CN107366634B - A kind of compressor blade row loss calculation method - Google Patents
A kind of compressor blade row loss calculation method Download PDFInfo
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- CN107366634B CN107366634B CN201710705044.8A CN201710705044A CN107366634B CN 107366634 B CN107366634 B CN 107366634B CN 201710705044 A CN201710705044 A CN 201710705044A CN 107366634 B CN107366634 B CN 107366634B
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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
- F04D27/00—Control, e.g. regulation, of pumps, pumping installations or pumping systems specially adapted for elastic fluids
- F04D27/001—Testing thereof; Determination or simulation of flow characteristics; Stall or surge detection, e.g. condition monitoring
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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
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/28—Rotors specially for elastic fluids for centrifugal or helico-centrifugal pumps for radial-flow or helico-centrifugal pumps
- F04D29/30—Vanes
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- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses a kind of compressor blade row loss calculation methods, the compressor blade row loss appraisal method proposed through the invention, it can substantially judge to calculate in compressor blade row since the size and proportion of all kinds of losses such as consumption and boundary-layer friction are rolled into a ball in various whirlpools, it can be used for judging that the main loss source in compressor blade row is, to provide theoretical direction to the flow mechanism assurance in compressor and the flowing control in the compressor blade row in later period.
Description
Technical field
The invention belongs to turbine fields, and in particular to a kind of compressor blade row loss calculation method.
Background technique
In compressor blade row, since the low speed of the pressure difference and end wall fluid in blade pressure surface and adjacent suction face is special
Property, therefore strong lateral flow can be generated at end wall.In addition the wall surface of the induction of leading edge horse shoe vortex and end wall angular region complexity
Thus shear effect causes the Passage Vortex in channel to continue to develop and grows, and generates apparent defiber in blade suction surface, lure
Concentrated shed vortex is generated, thus leads to low regime in the accumulation of angular region and then expands to entire leaf exhibition section.Especially attacking greatly
In the case where angle, Passage Vortex coverage is wider, and low regime accumulation is even more serious, thus generates serious corner separation phenomenon.
Biggish energy consumption is resulted in because of the mutual shearing between viscous vortex group, apparent loss concentration zones occurs.Meanwhile the angle
Area's segregation phenomenon can not only be such that leaf grating efficiency declines, and the stall event of whole grade compressor can also be induced due to corner separation, in turn
Lead to surge problems.Therefore, in order to design the efficient compressor of high-performance, it is necessary to the damage of the corner separation in leaf grating
It loses expansion correlative study and is controlled.
Currently, the method for being also concentrated mainly on the loss coefficient loss based on stagnation pressure to the assessment of leaf grating angular region.Wherein
Loss is defined as follows formula：
Pt in formula, p respectively indicate stagnation pressure and static pressure, and Loss is with static pressure in the middle part of the exhibition of import leaf and dynamic pressure for referring to progress structure
It makes, i.e. subscript in, m indicates the data that exhibition position is set in import leaf.
Current universal method be to extend by the loss cloud charts or loss in certain section to circumferential average data
To characterize the loss size in channel, it is believed that the small place loss of loss absolute value is small.But this method is there are two drawbacks,
One, the continuous accumulation of loss is shown as by the loss that stagnation pressure is estimated, i.e. air-flow constantly flows through entire leaf grating by leaf grating import
The loss size that process generates in total is entirely flowed through at this until flowing through measurement point, and can not be with regard to certain elementary volume, volume element situation table
It levies in the unit and loses size as caused by air-flow stickiness.Second, this method can only probably characterize the size cases of loss,
But due to mainly there is Passage Vortex in compressor blade row channel, angle whirlpool, the vortex structures such as concentrated shed vortex and tail Low Energy Region, and
Loss is also concentrated mainly on certain several region, and simple loss coefficient method can not be by loss and the vortex structures phase in channel
In conjunction with.Therefore, it is necessary to be improved to existing cascade loss analysis method.
Summary of the invention
Present invention solves the technical problem that being：Present invention aims at solve current compressor blade row internal loss analysis method
Incomplete status, therefore, it is proposed to which a kind of compressor blade row for carrying out volume point to different zones based on dissipative function loses
Analysis method, in this way, the loss size in each region in space can be accurately calculated, meanwhile, the whirlpool in this method and compressor
Architecture combines, and can accurately calculate and distinguish in runner such as Passage Vortex, angle whirlpool and near wall shear action region etc.
The loss size of different zones.In addition, this method is different from the conventional method based on pitot loss, this method is directly based upon consumption
Function is dissipated, loss size is only and the deformation at the position is related with shearing power, and the problem of loss is accumulated may be not present.
The technical scheme is that：A kind of compressor blade row loss calculation method, includes the following steps：
Step 1：It is leaf grating leading edge, region of the terminal between 40% chord length after leaf grating trailing edge, according to axial whirlpool to starting point
Amount positive and negative, each defiber and attachment line position and wall surface distance carry out vorticity field region division, be respectively divided into Passage Vortex region,
Suction/pressure face angle whirlpool region, concentrated shed vortex region, trailing edge Shedding Vortex region, near wall friction loss region and other regions,
Definition of Division is as follows：
Passage Vortex region：In entire channel, close to end wall, axial vorticity is negative, and opening up to height is end wall to channel
Between the defiber of whirlpool；
Near wall friction loss region：At end wall, blade suction surface leans on blade pressure surface at the near wall position
At near wall position, wall surface is millimeter magnitude apart from size, and axis vorticity is positive；
Suction/pressure face angle whirlpool region：Positioned at/the intersection of pressure face and end wall is inhaled in blade, axial vorticity is positive；Zhan Xiang
Height is end wall between the defiber of angle whirlpool, and circumferential zones are blade root between the attached wire of angle whirlpool；
Trailing edge Shedding Vortex region：Positioned at the tail area after trailing edge, open up to position between concentrated shed vortex and angle whirlpool
The region that is positive of axial vorticity；
Concentrated shed vortex region：In leaf grating leading edge to tail edge area, after the defiber of blade suction surface, direction is opened up in leaf
Upper to be located on Passage Vortex close to leaf central part point, axial vorticity performance is positive；
Other regions：In addition to above description region from 40% chord length position after blade inlet edge to trailing edge
The region set；
Step 2：Loss integral is carried out to the region divided in step 1：The body of corresponding region is carried out to dissipative function
Integral, calculates the loss size in each region, to obtain loss caused by each vortex structure.
Invention effect
The technical effects of the invention are that：The compressor blade row loss appraisal method proposed through the invention, Ke Yi great
Judgement is caused to calculate in compressor blade row since the size of all kinds of losses such as consumption and boundary-layer friction and shared is rolled into a ball in various whirlpools
Ratio can be used for judging that the main loss source in compressor blade row is, to hold to the flow mechanism in compressor
And the flowing control in the compressor blade row in later period provides theoretical direction.
Detailed description of the invention
40% chord positions LOSS is distributed isogram after Fig. 1 leaf grating trailing edge
20% chord positions axial direction Vorticity Distribution isogram of Fig. 2 leaf grating leading edge and subregion schematic diagram
50% chord positions axial direction Vorticity Distribution isogram of Fig. 3 leaf grating leading edge and subregion schematic diagram
20% chord positions axial direction Vorticity Distribution isogram and subregion schematic diagram after Fig. 4 leaf grating trailing edge
Description of symbols：
To Fig. 1：A- compressor blade row blade B- compressor blade row wheel hub C- blade inlet edge D- blade trailing edge E- blade trailing edge
40% axial position section afterwards
To Fig. 2-4：The suction face angle whirlpool the 1- region pressure face angle whirlpool 2- region 3- proximal end wall friction loss region 4- closely inhales
Power face friction loss region 5- nearly pressure face friction loss region 6- Passage Vortex region 7- concentrated shed vortex region 8- trailing edge
Shedding Vortex region 9- vorticity compensating basin 10- is other
Region
Specific embodiment
Firstly the need of explanation, dissipative functionIt is defined as：
In formula, μ refers to dynamic viscosity,Indicate viGradient of the velocity component on the direction j on direction, such asIt indicates
Velocity component vxGradient magnitude in y-direction
By Euler's method, certain minute cells in convection current field areas calculate the size of its dissipative function, can obtain
Since minute cells deformation is flexible, size is lost caused by the stickiness factor such as shear-deformable.Meanwhile by dissipative function pair
Space specific region is integrated, then can calculate in the region and lose size as caused by viscosity of fluid.So, it presses
It is divided according to the different convection current field areas of loss type, and volume point is carried out with dissipative function to the region, can be distinguished
And obtain in flow field and lose size caused by different zones and different loss types, by the ratio that different zones are lost with size
Compared with, the main loss source in flow field can be obtained, for subsequent Cascade Flow situation and flow control mechanism announcement mention
For theoretical basis.So, how the difficult point of problem divides cascade flow field region if being just converted into.
Past research have shown that the loss in compressor blade row channel is mainly the friction loss area and channel of near wall
The secondary flow loss that strong shearing in interior difference vortex structure generates, therefore, present invention is generally directed in compressor blade row
Vortex structure feature divides leaf grating flow passage area.The flow field regions that the present invention is considered are that leaf grating leading edge starts to trailing edge
At 40% chord positions.Because the forefoot area of leaf grating leading edge is steady flow segment, loss is smaller, and the blending of 40% rear region flow field is tight
Heavy, each vortex system can not be identified preferably, so, the present invention only considers the flow field regions of 40% chord length after leaf grating leading edge to trailing edge.
Compressor blade row vortex structure model common at present thinks mainly to include leading edge horse shoe vortex in compressor blade row, leads to
Road whirlpool, suction/pressure face angle whirlpool, blade surface concentrated shed vortex, trailing edge Shedding Vortex.In view of horse shoe vortex only influences leaf grating leading edge
Region, vortex structure is smaller, therefore, the influence of horse shoe vortex is ignored in the division to whirlpool influence area, i.e., mainly with regard to Passage Vortex,
Suction/pressure face angle whirlpool, blade surface concentrated shed vortex and trailing edge Shedding Vortex these types vortex structure, leaf grating runner are divided into above-mentioned
Several whirlpool influence areas and other regions in addition to this.Simultaneously as the near wall area of leaf grating wheel hub and blade near wall
There is also biggish friction losses in domain, therefore are also required to its is independent.Finally, flow field regions are divided into following several pieces：
Passage Vortex region, suction/pressure face angle whirlpool region, concentrated shed vortex region, trailing edge Shedding Vortex region, near wall friction loss region
And other regions.The criterion that each region is distinguished in judgement mainly has：Positive and negative, each defiber and the attachment line position of axial vorticity, wall
Identity distance from.The characteristics of its each region, is as follows；
1. Passage Vortex region：In entire channel, close to end wall side, coverage is most wide, and axial vorticity is negative, exhibition
Can substantially it be judged by the Passage Vortex defiber on suction surface to position.About the defiber and hereafter related introduction of attached wire,
Which is not described herein again, can with reference to Alexander Hergt pertinent literature (Heydorn A, et al.Effects of Vortex Generator Application on the Performance of
a Compressor Cascade[J].Journal of Turbomachinery,2012,135(2):021026.)
2. near wall friction loss region：Pressure face is inhaled positioned at end wall and blade and leans near wall position, and wall surface distance is
Millimeter magnitude can be used restraint by wall surface distance, and axis vorticity is positive.Therefore, it is considered herein that wall surface distance is less than centainly
The region that value and vorticity are positive is boundary-layer region.(except the region of angle whirlpool)
3. suction/pressure face angle whirlpool region：In leaf grating leading edge to tail edge area, it is confined to the friendship of blade suction/pressure face and end wall
At boundary, until being always existed in 40% chord length after trailing edge since the leaf grating leading edge.It is opened up can be by suction/pressure face to upper height limit
Judge close to the defiber of tail edge area, and the influence distance at end wall can also be judged by the attached wire on end wall.Axial whirlpool
Amount is positive.After leaf grating trailing edge to trailing edge in 40% chord region, due to losing the constraint of blade wall surface, impact position is had
Changed, but is changed small.Due in leaf grating leading edge to tail edge area angle whirlpool region and boundary-layer region have overlapping, so at this
Region can ignore the influence of boundary-layer, be divided into angle whirlpool region.Therefore, it is considered herein that after leaf grating angular region and trailing edge
The region that axial vorticity is positive in the extended segment of angular region is suction/pressure face angular region region.
4. concentrated shed vortex region：In leaf grating leading edge to tail edge area, after the defiber of blade suction surface, in Ye Zhanfang
Upwards close to leaf central part point, it is located on Passage Vortex, axial vorticity performance is positive.The 40% chord length area after leaf grating trailing edge to trailing edge
Domain, influence area are gradually expanded, and exhibition is located on trailing edge Shedding Vortex upwards, and finally mutually converges with trailing edge Shedding Vortex.Therefore,
It is considered herein that the region that the axial vorticity after blade suction surface defiber and after blade trailing edge positioned at leaf central part is positive
For concentrated shed vortex region.
5. trailing edge Shedding Vortex region：Positioned at the tail area after trailing edge, open up to position be located at concentrated shed vortex and angle whirlpool it
Between the region that is positive of axial vorticity.
6. other regions：The area from 40% chord positions after blade inlet edge to trailing edge in addition to above description region
Domain.
By analyzing above, can by the positive negativity of axial vorticity, the position and wall surface of each attached wire and defiber away from
Leaf grating runner is divided into above 6 region by from three indexs.But it is real to be accurately distinguished due to list with the positive negativity of axial vorticity
Vortex structure, i.e. such as boundary-layer region even if apparent vortex structure is not present in the region, but still have certain axial vorticity.
Therefore, in practical operation, region singly cannot be divided with the positive negativity of axial vorticity, and a threshold value should be set, with screen
Cover the interference of vorticity smaller area.The size of its threshold value can be set between the 1%-10% of axial vorticity magnitude.For example, when examining
Axial vorticity in the compressor blade row channel of worry is 103-104Between when, can be set threshold value be 100s-1.I.e. to above
The axial vorticity of analysis is positive and indicates that axial vorticity is greater than 100s-1, axial vorticity be negative spindle to vorticity be less than -100s-1.Therefore,
Other regions include in flow field vorticity away from face-off size be less than 100s-1Within region.Simultaneously as vorticity characteristic, in vorticity
Large area can form vorticity direction different vorticity compensatory zone therewith in its vicinity, such as near pressure face shear zone
Vorticity is that vorticity near negative region and angle whirlpool is that nearby vorticity is negative region for concentrated shed vortex after negative region and trailing edge.
The presence of vorticity compensating basin is also exactly the physical location reason for it that vorticity is unable to Precise Representation whirlpool, but vorticity can be substantially anti-
Reflect the distribution situation in whirlpool.Due to might not but have the presence in whirlpool, since its coverage is small, institute in these vorticity compensatory zones
By these regions and in other regions.
It can by the integral calculation to progress dissipation in different zones by above region division criterion
Loss size caused by various whirlpools group and the boundary-layer in compressor blade row is obtained, by comparing the loss size in each region,
The main loss source in compressor blade row can be measured.
The loss for 40% chord length after compressor blade row and blade trailing edge is distributed isogram as shown in Figure 1, due to rectangle
Leaf grating has the characteristics that open up along 50% symmetrical to section, therefore Fig. 1 only indicates half leaf high scope of leaf grating, and below to leaf grating
Leaf open up height description be the leaf grating high to half leaf for, i.e., the exhibition of the high leaf grating of half leaf to position range be 0-
100% opens up to position.
Fig. 2-4 show the axial Vorticity Distribution isogram and subregion of the equal axial cross sections in certain compressor blade row channel
Schematic diagram.Fig. 2 is the axial chord positions of leaf grating 20% section, and Fig. 3 is 50% axial chord positions section, and Fig. 4 is after trailing edge
20% chord positions section.(since isopleth is intensive, consider clarity, do not mark the size data of axial vorticity isopleth,
The positive negativity of its numerical value can be supplemented by the cloud charts of axial vorticity and be obtained)
By Fig. 2 and corresponding axial Vorticity Distribution cloud atlas, it can be found that being biased to have axial whirlpool on a large scale at end wall
Amount is negative region, is Passage Vortex region.And in the smaller position of wall surface distance, i.e. abutting end wall and blade suction surface exists axial
Vorticity is positive region, i.e. near wall friction loss region, is divided into three parts, that is, leans on proximal end wall, blade suction surface and pressure face are attached
Near field.Having lesser vorticity at angular region is positive region, i.e. suction/pressure face angle whirlpool region.It is de- there is no concentrating in the position
Fall whirlpool region and trailing edge Shedding Vortex region.Fig. 3 increases the concentrated shed vortex region of middle part of blade on the basis of Fig. 2.Its angle
Whirlpool constrains near defiber and the attached wire of angular region position, and concentrated shed vortex is located at the rear region of suction surface defiber, leads to
The exhibition in road whirlpool is then confined to the Passage Vortex defiber of suction surface to position.Concentrated shed vortex position is lifted upwards at Fig. 4, is being concentrated
New trailing edge Shedding Vortex region is generated between Shedding Vortex and angle whirlpool, and vorticity compensation occurs close to suction surface side in concentrated shed vortex
Region.In addition, the angle Vortices merging for inhaling pressure face at Fig. 4 is angle whirlpool region.Accordingly, it is believed that leading in the above method
The positive and negative of axial vorticity, each defiber and attachment line position are crossed, three indexs of wall surface distance can probably distinguish the shadow of each whirlpool group
Ring region.
After completing region division, just needs to carry out loss integral to the region divided, calculate the damage in each region
Lose size.Its integration method directly can carry out volume point to the region divided by CFD the poster processing soft, due to grasping to be conventional
Make, which is not described herein again.
Embodiment 1
In order to verify the exploitativeness of the invention, to a certain high load axial compressor and fan leaf grating, under its+5 degree angle of attack
The case where, the loss in leaf grating is solved using this method, the loss in each region of topology discovery integrates size such as the following table 1 institute
Show.
It can be found that the volume as shared by Passage Vortex is maximum, corresponding percent loss is also maximum for analysis, therefore,
For the leaf grating, Passage Vortex is that the root of its loss exists, and to improve the efficiency of the leaf grating, it should be noted that inhibit channel internal channel whirlpool
Development.Secondly, it is found that although shared volume ratio is also larger in other regions, but the flowing in the region is closer to mainstream,
Therefore its corresponding loss is smaller, this is consistent with previous research conclusion.
Claims (1)
1. a kind of compressor blade row loss calculation method, which is characterized in that include the following steps：
Step 1：It is leaf grating leading edge, region of the terminal between 40% chord length after leaf grating trailing edge, according to axial vorticity to starting point
Positive and negative, each defiber, attachment line position and wall surface distance carry out vorticity field region division, are respectively divided into Passage Vortex region, suction/pressure
Power face angle whirlpool region, concentrated shed vortex region, leaf grating trailing edge Shedding Vortex region, near wall friction loss region and other regions,
Definition of Division is as follows：
Passage Vortex region：In entire channel, close to end wall, axial vorticity is negative, and opening up to height is that end wall to Passage Vortex divides
Between offline；
Near wall friction loss region：At end wall, blade suction surface is near wall position and blade pressure surface is close to wall
At the position of face, the wall surface of near wall is millimeter magnitude apart from size, and axis vorticity is positive；
Suction/pressure face angle whirlpool region：Positioned at/the intersection of pressure face and end wall is inhaled in blade, axial vorticity is positive；It opens up to height
It is end wall between the defiber of angle whirlpool, circumferential zones are blade root between the attached wire of angle whirlpool；
Leaf grating trailing edge Shedding Vortex region：Positioned at the tail area after leaf grating trailing edge, opens up to position and be located at concentrated shed vortex and angle whirlpool
Between the region that is positive of axial vorticity；
Concentrated shed vortex region：In leaf grating leading edge to leaf grating tail edge area, after the defiber of blade suction surface, direction is opened up in leaf
Upper to be located on Passage Vortex close to leaf central part point, axial vorticity performance is positive；
Other regions：In addition to above description region from 40% chord length position after blade inlet edge to leaf grating trailing edge
The region set；
Step 2：Loss integral is carried out to the region divided in step 1：The volume point of corresponding region is carried out to dissipative function,
The loss size in each region is calculated, to obtain loss caused by each vortex structure.
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