CN109268077A - The flow losses control method of blade boundary-layer fluid - Google Patents
The flow losses control method of blade boundary-layer fluid Download PDFInfo
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- CN109268077A CN109268077A CN201811006975.XA CN201811006975A CN109268077A CN 109268077 A CN109268077 A CN 109268077A CN 201811006975 A CN201811006975 A CN 201811006975A CN 109268077 A CN109268077 A CN 109268077A
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- Prior art keywords
- boundary
- blade
- layer fluid
- flow losses
- control method
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D15/00—Control, e.g. regulation, of pumps, pumping installations or systems
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/02—Surge control
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The embodiment of the present invention provides a kind of flow losses control method of blade boundary-layer fluid, comprising the following steps: S1. classifies to the movement of the boundary-layer fluid of blade;S2. according to the type of the movement of boundary-layer fluid, the influence factor of the flow losses of boundary-layer fluid is obtained;S3. it is taken appropriate measures according to the influence factor of the flow losses of boundary-layer fluid to reduce flow losses.The present invention is classified by the movement to boundary-layer fluid, is moved to different types of boundary-layer and is used different control methods, versatility is good, and practical, control effect is obvious.
Description
Technical field
The present invention relates to turbomachine field more particularly to a kind of flow losses control methods of blade boundary-layer fluid.
Background technique
Turbomachine is widely used in industrial circle, such as aero-engine, ground gas turbine, steam turbine and mine
Well ventilation and pipeline transportation etc., reduce blade interior flow losses has for reducing energy loss and improving impeller mechanical efficiency
Important function.However, generally requiring to take difference according to different flow field situations during reducing flow losses at present
Control method, lack a kind of guiding method that is general, quickly reducing flow losses.
Summary of the invention
In order to overcome at least one aspect of the above problem, the embodiment of the present invention provides a kind of stream of blade boundary-layer fluid
Dynamic damage control method, versatility is good, and practical, control effect is obvious.
According to an aspect of the present invention, a kind of flow losses control method of blade boundary-layer fluid is provided, including with
Lower step: S1. classifies to the movement of the boundary-layer fluid of blade;S2. it according to the type of the movement of boundary-layer fluid, obtains
The influence factor of the flow losses of boundary-layer fluid;S3. it is taken accordingly according to the influence factor of the flow losses of boundary-layer fluid
Measure reduce flow losses.
According to some embodiments, in step sl according in the movement of the boundary-layer fluid of blade whether there is defiber come
Classify to the movement of boundary-layer fluid.
According to some embodiments, the wall surface flow pattern generated according to the flowing by the boundary-layer fluid of blade to determine whether
There are defibers.
According to some embodiments, the movement of the boundary-layer fluid of blade is divided into there is no the attached of defiber in step sl
Vortex sheet migration and since defiber free vortex sheet migration.
Pass through shape in the case where the movement of the boundary-layer fluid of blade is attachment vortex sheet migration according to some embodiments
It is distributed at more preferably pressure to reduce flow losses.
According to some embodiments, forming more preferably pressure distribution includes carrying out positive crook reason to the blade of small angle tower leaf grating.
According to some embodiments, in the case where the movement of the boundary-layer fluid of blade is that free vortex sheet migrates, by subtracting
Less or change vortex distribution to reduce flow losses.
According to some embodiments, reducing or changing vortex distribution includes carrying out recurvation processing to large turning angle cascade blade.
Compared with prior art, the present invention at least has the advantages that the present invention classifies boundary-layer fluid motion,
Different control methods are used to different flow field situations, have versatility good, practical, control effect clear advantage.
Detailed description of the invention
By the description made for the present invention of below with reference to attached drawing, other objects and advantages of the present invention will be aobvious and easy
See, and can help that complete understanding of the invention will be obtained.
Fig. 1 is the work flow diagram of the flow losses control method of blade boundary-layer fluid according to an embodiment of the present invention;
Fig. 2 is the separation flow pattern two-dimensional section figure of blade boundary-layer according to an embodiment of the present invention;
Fig. 3 is the stereoscopic schematic diagram of blade according to an embodiment of the present invention, wherein (a) is positively curved blade schematic diagram, (b) is
Recurvation blade schematic diagram (c) is prismatic blade schematic diagram;
Fig. 4 is small angle tower positively curved blade " C " type pressure-plotting according to an embodiment of the present invention;
Fig. 5 a is the free vortex sheet migration of the boundary-layer according to an embodiment of the present invention using big corner prismatic blade before recurvation
The vortex schematic diagram of formation;
Fig. 5 b is the free vortex sheet migration shape of the boundary-layer according to an embodiment of the present invention using the big corner blade after recurvation
At vortex schematic diagram.
Specific embodiment
In order to make the object, technical scheme and advantages of the embodiment of the invention clearer, below in conjunction with the embodiment of the present invention
In attached drawing, technical scheme in the embodiment of the invention is clearly and completely described, it is clear that described embodiment is
A part of the embodiment of the present invention, instead of all the embodiments.Based on method and embodiment proposed by the invention, this field is general
Logical technical staff without making creative work, utilizes method every other reality obtained proposed by the invention
Example is applied, shall fall within the protection scope of the present invention.
The term used in embodiments of the present invention is only to be not intended to be limiting merely for for the purpose of describing particular embodiments
The present invention.Unless otherwise defined, the technical term or scientific term that the present invention uses should be tool in fields of the present invention
The ordinary meaning for thering is the personage of general technical ability to be understood.
The present invention provides a kind of flow losses control method of blade boundary-layer fluid, and versatility is good, practical, control
Effect is obvious.
The embodiment of the present invention is further described with reference to the accompanying drawing.
Fig. 1 is the work flow diagram of the flow losses control method of blade boundary-layer fluid according to an embodiment of the present invention.
As shown in Figure 1, the flow losses control method of blade boundary-layer fluid includes the following steps:
S1. classify to the movement of the boundary-layer fluid of blade.
It, can be in the surface of solids when water, air or other viscous fluids are flowed along the surface of solids or solid moves in a fluid
One layer of low velocity fluid is formed, this layer fluid is boundary-layer.The movement of boundary-layer can leave wall surface flow pattern in wall surface, when flowing
When dynamic separation, it will appear defiber in wall surface flow pattern.Fig. 2 is the separation flow pattern two of blade boundary-layer according to an embodiment of the present invention
Tie up schematic diagram.As shown in Fig. 2, fluid is flowed along arrow direction, fluid along wall surface when flowing, due to viscous friction, pressure
Force gradient etc. influences, and the boundary-layer fluid dynamic energy near wall has very big loss, therefore, at certain point O by near wall
Fluid stop flowing so that the phenomenon that refluence occurs in the fluid inside boundary-layer after O point, O point is known as burble point.
According to preferred embodiment, being formed by wall surface flow pattern according to the movement of the boundary-layer fluid of blade whether there is
Defiber classifies to the movement of boundary-layer fluid.Defiber can directly be observed to obtain, and there are defibers to be shown to be certainly
It is migrated by vortex sheet;There is no defibers to be shown to be attachment vortex sheet migration.
According to preferred embodiment, the movement of the boundary-layer fluid of blade is divided into there is no defibers in step sl
Adhere to vortex sheet migration and the free vortex sheet migration since defiber.Attachment vortex sheet refers to the boundary-layer fluid developed along wall surface;
Free vortex sheet fingering enters the swirling fluid into flow field.When not having defiber, the movement of boundary-layer is attachment vortex sheet;When having point
When offline, since defiber, the movement of boundary-layer is changed from attachment vortex sheet to free vortex sheet.
S2. according to the type of the movement of the boundary-layer fluid, the influence factor of the flow losses of boundary-layer fluid is obtained.
The expression formula of fluid momentum equation are as follows:
Wherein the equation left side is momentum principle,For body force suffered by fluid,For pressure gradient term,
For viscosity term.The momentum principle of boundary-layer fluid is determined by two critical quantities known to fluid momentum equation: barometric gradient
And viscosity.
When not having defiber in wall surface flow pattern, boundary-layer is close to wall surface movement always, that is, attachment vortex sheet migration occurs, this
When flow losses are mainly influenced by barometric gradient;When there is defiber in wall surface flow pattern, boundary-layer passes through wall surface flow pattern
Defiber leave wall surface, form free vortex sheet, that is, free vortex sheet occur and migrates, at this time mainly by viscosity, i.e. vortex influences
Flow losses.
S3. it is taken appropriate measures according to the influence factor of the flow losses of the boundary-layer fluid to reduce flowing damage
It loses.
In the case where the movement of the boundary-layer fluid of blade is attachment vortex sheet migration, it is distributed by forming more preferably pressure
To reduce flow losses.According to preferred embodiment, forming more preferably pressure distribution includes carrying out to the blade of small angle tower leaf grating
Positive crook reason.Fig. 3 is the stereoscopic schematic diagram of blade.As shown in figure 3, (c) being prismatic blade, (a) is positively curved blade, (b) is recurvation
Blade.Positively curved blade can control the attachment vortex sheet flowing of blade surface, improve the aeroperformance of leaf grating.In prismatic blade runner
It is interior, the main integrated distribution of boundary-layer fluid of low speed near end walls with end wall/suction surface angular region, end wall nearby and end wall/
The flow losses of suction surface angular region are big, and Fig. 4 is that small angle tower positively curved blade according to an embodiment of the present invention is formed by along blade height
" C " the type pressure-plotting in direction is spent, as shown in figure 4, foring quiet along " C " type that leaf exhibition pressure at two ends is high, intermediate pressure is low
Pressure distribution is distributed to form more preferably pressure, and driving blade root boundary-layer moves to middle part of blade, to significantly reduce end
Wall nearby and end wall/suction surface angular region flow losses.
In the case where the movement of the boundary-layer fluid of blade is that free vortex sheet migrates, by reducing or changing vortex distribution
To reduce flow losses.According to preferred embodiment, reducing or changing vortex distribution includes carrying out instead to large turning angle cascade blade
Crook reason.Exist in the blade suction surface flow pattern of big corner (such as 60 ° of compressor blade, 120 ° of turbo blade) leaf grating a large amount of
Defiber, fluid can generate vortex at defiber, and therefore, flowing is leading with the migration of free vortex sheet.By using recurvation leaf
Piece reduces vortex intensity and range, or changes the distribution and positional relationship between vortex, to reduce the viscosity between vortex
Mixing loss.Fig. 5 a and 5b are the vortex distribution maps before and after the recurvation blade according to an embodiment of the present invention using big corner.Such as figure
Shown in 5a and 5b, PV is Passage Vortex, TV is trailing edge whirlpool, SV is secondary vortices, CV is wall angle whirlpool.It, can be obvious from Fig. 5 a to Fig. 5 b
It was found that Passage Vortex obviously becomes smaller with trailing edge whirlpool coverage by using recurvation blade, secondary vortices disappear, therefore, viscosity blending
Loss reduces.
The present invention provides a kind of flow losses control methods of blade boundary-layer fluid, by two keys in the equation of momentum
Barometric gradient and viscosity are measured, to determine the development of boundary-layer fluid.On this basis, the present invention is by boundary-layer fluid motion to have
No defiber is to use different control methods according to classifying to different flow field situations, have versatility good, practical,
Control effect clear advantage.
Finally, it should be noted that the above embodiments are merely illustrative of the technical solutions of the present invention, rather than its limitations;Although
Present invention has been described in detail with reference to the aforementioned embodiments, those skilled in the art should understand that: it still may be used
To modify the technical solutions described in the foregoing embodiments or equivalent replacement of some of the technical features;
And these are modified or replaceed, technical solution of various embodiments of the present invention that it does not separate the essence of the corresponding technical solution spirit and
Range.
Claims (8)
1. a kind of flow losses control method of blade boundary-layer fluid, comprising the following steps:
S1. classify to the movement of the boundary-layer fluid of blade;
S2. according to the type of the movement of the boundary-layer fluid, the influence factor of the flow losses of boundary-layer fluid is obtained;
S3. it is taken appropriate measures according to the influence factor of the flow losses of the boundary-layer fluid to reduce flow losses.
2. the flow losses control method of blade boundary-layer fluid according to claim 1, which is characterized in that in step S1
It is middle to classify according to whether there is defiber in the movement of the boundary-layer fluid of blade to the movement of boundary-layer fluid.
3. the flow losses control method of blade boundary-layer fluid according to claim 2, which is characterized in that according to by leaf
The flowing of the boundary-layer fluid of piece and the wall surface flow pattern generated are to determine whether there are defibers.
4. according to right want 2 or 3 described in blade boundary-layer fluid flow losses control method, which is characterized in that in step
The movement of the boundary-layer fluid of blade is divided into wall surface flow pattern there is no the migration of the attachment vortex sheet of defiber and from wall surface stream in S1
The free vortex sheet migration that defiber starts in spectrum.
5. according to right want 4 described in blade boundary-layer fluid flow losses control method, which is characterized in that in the attached of blade
In the case that the movement of surface layer fluid is attachment vortex sheet migration, flow losses are reduced by forming more preferably pressure distribution.
6. according to right want 5 described in blade boundary-layer fluid flow losses control method, which is characterized in that it is described formation more
Good pressure distribution includes carrying out positive crook reason to the blade of small angle tower leaf grating.
7. according to right want 4 described in blade boundary-layer fluid flow losses control method, which is characterized in that in the attached of blade
In the case that the movement of surface layer fluid is the migration of free vortex sheet, flow losses are reduced by reducing or changing vortex distribution.
8. the flow losses control method of blade boundary-layer fluid according to claim 7, which is characterized in that it is described reduction or
Changing vortex distribution includes carrying out recurvation processing to large turning angle cascade blade.
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Citations (3)
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---|---|---|---|---|
CN101666343A (en) * | 2008-09-03 | 2010-03-10 | 中国科学院工程热物理研究所 | Control system and control method for plasma excitation for cascade internal flow |
KR20160047715A (en) * | 2014-10-23 | 2016-05-03 | 한국에너지기술연구원 | Mixed flow impeller having hollow airfoil blades |
CN107366634A (en) * | 2017-08-17 | 2017-11-21 | 西北工业大学 | A kind of compressor blade row loss calculation method |
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2018
- 2018-08-30 CN CN201811006975.XA patent/CN109268077B/en active Active
Patent Citations (3)
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---|---|---|---|---|
CN101666343A (en) * | 2008-09-03 | 2010-03-10 | 中国科学院工程热物理研究所 | Control system and control method for plasma excitation for cascade internal flow |
KR20160047715A (en) * | 2014-10-23 | 2016-05-03 | 한국에너지기술연구원 | Mixed flow impeller having hollow airfoil blades |
CN107366634A (en) * | 2017-08-17 | 2017-11-21 | 西北工业大学 | A kind of compressor blade row loss calculation method |
Non-Patent Citations (1)
Title |
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王秀卓: "叶轮机械叶片气动优化设计方法的研究", 《中国优秀硕士学位论文全文数据库 工程科技Ⅱ辑》 * |
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