdi, spring tide mountain etc., cause leaf destruction, draft tube tube wall is torn, the buildings such as factory building that even cause that have resonate, and jeopardize the safe operation in power station.
Model test and field observation shows, the structural vibration that the vibration of Hydraulic Power Unit causes from the non-permanent vortex in runner and vortex.Water turbine, under sub load low flow rate condition, can occur turning to identical forward bias vortex cordis band with runner at the import pipeline section of outlet of rotary wheel and draft tube, and this whirlpool band cavitation can occur conventionally and forms cavitation whirlpool band; And under large flow rate working conditions, also can, at the higher negative sense revolution whirlpool band of the central frequency of occurrences of draft tube section, in the time of the large capacity of high head, cause unit vibration.Non-permanent cavitation whirlpool band in draft tube is an important factor of water wheels stable operation of unit.
About the characteristic of tail water whirlpool band in draft tube with and harm, existingly at present understand widely and consistent conclusion, still not yet have consistent conclusion for the origin cause of formation of this whirlpool band, the research of its control is just started.Successfully suppressing on the flow instability of mixed flow pump runner and the Research foundation of mixed flow pump stator rotating stall based on jet groove, adopting and penetrating groove structure is to suppress turbine draft tube cavitation whirlpool band, the stable effective way of raising hydraulic turbine operation.
Summary of the invention
The object of the invention is to solve described in background technique and adopt jet groove STRUCTURE DEPRESSION turbine draft tube cavitation whirlpool band, improve the stable problem of hydraulic turbine operation, a kind of groove structure of penetrating that suppresses turbine draft tube cavitation whirlpool band is provided, it is characterized in that, penetrating groove structure is to be along the circumferential direction evenly arranged jet groove 3 on draft cone section 1 inwall of water turbine, the length direction of jet groove 3 is parallel to the bus of draft cone section 1, penetrating groove structure is A-A face along the upper radial end face of draft cone section axial direction, lower radial end face is B-B face, described jet groove 3 is rectangle perpendicular to the section configuration of draft cone section axis, the parameter of penetrating groove structure comprises: jet groove depth D, jet well width W, jet slot length L, penetrate the axial distance h between upper radial end face A-A and the draft cone section import 2 of groove structure
1with jet groove quantity N, with draft cone section wall thickness D
0for reference, the span of jet groove depth D is
, to penetrate the draft cone section inwall 7 girth C corresponding to upper radial end face A-A place of groove structure
0for reference, the span of jet well width W is
, with the axial height h of draft cone section
0for reference, the span of jet slot length L is
, wherein θ represents the half-angle of spread of draft cone section, penetrate the axial distance h between upper radial end face A-A and the draft cone section import 2 of groove structure
1be more than or equal to 0.15 h
0, the span of jet groove quantity N is 9～12,
The described jet groove 3 of penetrating in groove structure is longitudinally grooving formation on draft cone section inwall 7, or longitudinally splint fixation formation on draft cone section inwall 7.
Beneficial effect of the present invention is, penetrates groove structure and utilizes the adverse pressure gradient in draft cone section to produce microjet, suppresses turbine draft tube cavitation whirlpool band, improved the stability of hydraulic turbine operation, but very little on the impact of hydraulic turbine operation efficiency; Simple in structure, easily process and manufacture; Be applicable to the water turbine of any type.
Brief description of the drawings
Fig. 1 is the structural representation of draft cone section jet groove, only draws the structure on draft cone section inwall in figure;
Fig. 2 is that in Fig. 1, A-A place draft cone section is penetrated radially section configuration schematic diagram of groove structure;
Fig. 3 is the 3D shape schematic diagram that draft cone section is penetrated groove structure;
Fig. 4 is the working principle schematic diagram of the jet groove STRUCTURE DEPRESSION turbine draft tube cavitation whirlpool band development of draft cone section.
Wherein: 1--draft cone section, the import of 2--draft cone section, 3--jet groove, the outlet of 4--draft cone section, 5--draft tube cavitation whirlpool band, 6--draft cone section outer wall, 7--draft cone section inwall, 8--microjet, 9--turbine draft tube flow direction.
Embodiment
Below in conjunction with embodiment and accompanying drawing, the present invention is further illustrated.
Fig. 1 is the structural representation of draft cone section jet groove, and Fig. 2 is that in Fig. 1, A-A place draft cone section is penetrated radially section configuration schematic diagram of groove structure.Penetrate groove structure and be on the draft cone section inwall 7 of the draft cone section 1 of water turbine and be along the circumferential direction evenly arranged jet groove 3, the length direction of jet groove 3 is parallel to the bus of draft cone section 1, penetrating groove structure is A-A face along the upper radial end face of draft cone section axial direction, lower radial end face is B-B face, and described jet groove 3 is rectangle perpendicular to the section configuration of draft cone section axis.
The parameter of as depicted in figs. 1 and 2, penetrating groove structure comprises: jet groove depth D, jet well width W, jet slot length L, penetrate the axial distance h between upper radial end face A-A and the draft cone section import 2 of groove structure
1with jet groove quantity N.With draft cone section wall thickness D
0for reference, draft cone section wall thickness D
0the radial spacing that is draft cone section outer wall 6 and draft cone section inwall 7, the span of jet groove depth D is
; To penetrate the draft cone section inwall 7 girth C corresponding to upper radial end face A-A place of groove structure
0for reference, the span of jet well width W is
; With the axial height h of draft cone section
0for reference, h
0be draft cone section import 2 and export 4 axial perpendicular distance with draft cone section, the span of jet slot length L is
, wherein θ represents the half-angle of spread of draft cone section; Penetrate the axial distance h between upper radial end face A-A and the draft cone section import 2 of groove structure
1be more than or equal to 0.15 h
0; The span of jet groove quantity N is 9～12.
The jet groove 3 of penetrating in groove structure is longitudinally grooving formation on draft cone section inwall 7, or on draft cone section inwall 7, longitudinally splint fixation forms, the present embodiment is longitudinal grooving structure on draft cone section inwall 7, as shown in Figure 3, concrete data are the 3D shape schematic diagram of draft cone section jet groove: h
0for 500mm, D
0for 52mm, θ is 3 °, C
0for 1124.25mm, D is 14mm, and W is 45.8mm, and L is 375.51mm, h
1for 75mm, N is 12.
Working principle of the present invention is as follows:
The working principle schematic diagram of the jet groove STRUCTURE DEPRESSION turbine draft tube cavitation whirlpool band development of draft cone section as shown in Figure 4, the tail water of water turbine enters draft cone section 1 by turbine draft tube flow direction 9 from draft cone section import 2, discharged by draft cone section outlet 4, due to the diffusion action of draft cone section 1, draft cone section 1 is interior becomes large along water (flow) direction pressure, has the adverse pressure gradient with flow opposite direction.Under the effect of adverse pressure gradient, the interior formation of jet groove 3 microjet 8 contrary with draft cone section 1 main flow direction between the upper radial end face A-A and the lower radial end face B-B that penetrate groove structure; Microjet 8 mixes with the interior main flow of draft cone section 1, reduces the circumferential speed of draft tube cavitation whirlpool band 5, weakens the intensity of draft tube cavitation whirlpool band 5, suppresses the development of draft tube cavitation whirlpool band 5; Meanwhile, microjet 8 is limited on the interior main flow impact of draft cone section 1, very little on the impact of hydraulic turbine operation efficiency.
Be more than on draft cone section inwall 7 longitudinally grooving form the embodiment's of jet groove 3 structure and principles illustrated, on draft cone section inwall 7 longitudinally splint fixation form jet groove 3 embodiment's structure and principles illustrated similarly.
According to the working principle of jet groove 3, penetrate groove structure and be applicable to the water turbine of any type, comprise Francis turbine, axial flow hydraulic turbine, inclined flow turbine and pump turbine.
The above; only for preferably embodiment of the present invention, but protection scope of the present invention is not limited to this, is anyly familiar with in technical scope that those skilled in the art disclose in the present invention; the variation that can expect easily or replacement, within all should being encompassed in protection scope of the present invention.Therefore, protection scope of the present invention should be as the criterion with the protection domain of claim.
Claims (2)
1. one kind is suppressed the groove structure of penetrating of turbine draft tube cavitation whirlpool band, it is characterized in that, penetrating groove structure is to be along the circumferential direction evenly arranged jet groove (3) on draft cone section (1) inwall of water turbine, the length direction of jet groove (3) is parallel to the bus of draft cone section (1), penetrating groove structure is A-A face along the upper radial end face of draft cone section axial direction, lower radial end face is B-B face, and described jet groove (3) is rectangle perpendicular to the section configuration of draft cone section axis; The parameter of penetrating groove structure comprises: jet groove depth D, jet well width W, jet slot length L, penetrate the axial distance h between upper radial end face A-A and the draft cone section import (2) of groove structure
1with jet groove quantity N, with draft cone section wall thickness D
0for reference, the span of jet groove depth D is
; To penetrate draft cone section inwall (7) the girth C corresponding to upper radial end face A-A place of groove structure
0for reference, the span of jet well width W is
; With the axial height h of draft cone section
0for reference, the span of jet slot length L is
, wherein θ represents the half-angle of spread of draft cone section; Penetrate the axial distance h between upper radial end face A-A and the draft cone section import (2) of groove structure
1be more than or equal to 0.15 h
0; The span of jet groove quantity N is 9～12.
2. a kind of groove structure of penetrating that suppresses turbine draft tube cavitation whirlpool band according to claim 1, it is characterized in that, the described jet groove (3) of penetrating in groove structure is to form in the upper longitudinal grooving of draft cone section inwall (7), or forms in the upper longitudinal splint fixation of draft cone section inwall (7).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210276351.6A CN102828884B (en) | 2012-08-03 | 2012-08-03 | Jet flow groove structure for inhibiting turbine draft tube cavitation vortex strip |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210276351.6A CN102828884B (en) | 2012-08-03 | 2012-08-03 | Jet flow groove structure for inhibiting turbine draft tube cavitation vortex strip |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102828884A CN102828884A (en) | 2012-12-19 |
| CN102828884B true CN102828884B (en) | 2014-06-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201210276351.6A Expired - Fee Related CN102828884B (en) | 2012-08-03 | 2012-08-03 | Jet flow groove structure for inhibiting turbine draft tube cavitation vortex strip |
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Families Citing this family (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104121138B (en) * | 2014-07-28 | 2016-12-07 | 清华大学 | A kind of turbine draft tube with whirlpool inhibitory action |
| CN105240186A (en) * | 2015-10-16 | 2016-01-13 | 江苏大学 | Hydraulic design method for tail water pipe of small hydraulic turbine device |
| CN105275711A (en) * | 2015-10-16 | 2016-01-27 | 江苏大学 | Hydraulic design method for bent tail water pipe of hydraulic turbine device |
| CN113049219B (en) * | 2021-03-05 | 2022-09-16 | 哈尔滨工业大学 | Experimental device for simulating cavitation vortex strip form |
| CN115199455A (en) * | 2022-08-03 | 2022-10-18 | 温州大学 | Grooved draft tube for inhibiting hump characteristic of water pump turbine and use method thereof |
| CN115949543B (en) * | 2023-03-15 | 2023-11-28 | 哈尔滨电机厂有限责任公司 | Taper pipe structure for improving water pump stability of water pump turbine under water pump working condition |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2100503U (en) * | 1991-07-20 | 1992-04-01 | 东方电机厂 | Vane flow-stabilizing device of turbines |
| CN1740556A (en) * | 2005-09-16 | 2006-03-01 | 清华大学 | Electromagnetic eddy inhibitor for draft tube of mixed flow water turbine |
| CA2549749A1 (en) * | 2006-06-09 | 2007-12-09 | General Electric Company | Control jet for hydraulic turbine |
| CN101158328A (en) * | 2007-10-12 | 2008-04-09 | 杭州电子科技大学 | Novel draft-tube and preparation method thereof |
-
2012
- 2012-08-03 CN CN201210276351.6A patent/CN102828884B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2100503U (en) * | 1991-07-20 | 1992-04-01 | 东方电机厂 | Vane flow-stabilizing device of turbines |
| CN1740556A (en) * | 2005-09-16 | 2006-03-01 | 清华大学 | Electromagnetic eddy inhibitor for draft tube of mixed flow water turbine |
| CA2549749A1 (en) * | 2006-06-09 | 2007-12-09 | General Electric Company | Control jet for hydraulic turbine |
| CN101158328A (en) * | 2007-10-12 | 2008-04-09 | 杭州电子科技大学 | Novel draft-tube and preparation method thereof |
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|---|---|
| CN102828884A (en) | 2012-12-19 |
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Granted publication date: 20140618 |