CN102182517B - Boundary layer turbine with blade plate - Google Patents
Boundary layer turbine with blade plate Download PDFInfo
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- CN102182517B CN102182517B CN 201110112912 CN201110112912A CN102182517B CN 102182517 B CN102182517 B CN 102182517B CN 201110112912 CN201110112912 CN 201110112912 CN 201110112912 A CN201110112912 A CN 201110112912A CN 102182517 B CN102182517 B CN 102182517B
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- blade
- disc
- boundary layer
- rotating shaft
- turbine
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- 239000012530 fluid Substances 0.000 abstract description 12
- 230000000149 penetrating effect Effects 0.000 abstract 1
- 238000000034 method Methods 0.000 description 4
- 230000000694 effects Effects 0.000 description 3
- 239000011888 foil Substances 0.000 description 2
- 238000005728 strengthening Methods 0.000 description 2
- 239000002028 Biomass Substances 0.000 description 1
- UGFAIRIUMAVXCW-UHFFFAOYSA-N Carbon monoxide Chemical compound [O+]#[C-] UGFAIRIUMAVXCW-UHFFFAOYSA-N 0.000 description 1
- 230000004308 accommodation Effects 0.000 description 1
- 238000004140 cleaning Methods 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000007812 deficiency Effects 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000009826 distribution Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 239000003546 flue gas Substances 0.000 description 1
- 238000013467 fragmentation Methods 0.000 description 1
- 238000006062 fragmentation reaction Methods 0.000 description 1
- 239000000446 fuel Substances 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 238000003754 machining Methods 0.000 description 1
- 239000000463 material Substances 0.000 description 1
- 239000002245 particle Substances 0.000 description 1
- 239000003381 stabilizer Substances 0.000 description 1
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Abstract
The invention relates to a boundary layer turbine with a blade plate, which belongs to the field of energy and power and the like, is characterized by comprising a barrel (2), end covers (8, 9) arranged at two ends of the barrel, a rotating shaft (5) penetrating the end covers and supported at the center of the barrel (2) by bearings (11, 12), and a working plate group (14) arranged on the rotating shaft, wherein a blade (4) is arranged between every two adjacent working plates (3) in the working plate group (14) and divides an annular passage between the plates into a plurality of sector passages, an included angle between the inlet airflow direction of a nozzle (1) and a blade profile at the inlet of the blade (4) is 0 degree, the turbine working plate group is provided with an outlet airflow passage (7), and the end cover is provided with a turbine airflow outlet hole (13). The boundary layer turbine with the blade plate has the characteristics of being simple and compact in structure, high in efficiency, shake-resistant and wide in fluid application range, and being especially applicable to an organic Ranking cycle (ORC) generating system with small scale and low temperature.
Description
Technical field
The present invention relates to a kind of band leaf disc type boundary layer turbine, belong to the energy and power field.
Background technique
That disc type boundary layer turbine has is simple in structure, machining require low, cost is little and characteristics such as fluid wide accommodation, can be applied in the occasion that multiple impeller type turbine can't adapt to, be specially adapted to the flue gas behind high viscosity, non-Newtonian fluid or unconventional fuel such as the biomass combustion.Because the annular pass that every adjacent two work discs constitute in the disc type boundary layer turbine work disc group has self-cleaning function, also is applicable to the heterogeneous fluid of band particle.
But the research to disc type boundary layer turbine only limits to the laboratory at present, does not obtain extensive use as yet.The subject matter that influences the application of disc type boundary layer turbine is that its efficient is low, the life-span short.Only rely on the boundary layer friction torque and promote the rotating shaft rotation and realize that the disc type turbine moment of heat commentaries on classics merit is little, the turbine internal drop is low, isentropic efficiency not high (14%-35%).In addition, in order to improve disc type boundary layer turbine output power, researchers, and the increase turbine inlet outlet pressure differential that adopts improves rotating speed, uses the method for the thin light disc of major diameter simultaneously.Yet, disc under high speed conditions since the fluctuation of flowing can shake.Because the vibrations of disc can cause the further deterioration of mobility status between disc after disc shakes, and this can be strengthened in the flow channel gap little (generally less than 1 mm) that adjacent two discs constitute in the disc group.Generally, disc vibrations meeting improves and aggravates along with rotating speed, even fragmentation can take place suddenly, so the life-span of disc type boundary layer turbine work disc is generally shorter.Therefore, in order to improve disc type boundary layer turbine technology economic performance and to advance its application, be necessary that improving its isentropic efficiency by the improvement disc structure reduces vibrations simultaneously.
Summary of the invention
The objective of the invention is to propose a kind of isentropic efficiency height, the little band leaf disc type boundary layer turbine of vibrations.
A kind of band leaf disc type boundary layer turbine, it is characterized in that: comprise cylindrical shell, be installed on the end cap at cylindrical shell two ends, also comprise and pass end cap and by the rotating shaft of bearings in the cylindrical shell center, work disc group is installed in the rotating shaft, between every adjacent work disc the blade that annular pass between disc is divided into a plurality of sector channels is installed in the work disc group, also comprise the nozzle of being located at work disc side, wherein nozzle entrance airflow direction and blade inlet place blade profile angle are the 0-15 degree, above-mentioned turbine work disc is provided with the exit flow passage, and end cap is provided with turbine flow outlet hole.
Above-mentioned blade is uniformly distributed on the work disc, constitutes the similar sector channel of a plurality of flow characteristics, can avoid the big deficiency of local flow loss in the conventional disc type boundary layer turbine annular fluid passage on the one hand; Blade can also play the effect of disc strengthening rib on the other hand, compare with the annular pass, the interior flow fluctuation amplitude of the sector channel that a plurality of fluid characteristicss are identical can significantly reduce, thus the short problem of disc life-span that can alleviate the vibrations of disc group and cause therefrom.
Above-mentioned blade is straight line type or arc line type, conventional not little with the disc type boundary layer turbine difficulty of processing increase of blade, and because increasing vane foil the air current flow direction is changed the isentropic efficiency that the moment of thrust that produces can significantly improve turbine, can also omit pad between the required disc of conventional disc type boundary layer turbine.And compare with conventional radial-inward-flow turbine etc., although it is not this turbine isentropic efficiency is lower slightly, because this turbine blade molded lines is simple, high to material and processes required precision.
Above-mentioned exit flow channel arrangement is axial in the disc group, every adjacent two discs constitute a mobile operation element, adopt that the disc group of axial passage is actual to be equivalent to a plurality of mobile operation elements with parallel form of identical import and export operational condition, when behind some disc operational failure wherein or can not influence the proper functioning of other discs after damaging, turbine integral body can also work on.
If said nozzle inlet air flow direction and blade inlet place blade profile angle are 0 degree, help stabilizer vane ingress air velocity distribution on the one hand, reduce blade inlet place air-flow crushing, can also reduce on the other hand because of the direct high requirement of impacting blade strength of air-flow.
Another kind of band leaf disc type boundary layer turbine, it is characterized in that: comprise cylindrical shell, be installed on the end cap at cylindrical shell two ends, also comprise and pass end cap and in the rotating shaft at cylindrical shell center, rotating shaft, work disc group is installed by bearings, between the adjacent work disc blade that annular pass between disc is divided into a plurality of sector channels is installed in the work disc group, also comprise the nozzle of being located at work disc side, wherein nozzle entrance airflow direction and blade inlet place blade profile angle are the 0-15 degree; Above-mentioned rotating shaft is hollow rotating shaft, and the cavity of hollow rotating shaft is the exit flow passage, and the hollow rotating shaft of root of blade radially has the air flow inlet hole.。
Description of drawings
Fig. 1 is disc type boundary layer turbine structural drawing
Fig. 2 is band leaf disc type boundary layer turbine working disk chip architecture figure
Fig. 3 is with the band leaf disc type boundary layer turbine disc structure figure of hollow shaft cavity as the exit flow passage
Fig. 4 is conventional disc type boundary layer turbine working disk chip architecture figure
Number in the figure title: 1. nozzle, 2. cylindrical shell, 3. work disc, 4. blade, 5. rotating shaft, 6. pad, 7. exit flow passage, 8. left end cap, 9. right end cap, 10. hollow shaft radial air flow inlet opening, 11. left bearing, 12. right bearing, 13. turbine flow outlet holes, 14. work disc groups
Embodiment
With reference to accompanying drawing, the invention provides a kind of band leaf disc type boundary layer turbine, comprising cylindrical shell 2, be installed on the end cap 8 and 9 at cylindrical shell 2 two ends, also comprise in the rotating shaft 5, rotating shaft 5 of passing end cap and being supported in the cylindrical shell center by bearing 11 and 12 work disc group 14 is installed, between the adjacent work disc 3 blade 4 is installed in the work disc group 14, wherein nozzle 1 inlet air flow direction and blade 4 ingress blade profile angles are 0 degree; Above-mentioned turbine work disc group 14 is provided with exit flow passage 7, and left end cap 8 is provided with turbine flow outlet hole 13.
Describe the running of band leaf disc type boundary layer turbine provided by the invention in detail below with reference to Fig. 2, Fig. 3.Working fluid tangentially enters the fan-shaped fluid passage that work disc 3 and blade 4 gaps constitute by nozzle 1 along work disc group 14 edges, change under the moment of thrust synergy that airflow direction produces in friction torque and blade 4 blade profiles between fluid and work disc, promote rotating shaft 5 rotations, thereby realize heat commentaries on classics merit.The low-pressure fluid of finishing merit flows out turbine flow outlet holes 13 along the exit flow passage 7 of axial direction from disc group 14.
Shown in Figure 3 basic and Fig. 2 is similar as the band leaf disc type boundary layer turbine implementation process of exit flow passage with the hollow shaft cavity, difference is, the low-pressure fluid of finishing after the merit is that exit flow passage 7 is discharged turbines by the cavity that blade 4 root hollow rotating shafts 5 air flow inlet hole 10 radially enters hollow rotating shaft.This turbine rotating shaft cavity namely is equivalent to turbine flow outlet hole, need not set up flow outlet hole 13 at the turbine end cap.
Compare with the disc type boundary layer turbine of work disc pattern shown in Figure 4, adopt Fig. 2 and band leaf disc shown in Figure 3, can work in coordination with on the one hand and utilize friction torque and vane foil to change the moment of thrust acting that airflow direction produces, increase turbine output power and turbine isentropic efficiency, improve turbine acting ability; On the other hand, blade 4 can play the effect of work disc 3 strengthening rib, and stabilize fluid flow reduces the vibrations of work disc group 14, thereby can prolong the turbine operating life.In addition, blade also can play the effect of pad between conventional disc type boundary layer turbine work disc, thereby can omit pad, simplifies the turbine rotor structure.
Claims (6)
1. be with leaf disc type boundary layer turbine for one kind, it is characterized in that: comprise cylindrical shell (2), be installed on the end cap at cylindrical shell (2) two ends, also comprise and pass end cap and by the rotating shaft (5) of bearings in cylindrical shell (2) center, work disc group (14) is installed in the rotating shaft, between the adjacent work disc (3) blade (4) that annular pass between disc is divided into a plurality of sector channels is installed in the work disc group (14), also comprise the nozzle (1) of being located at work disc (3) side, wherein nozzle (1) inlet air flow direction and blade (4) ingress blade profile angle are the 0-15 degree; Above-mentioned turbine work disc group (14) is provided with exit flow passage (7), and end cap is provided with turbine flow outlet hole (13).
2. band leaf disc type boundary layer turbine according to claim 1, it is characterized in that: above-mentioned blade (4) is uniformly distributed in (3) on the work disc.
3. band leaf disc type boundary layer turbine according to claim 1, it is characterized in that: above-mentioned blade (4) blade profile is straight line type or arc line type.
4. band leaf disc type boundary layer turbine according to claim 1 is characterized in that: above-mentioned exit flow passage (7) be arranged in work disc group (14) axially.
5. band leaf disc type boundary layer turbine according to claim 1 is characterized in that: said nozzle (1) inlet air flow direction and blade (4) ingress blade profile angle are 0 degree.
6. be with leaf disc type boundary layer turbine for one kind, it is characterized in that: comprise cylindrical shell (2), be installed on the end cap at cylindrical shell (2) two ends, also comprise and pass end cap and by the rotating shaft (5) of bearings in cylindrical shell (2) center, work disc group (14) is installed in the rotating shaft, between the adjacent work disc (3) blade (4) that annular pass between disc is divided into a plurality of sector channels is installed in the work disc group (14), also comprise the nozzle (1) of being located at work disc (3) side, wherein nozzle (1) inlet air flow direction and blade (4) ingress blade profile angle are the 0-15 degree; Above-mentioned rotating shaft (5) is hollow rotating shaft, and the cavity of hollow rotating shaft (5) is exit flow passage (7), and the hollow rotating shaft (5) of blade (4) root radially has air flow inlet hole (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110112912 CN102182517B (en) | 2011-05-04 | 2011-05-04 | Boundary layer turbine with blade plate |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 201110112912 CN102182517B (en) | 2011-05-04 | 2011-05-04 | Boundary layer turbine with blade plate |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN102182517A CN102182517A (en) | 2011-09-14 |
| CN102182517B true CN102182517B (en) | 2013-08-21 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 201110112912 Expired - Fee Related CN102182517B (en) | 2011-05-04 | 2011-05-04 | Boundary layer turbine with blade plate |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102729145B (en) * | 2012-06-19 | 2014-09-17 | 无锡宇吉科技有限公司 | Vane wheel |
| CN103161515B (en) * | 2013-03-14 | 2015-02-18 | 中国科学院理化技术研究所 | Airflow driving device |
| CN108331616B (en) * | 2018-04-04 | 2023-05-02 | 西安交通大学 | Wheel disc structure of disc turbine |
| CN108487940B (en) * | 2018-04-04 | 2024-04-02 | 西安交通大学 | Nozzle structure of disk turbine |
| CN113882904A (en) * | 2021-10-26 | 2022-01-04 | 范家铭 | Unsteady surface layer flow channel composite blade type turbine |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2032275U (en) * | 1988-07-12 | 1989-02-08 | 中国科学院北京真空物理实验室 | Air-extracting disk moving impeller structure |
| CN2097280U (en) * | 1991-07-20 | 1992-02-26 | 张有权 | Radial steam turbine |
| WO2001040111A1 (en) * | 1999-12-02 | 2001-06-07 | Micromachines Limited | Micromachines |
| WO2002004788A1 (en) * | 2000-07-06 | 2002-01-17 | Drysdale Kenneth William Patte | Turbine, power generation system therefor and method of power generation |
-
2011
- 2011-05-04 CN CN 201110112912 patent/CN102182517B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN2032275U (en) * | 1988-07-12 | 1989-02-08 | 中国科学院北京真空物理实验室 | Air-extracting disk moving impeller structure |
| CN2097280U (en) * | 1991-07-20 | 1992-02-26 | 张有权 | Radial steam turbine |
| WO2001040111A1 (en) * | 1999-12-02 | 2001-06-07 | Micromachines Limited | Micromachines |
| WO2002004788A1 (en) * | 2000-07-06 | 2002-01-17 | Drysdale Kenneth William Patte | Turbine, power generation system therefor and method of power generation |
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| CN102182517A (en) | 2011-09-14 |
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Granted publication date: 20130821 Termination date: 20160504 |