CN204511524U - A kind of inlet guide vane structure of turbomachine non-axisymmetric distribution - Google Patents
A kind of inlet guide vane structure of turbomachine non-axisymmetric distribution Download PDFInfo
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- CN204511524U CN204511524U CN201520153257.0U CN201520153257U CN204511524U CN 204511524 U CN204511524 U CN 204511524U CN 201520153257 U CN201520153257 U CN 201520153257U CN 204511524 U CN204511524 U CN 204511524U
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- 238000009826 distribution Methods 0.000 title claims abstract description 35
- 239000012530 fluid Substances 0.000 claims abstract description 14
- 239000000126 substance Substances 0.000 claims abstract description 11
- 230000035772 mutation Effects 0.000 claims description 4
- 238000009828 non-uniform distribution Methods 0.000 claims description 4
- 230000003068 static effect Effects 0.000 claims description 4
- 238000010276 construction Methods 0.000 claims description 3
- 238000013461 design Methods 0.000 abstract description 22
- 230000008676 import Effects 0.000 abstract description 11
- 230000000737 periodic effect Effects 0.000 abstract description 6
- 230000007812 deficiency Effects 0.000 abstract description 3
- 238000006243 chemical reaction Methods 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 4
- 238000012546 transfer Methods 0.000 description 3
- 230000000694 effects Effects 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000002485 combustion reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010205 computational analysis Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 239000007788 liquid Substances 0.000 description 1
- 238000005461 lubrication Methods 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000005457 optimization Methods 0.000 description 1
- 230000001314 paroxysmal effect Effects 0.000 description 1
- 238000012545 processing Methods 0.000 description 1
- 238000007789 sealing Methods 0.000 description 1
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Abstract
The utility model discloses a kind of inlet guide vane structure of turbomachine non-axisymmetric distribution, for with inlet guide vane and fluid working substance to be obvious stable state in import cross section non-homogeneous or the turbomachine of Periodic Unsteady distribution, this inlet guide vane is designed to non-axisymmetric distribution structure.The utility model is for the flowing state parameter distribution feature of fluid working substance in inlet guide vane import cross section, adopt non-axisymmetric distribution inlet guide vane structure, make the distribution of the status parameters such as the pressure of working medium in inlet guide vane outlet, speed, flow direction closer to design conditions, make up the deficiency that current turbomachinery design system adopts stable and uniform inlet flow state assumed condition, to improve energy conversion efficiency and the operation stability of impeller, the design for inlet guide vane adds two degrees of freedom.
Description
Technical field
The utility model relates to the turbomachine in field of fluid mechanics, the inlet guide vane structure of the non-axisymmetric distribution specifically in turbomachine.
Background technique
Very extensive as the application of the turbomachine of working medium using various fluid, structural type is also varied, for productive life provides electric power, power and various product.The working medium of the flowing in turbomachine is by the state (as pressure, temperature, speed etc.) of static stator alter, by rotate movable vane consumption or export mechanical shaft work, therefore, the height of impeller performance depends primarily on the design level of each row's blade.
In current turbomachinery design system, all suppose that flow working medium is stable, uniform state in import cross section, each row's stator and movable vane (except the support plate that structural strength or built-in pipe circuit are considered) are all axisymmetric distributions, namely circumference is uniformly distributed and geometrical shape identical (as shown in Figure 3), does not consider the circumferential difference of blade row when design, computational analysis, processing, installation.But in the application of many turbomachines, the import cross section working medium before part of generating units inlet guide vane is had to be the distribution of stable state non-homogeneous or Periodic Unsteady, such as: 1. turbosupercharger, although the two air feeder structure of some employings, reduce the nonuniformity of air inlet as much as possible, but still the working medium stable and uniform inlet flow state assumed condition adopted when not reaching design impeller, 2. ground or combustion engine peculiar to vessel are furnished with and transfer air-flow to axial air inlet volute (or collection chamber) by radial direction, particularly to air inlet volute size have strictly limit time, the uniformity of air inlet can be affected, 3. gear-box type compression or expansion unit, the general cantilever of impeller is arranged on gear shaft, and need to transfer air-flow to axial air inlet volute by radial direction, so the stability requirement of rotor dynamics then limits the axial dimension (requiring that leaf dish is close to gear-box) of spiral case, and the linear velocity of gear, centre distance between each gear shaft again limit the radial dimension of spiral case (as Fig. 1, shown in 2), the air distribution of 90 ° of turning back generally can not obtain very well by therefore size-constrained air inlet volute, the working medium of spiral case and inlet guide vane interface has obvious non-axisymmetric distribution feature, 4. aeroengine is paroxysmal import heterogeneous state due to the inlet distortion that crosswind, eddy flow, maneuver or weapon delivery cause, be not included in the utility model for problem domains.Above-mentioned, 1., 2., 3. even if three kinds of typical air inlet volute structures are through optimal design as much as possible, also still can turn back and the annular water conservancy diversion basin structure of centre due to size restrictions, air-flow, make astable, heterogeneous state that the flow field before inlet guide vane occurs in various degree always, namely other blade working in inlet guide vane and downstream is in off-design behaviour, aerodynamic loading, the flow field of different circumferential position blade, stressed, noise variance is obvious, downstream movable vane bears the impact of non-axis symmetry air-flow, thus reduces the performance of impeller and the stability of operation.
Model utility content
In order to improve the performance that fluid working substance is the turbomachine of the non-homogeneous or Periodic Unsteady distribution of obvious stable state in import cross section further, improve efficiency and the stable operation scope of impeller, the utility model discloses a kind of inlet guide vane structure of turbomachine non-axisymmetric distribution, this structure is optimized the circumference distribution of inlet guide vane and blade shape, working medium is made to flow through inlet guide vane and wheel hub, during the passage that casing forms, loss is less, discharge state is closer to design conditions, make up the deficiency that current turbomachinery design system adopts stable and uniform inlet flow state assumed condition, design for inlet guide vane adds two degrees of freedom, design more flexible, be particularly useful for all kinds of turbomachines with air inlet volute.The inlet guide vane structure of non-axisymmetric distribution of the present utility model is when designing, introduce the design concept of the inlet guide vane non-axisymmetric distribution considering the astable Uniform Flow state of working medium import, excavate the potentiality improving impeller performance and stability, the structural configuration of unit and cost are not had a significant effect, there is good application prospect.
In order to achieve the above object, technical solution of the present utility model is as follows:
A kind of inlet guide vane structure of turbomachine non-axisymmetric distribution, the movable vane that at least one row that described turbomachine comprises the static inlet guide vane of at least one row and is positioned at inlet guide vane downstream rotates, described inlet guide vane and movable vane are circumferentially, there is common axle center, it is characterized in that: described inlet guide vane is non-axisymmetric distribution structure, fluid working substance flows through from the inlet guide vane passage of turbomachine and the movable vane passage of adjacent position, downstream thereof successively.
Be the non-homogeneous or Periodic Unsteady distribution of obvious stable state in import cross section for fluid working substance, and comprise the turbomachine of at least one row's movable vane of inlet guide vane and downstream thereof, according to the flow pattern of flow working medium on the import cross section before inlet guide vane, non-axisymmetric distribution design is carried out to inlet guide vane, complete cycle flow field mainly through numerical calculation software analysis inlet guide vane completes optimization, as necessary by experimental technique checking design proposal.
Preferably, in the inlet guide vane structure of turbomachine non-axisymmetric distribution of the present utility model, each described inlet guide vane circumference non-uniform Distribution, each stator interval is uneven, but the geometrical shape of each described inlet guide vane, established angle are all identical.
Preferably, in the inlet guide vane structure of turbomachine non-axisymmetric distribution of the present utility model, each described inlet guide vane circumference is uniformly distributed, but the geometrical shape of inlet guide vane, established angle are incomplete same.
Preferably, in the inlet guide vane structure of turbomachine non-axisymmetric distribution of the present utility model, each described inlet guide vane circumference nonuniform mutation operator, and the geometrical shape of inlet guide vane, established angle are also incomplete same.
Preferably, the difference of described inlet guide vane geometrical shape is embodied in the incomplete same of blade shape construction parameter.Preferably, described blade shape construction parameter is entrance geometry angle, outlet geometry angle, leading-edge radius, trailing edge radius, thickness distribution, wheel hub molded line, casing molded line or blade stacking line.
For the inlet guide vane of described non-axisymmetric distribution, the parameter such as throat area, denseness, Flow Field Distribution of circumferential different runner may be incomplete same, but object is all for downstream movable vane provides more suitably entry condition.
Preferably, the number of described inlet guide vane be greater than 1 and be less than 300 integer.
Preferably, described turbomachine is the compressor of single-stage or multilevel hierarchy, pump or decompressor.
Preferably, the rotary blade of described turbomachine is radial-flow type, mixed-flow or axial flow.
Preferably, described fluid working substance is gas, liquid or heterogeneous fluid.
Advantage of the present utility model and beneficial effect are:
1. the potentiality that fluid working substance is the turbomachine inlet guide vane optimal design of obvious stable state non-homogeneous or Periodic Unsteady distribution in import cross section have been excavated further, propose non-axis symmetry inlet guide vane structure, make up the deficiency that current turbomachinery design system adopts stable and uniform inlet flow state assumed condition, when not having a significant effect to unit existing structure and cost, improve the performance of unit and the stability of operation, be applicable to the turbomachine of various structure type, flow working medium;
2. in actual applications, three kinds of described non-axis symmetry inlet guide vane structures can be chosen flexibly according to design accuracy, cost, assembling difficulty etc.
Accompanying drawing explanation
Fig. 1 is the gear-box type axial flow turbine threedimensional model schematic diagram of application of the present utility model with air inlet volute;
Fig. 2 is the cross section structure schematic diagram of the gear-box type axial flow turbine with air inlet volute;
Fig. 3 is the axisymmetric distributed architecture that prior art turbomachinery design adopts, and wherein, A is floor map, and B is perspective view;
Fig. 4 is non-axis symmetry inlet guide vane structure of the present utility model, blade circumference non-uniform Distribution, and geometrical shape, the established angle of each inlet guide vane are all identical, and wherein, A is floor map, and B is perspective view;
Fig. 5 is non-axis symmetry inlet guide vane structure of the present utility model, and blade circumference is evenly arranged, but the geometrical shape of inlet guide vane, established angle are incomplete same, and wherein, A is floor map, and B is perspective view;
Fig. 6 is non-axis symmetry inlet guide vane structure of the present utility model, blade circumference nonuniform mutation operator, and the geometrical shape of inlet guide vane, established angle are also incomplete same, and wherein, A is floor map, and B is perspective view;
Fig. 7 is non-axis symmetry inlet guide vane structure of the present utility model, the schematic diagram that each inlet guide vane established angle is incomplete same, and wherein, A is schematic perspective view, and B is floor map.
Embodiment
For making the purpose of this utility model, technological scheme and advantage clearly understand, to develop simultaneously embodiment referring to accompanying drawing, the utility model is further described.It should be noted that, the following stated is only preferred embodiment of the present utility model, does not therefore limit protection domain of the present utility model.
As shown in Figure 1, of the present utility modelly be applied in the non-axis symmetry inlet guide vane structure in the gear-box type axial flow turbine of air inlet volute, comprise air inlet volute 4, the movable vane 6 that the one static inlet guide vane 5 of row and at least one row in downstream thereof rotate, each movable vane 6 is arranged on wheel disc 7, and ensure the rotor that described turbomachine runs well, lubrication, sealing, support, fastening, measure, the component such as control, the flow working medium entering turbine from air inlet volute 4 flows through from the movable vane passage of inlet guide vane passage and adjacent position, downstream thereof successively, status parameter changes, drive turbine does work, by being arranged on, gear on gear shaft 3, reaches the object absorbing or export mechanical shaft work.
Fig. 2 is the axial flow turbine with air inlet volute 4 and speed-change gear box 1, air inlet volute 4 makes fluid working substance transfer axis to by radial direction, fluid working substance enters axial flow turbine through volute outlet 8, then successively through the movable vane 6 be arranged on wheel disc 7 of inlet guide vane 5 and adjacent position, downstream thereof, present non-axis symmetry state in various degree, make inlet guide vane 5 majority be operated in off-design behaviour.
Fig. 3 for prior art design adopt axisymmetric distributed architecture, Fig. 4-6 gives three kinds of structures of inlet guide vane non-axisymmetric distribution; Fig. 4 is blade of the present utility model circumference non-uniform Distribution, and the blade pitgh of different circumferential position is different, but the geometrical shape of each inlet guide vane, established angle are all identical; Fig. 5 is of the present utility modelly evenly arranged for blade circumference, but the geometrical shape of inlet guide vane, established angle are incomplete same, the blade stacking line difference (difference of prismatic blade and bent blades) of different circumferential position; Fig. 6 is blade of the present utility model circumference nonuniform mutation operator, and the geometrical shape of inlet guide vane, established angle are also incomplete same, structural rate Fig. 4,5 more complicated.Fig. 7 is the incomplete same schematic diagram of inlet guide vane established angle, and the difference of established angle can make the channel size of different circumferential position also different, to reach the object optimizing Flow Field Distribution.
The utility model embodiment is applicable to inlet guide vane, fluid working substance be the turbomachine of the non-homogeneous or Periodic Unsteady distribution of obvious stable state in import cross section, especially with the unit of air inlet volute.
By above-described embodiment, achieve the purpose of this utility model completely effectively.Person skilled in art is appreciated that the utility model includes but not limited to the content described in accompanying drawing and above embodiment.Although the utility model just thinks the most practical at present and preferred embodiment is described, but should know, the utility model is not limited to the disclosed embodiments, and any amendment not departing from function and structure principle of the present utility model all will comprise within the scope of the appended claims.
Claims (8)
1. the inlet guide vane structure of a turbomachine non-axisymmetric distribution, the movable vane that at least one row that described turbomachine comprises the static inlet guide vane of at least one row and is positioned at inlet guide vane downstream rotates, described inlet guide vane and movable vane are circumferentially, there is common axle center, it is characterized in that: described inlet guide vane is non-axisymmetric distribution structure, fluid working substance flows through from the inlet guide vane passage of turbomachine and the movable vane passage of adjacent position, downstream thereof successively.
2. inlet guide vane structure according to claim 1, is characterized in that, described turbomachine is the compressor of single-stage or multilevel hierarchy, pump or decompressor.
3. inlet guide vane structure according to claim 1, is characterized in that, the rotary blade of described turbomachine is radial-flow type, mixed-flow or axial flow.
4. inlet guide vane structure according to claim 1, is characterized in that, described inlet guide vane circumference non-uniform Distribution, each stator interval is uneven, but the geometrical shape of each described inlet guide vane, established angle are all identical.
5. inlet guide vane structure according to claim 1, is characterized in that, each described inlet guide vane circumference is uniformly distributed, but the geometrical shape of inlet guide vane, established angle are incomplete same.
6. inlet guide vane structure according to claim 1, is characterized in that, each described inlet guide vane circumference nonuniform mutation operator, and the geometrical shape of inlet guide vane, established angle are also incomplete same.
7. the inlet guide vane structure according to any one of claim 4 to 6, it is characterized in that, the difference of each described inlet guide vane geometrical shape is embodied in the incomplete same of the modeling parameters of blade, and described blade shape construction parameter is entrance geometry angle, outlet geometry angle, leading-edge radius, trailing edge radius, thickness distribution, wheel hub molded line, casing molded line or blade stacking line.
8. inlet guide vane structure according to claim 1, is characterized in that, the number of inlet guide vane be greater than 1 and be less than 300 integer.
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108194424A (en) * | 2017-11-22 | 2018-06-22 | 中国北方发动机研究所(天津) | A kind of vane type treated casing device based on compressor volute asymmetry |
| CN109209524A (en) * | 2018-10-19 | 2019-01-15 | 中国科学院工程热物理研究所 | A kind of combined nozzle gas distribution structure suitable for CAES system high pressure expansion machine |
| CN111502891A (en) * | 2020-04-28 | 2020-08-07 | 合肥华升泵阀股份有限公司 | Hydraulic turbine impeller and working method thereof |
| CN113123834A (en) * | 2021-06-17 | 2021-07-16 | 中国航发上海商用航空发动机制造有限责任公司 | Blade subassembly and engine of engine |
| CN113944654A (en) * | 2021-11-26 | 2022-01-18 | 中国北方发动机研究所(天津) | Wide-flow volute structure |
-
2015
- 2015-03-18 CN CN201520153257.0U patent/CN204511524U/en active Active
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108194424A (en) * | 2017-11-22 | 2018-06-22 | 中国北方发动机研究所(天津) | A kind of vane type treated casing device based on compressor volute asymmetry |
| CN108194424B (en) * | 2017-11-22 | 2020-05-08 | 中国北方发动机研究所(天津) | Vane type casing processing device based on compressor volute asymmetry |
| CN109209524A (en) * | 2018-10-19 | 2019-01-15 | 中国科学院工程热物理研究所 | A kind of combined nozzle gas distribution structure suitable for CAES system high pressure expansion machine |
| CN111502891A (en) * | 2020-04-28 | 2020-08-07 | 合肥华升泵阀股份有限公司 | Hydraulic turbine impeller and working method thereof |
| CN113123834A (en) * | 2021-06-17 | 2021-07-16 | 中国航发上海商用航空发动机制造有限责任公司 | Blade subassembly and engine of engine |
| CN113944654A (en) * | 2021-11-26 | 2022-01-18 | 中国北方发动机研究所(天津) | Wide-flow volute structure |
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| C14 | Grant of patent or utility model | ||
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Effective date of registration: 20190117 Address after: 100185 No. 301-63, No. 3, Building A 1, Eastern District of Qinghe Jiayuan, Haidian District, Beijing Patentee after: ZHONGCHU GUONENG (BEIJING) TECHNOLOGY Co.,Ltd. Address before: 100190 North four Ring West Road, Haidian District, Beijing, A202 Patentee before: Institute of Engineering Thermophysics, Chinese Academy of Sciences |
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Effective date of registration: 20231024 Address after: No. 603, Floor 6, Building 2, Yard 2, Yongjie South Road, Haidian District, Beijing 100094 Patentee after: Huake Super Energy (Beijing) Energy Technology Co.,Ltd. Address before: 100185 No. 301-63, No. 3, Building A 1, Eastern District of Qinghe Jiayuan, Haidian District, Beijing Patentee before: ZHONGCHU GUONENG (BEIJING) TECHNOLOGY Co.,Ltd. |
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| TR01 | Transfer of patent right |