CN108757178B - A kind of asymmetric wedge-shaped vortex generator and its design method applied to compressor blade row flowing control - Google Patents
A kind of asymmetric wedge-shaped vortex generator and its design method applied to compressor blade row flowing control Download PDFInfo
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- CN108757178B CN108757178B CN201810512443.7A CN201810512443A CN108757178B CN 108757178 B CN108757178 B CN 108757178B CN 201810512443 A CN201810512443 A CN 201810512443A CN 108757178 B CN108757178 B CN 108757178B
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- vortex generator
- wedge
- surface side
- shaped vortex
- compressor blade
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Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C3/00—Gas-turbine plants characterised by the use of combustion products as the working fluid
- F02C3/04—Gas-turbine plants characterised by the use of combustion products as the working fluid having a turbine driving a compressor
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
- F02C7/057—Control or regulation
Abstract
The present invention proposes a kind of asymmetric wedge-shaped vortex generator and its design method applied to compressor blade row flowing control, wedge-shaped vortex generator structure is redesigned, minimize the size of the vortex generator of controlled suction face branch side, and then form drag loss and the air-flow separation of suction surface side are effectively reduced, solve the problems, such as that wedge-shaped vortex generator reduces the indifferent of compressor flow losses.The present invention is by introducing asymmetric wedge-shaped vortex generator, on the one hand induction produces suction surface whirlpool and pressure face whirlpool, pass through the low energy fluid of volume absorption surface layer, and then change the structure and lateral flow of Passage Vortex, reduce suction surface/end wall angular region air-flow separation, to reduce the pitot loss of compressor blade row.
Description
Technical field
The present invention relates to a kind of flow control technique fields of axial compressor cascade, specially a kind of to be applied to compressor
The asymmetric wedge-shaped vortex generator and its design method of Cascade Flow control.
Background technique
Under the requirement of the high thrust ratio of aero-engine, the direction of compressor towards high load capacity is developed.However, high load capacity must
So with big adverse pressure gradient and lateral pressure difference, so as to cause low energy fluid in boundary layer to accumulating at blade suction surface/blade root,
Generation large area corner separation, blocking blades channel, especially under off-design behaviour, the rotating stall or asthma of Yi Yinfa compressor
Vibration.For this purpose, there is varied control method for inhibiting corner separation, as end wall moulding, vortex generator, boundary layer are inhaled
Gas, bulge structure.Wherein, vortex generator (vortex generator, VG) is that one kind can locally generate high-energy whirlpool
The device of vortex structure is widely used in aircraft portion because its structure is simple, Yi Shixian, significant to boundary-layer flowing control effect
Part flowing control research.Document " Effects of Vortex Generator Application on the
Performance of a Compressor Cascade[J].Journal of Turbomachinery,2013,135(2)”
Disclose three kinds of various forms of vortex generator schemes.In document result of study show wedge-shaped vortex generator application for
Cascade performance, which has, to be obviously improved, and design point pitot loss reduces 9%.Symmetric form wedge shape vortex generator ruler described in document
Very little big, being placed in runner can cause corresponding form drag loss to increase；Suction surface side vortex generator width is big, under big situations of attack
It will lead to air-flow separation, weaken the ability that wedge-shaped vortex generator reduces compressor flow losses.
Summary of the invention
In order to solve existing wedge-shaped vortex generator because can not efficiently reduce compressor flowing damage caused by unreasonable structure
The problem of mistake, the invention proposes a kind of asymmetric wedge-shaped vortex generator applied to compressor blade row flowing control and its sets
Meter method.
Result of study before project team is shown, before suction/pressure face whirlpool of wedge-shaped vortex generator induction is similar to blade
The horse shoe vortex of edge, suction surface branch into the formation that channel rear portion point participates in Passage Vortex, and section downstream dissipates, and pressure face point
Zhi Ze is primarily involved in the formation of Passage Vortex, and to reducing, pitot loss contribution is significant.Project team proposes a kind of asymmetric wedge as a result,
Shape vortex generator has redesigned wedge-shaped vortex generator structure, makes the vortex generator of controlled suction face branch side
Size minimizes, and then effectively reduces form drag loss and the air-flow separation of suction surface side, solves wedge-shaped vortex generator
Reduce the indifferent problem of compressor flow losses.
The technical solution adopted by the present invention to solve the technical problems are as follows:
A kind of asymmetric wedge-shaped vortex generator method applied to compressor blade row flowing control, feature exist
In: the following steps are included:
Step 1: the design parameter for determining wedge shape vortex generator geometry is radial height, axial length, suction surface
Side width and pressure surface side width；
Step 2: keeping suction surface side width and pressure surface side width equal, wedge shape is adjusted in the design domain of design parameter
The radial height of vortex generator, axial length and suction surface side width and pressure surface side width obtain several wedge-shaped whirlpool
Flow-generator design scheme；
Step 3: the several wedge-shaped vortex generator design scheme that step 2 obtains being modeled respectively, and is flowed using calculating
Mechanics means are tested under different designs scheme, and wedge-shaped vortex generator obtains wedge to the improvement of compressor blade row performance
The optimization value range of shape vortex generator design parameter；Wherein in cfdrc, wedge-shaped vortex generator mould
Type and gas compressor blade bar phantom installation relation are as follows: it is up-front that wedge-shaped vortex generator model is installed on compressor blade row leaf model
On end wall, the vertical point of wedge-shaped vortex generator top surface triangle base is 0.5mm at a distance from blade inlet edge point, and two o'clock line
Perpendicular to bottom edge；
Step 4: in the optimization value range for the wedge-shaped vortex generator design parameter that step 3 obtains, adjusting suction surface
Side width and pressure surface side width proportion obtain several asymmetric wedge-shaped vortex generator design side by Uniform ity Design Method
Case；
Step 5: the several asymmetric wedge-shaped vortex generator design scheme that step 4 obtains being modeled respectively, and is used
Fluid Mechanics Computation means are tested under different designs scheme, improvement of the asymmetric wedge shape vortex generator to compressor blade row performance
Effect obtains optimal asymmetric wedge-shaped vortex generator design scheme.
Further preferred embodiment, a kind of asymmetric wedge shape vortex generation applied to compressor blade row flowing control
Device method, it is characterised in that: compressor blade row performance improvement is commented as in step 3 and step 5 using pitot loss is reduced
Sentence foundation.
It is special using the asymmetric wedge-shaped vortex generator obtained by the above method applied to compressor blade row flowing control
Sign is: the design parameter of asymmetric wedge shape vortex generator geometry is radial height 12mm, axial length 35.6mm, is inhaled
Power surface side width 7.5mm, pressure surface side width 11.1mm.
Beneficial effect
The beneficial effects of the present invention are: the introducing of asymmetric wedge shape vortex generator, on the one hand induction produces suction surface
Whirlpool and pressure face whirlpool by the low energy fluid of volume absorption surface layer, and then change the structure and lateral flow of Passage Vortex, reduce suction
Power face/end wall angular region air-flow separation, to reduce the pitot loss of compressor blade row.Compared to prototype leaf grating, outlet
Pitot loss reduce 21.03%, reversed flow region area reduces 11.14%.On the other hand, it is vortexed and occurs relative to symmetric wedge
Device reduces the geometric dimension of suction surface side structure, reduces under the premise of guaranteeing pressure face side structure stream field beneficial to interference
The overall dimensions of vortex generator, so that since blocking bring form drag loss in vortex generator self-convection field reduces, from
And reduce the pitot loss of compressor.With the approximate symmetric wedge vortex generator of two kinds of geometries (scheme one: height
12mm, length 35.6mm, suction surface side width 7.5mm, pressure surface side width 7.5mm；Scheme two: height 12mm, length
35.6mm, suction surface side width 11.1mm, pressure surface side width 11.1mm) it compares, it can more effectively reduce blocked-off region, obtain
Lower pitot loss.
Additional aspect and advantage of the invention will be set forth in part in the description, and will partially become from the following description
Obviously, or practice through the invention is recognized.
Detailed description of the invention
Above-mentioned and/or additional aspect of the invention and advantage will become from the description of the embodiment in conjunction with the following figures
Obviously and it is readily appreciated that, in which:
Fig. 1 is the contour structure figure of non-symmetric wedge vortex generator；
Fig. 2 is that the asymmetric wedge-shaped vortex generator of the present invention applies schematic diagram in compressor blade row；
Fig. 3 is the partial enlarged view in Fig. 2 at A；
Fig. 4 is improvement of 12 kinds of different size symmetrical wedge shape vortex generator schemes to compressor blade row flow field pitot loss
Effect contrast figure；
Fig. 5 is that 26 kinds of different asymmetric wedge-shaped vortex generator schemes of size control compressor blade row flow field pitot loss
Comparison diagram；
Fig. 6 is that compressor blade row flow field edge flows to pitot loss comparison diagram；
Fig. 7 is compressor blade row flow field along the comparison diagram for flowing to recirculating zone size on different cross section.
Wherein: 1-radial height, 2-axial lengths, 3-suction surface side width, 4-pressure surface side width, 5-is non-right
Claim the vertical point of wedge-shaped vortex generator top surface triangle base, 6-compressor blade row blades, 7-compressor blade row blade inlet edges
Point.
Specific embodiment
The embodiment of the present invention is described below in detail, the embodiment is exemplary, it is intended to it is used to explain the present invention, and
It is not considered as limiting the invention.
One of the present embodiment is applied to the asymmetric wedge-shaped vortex generator method of compressor blade row flowing control, packet
Include following steps:
Step 1: the design parameter for determining wedge shape vortex generator geometry is radial height, axial length, suction surface
Side width and pressure surface side width.Referring to Fig.1, asymmetric wedge-shaped vortex generator generally tetrahedral structure.Geometric dimension by
Radial height 1, axial length 2, suction surface side width 3, pressure surface side width 4 determine.5 be asymmetric wedge-shaped vortex generator top
The vertical point of face triangle base.Radial height 1 is vertical with bottom surface end wall.
Step 2: keeping suction surface side width 3 and pressure surface side width 4 equal, adjust wedge in the design domain of design parameter
The radial height 1 of shape vortex generator, the size of axial length 2 and suction surface side width 3 and pressure surface side width 4 consider
To the universality for improving the device, the height of vortex generator is associated with boundary layer thickness, and one is obtained 12 kinds of design sides
Case；It is shown in Table 1:
1 12 kinds of table wedge-shaped vortex generator sizes
Step 3: the several wedge-shaped vortex generator design scheme that step 2 obtains being modeled respectively, and is flowed using calculating
Mechanics means are tested under different designs scheme, and wedge-shaped vortex generator obtains wedge to the improvement of compressor blade row performance
The optimization value range of shape vortex generator design parameter；Wherein referring to Fig. 2, Fig. 3, in cfdrc, wedge shape
Vortex generator model and gas compressor blade bar phantom installation relation are as follows: wedge-shaped vortex generator model is installed on compressor blade row leaf
On the up-front end wall of 6 model of piece, the vertical point 5 of wedge-shaped vortex generator top surface triangle base is at a distance from blade inlet edge point 7
0.5mm, and two o'clock line is perpendicular to bottom edge.
Wedge-shaped vortex generator design scheme is modeled using unstructured grid in the present embodiment, to reduce pitot loss
As the judging basis to compressor blade row performance improvement.The ability that wedge-shaped vortex generator reduces pitot loss passes through total crushing
Losing, which reduces percentage, measures.Pitot loss Loss is defined as follows:
P in formulat, p respectively indicate stagnation pressure and static pressure, subscript m represents 50% leaf height, and in represents entrance location.
Fig. 4 shows that 12 kinds of schemes all reduce total pressure loss coefficient to some extent, and when wedge-shaped vortex generator size
Fall in following range: height 10-12.5mm, when length 31-36mm, width 16-24mm, the effect for reducing pitot loss is optimal.
Step 4: in the optimization value range for the wedge-shaped vortex generator design parameter that step 3 obtains, adjusting suction surface
Side width 3 and pressure surface side width 4 match, and obtain 26 kinds of asymmetric wedge-shaped vortex generator design sides by Uniform ity Design Method
Case；It is shown in Table 2.
The asymmetric wedge-shaped vortex generator dimension plan of 26 kinds of 2 uniform design of table
Step 5: the several asymmetric wedge-shaped vortex generator design scheme that step 4 is obtained using unstructured grid
It models respectively, and using under Fluid Mechanics Computation means test different designs scheme, asymmetric wedge shape vortex generator is to calming the anger
The improvement of machine cascade performance obtains optimal asymmetric wedge-shaped vortex generator design scheme.
Fig. 5 is shown, installs 26 kinds of schemes of asymmetric wedge-shaped vortex generator additional compared under prototype leaf grating total pressure loss coefficient
Drop is more than 10.8%.Demonstrate the validity of the control method.Wherein scheme 21 (radial height 12mm, axial length
35.6mm, suction surface side width 7.5mm, pressure surface side width 11.1mm) pitot loss it is minimum, compared to prototype cascade loss
Reduce 21.03%.
In order to further compare Similar size symmetric wedge vortex generator and asymmetric wedge-shaped vortex generator convection current
The influence of field pitot loss, devises the comparison scheme of two kinds of symmetric wedge vortex generators: scheme one: height 12mm, length
35.6mm, suction surface side width 7.5mm, pressure surface side width 7.5mm；Scheme two: height 12mm, length 35.6mm, suction surface
Side width 11.1mm, pressure surface side width 11.1mm.
Fig. 6 and Fig. 7 explanation, compared to for symmetric wedge vortex generator, the implementation of asymmetric wedge shape vortex generator can
More effectively to improve flow losses along flow direction distribution, reduce the recirculation zone in blade grid passage, so that the stopping state in channel
It is greatly improved, to reduce pitot loss.
Although the embodiments of the present invention has been shown and described above, it is to be understood that above-described embodiment is example
Property, it is not considered as limiting the invention, those skilled in the art are not departing from the principle of the present invention and objective
In the case where can make changes, modifications, alterations, and variations to the above described embodiments within the scope of the invention.
Claims (3)
1. a kind of asymmetric wedge-shaped vortex generator method applied to compressor blade row flowing control, it is characterised in that: including
Following steps:
Step 1: the design parameter for determining wedge shape vortex generator geometry is radial height, axial length, and suction surface side is wide
Degree and pressure surface side width；
Step 2: keeping suction surface side width and pressure surface side width equal, wedge shape vortex is adjusted in the design domain of design parameter
The radial height of generator, axial length and suction surface side width and pressure surface side width obtain several wedge shape vortex hair
Raw device design scheme；
Step 3: the several wedge-shaped vortex generator design scheme that step 2 obtains being modeled respectively, and using calculating fluid force
It learns to do under section test different designs scheme, wedge-shaped vortex generator obtains wedge-shaped whirlpool to the improvement of compressor blade row performance
The optimization value range of flow-generator design parameter；Wherein in cfdrc, wedge-shaped vortex generator model with
Gas compressor blade bar phantom installation relation are as follows: wedge-shaped vortex generator model is installed on the up-front end wall of compressor blade row leaf model
On, the vertical point of wedge-shaped vortex generator top surface triangle base is 0.5mm at a distance from blade inlet edge point, and two o'clock line is vertical
In bottom edge；
Step 4: in the optimization value range for the wedge-shaped vortex generator design parameter that step 3 obtains, adjustment suction surface side is wide
Degree and pressure surface side width proportion obtain several asymmetric wedge-shaped vortex generator design scheme by Uniform ity Design Method；
Step 5: the several asymmetric wedge-shaped vortex generator design scheme that step 4 obtains being modeled respectively, and using calculating
Hydrodynamics means are tested under different designs scheme, and asymmetric wedge shape vortex generator imitates the improvement of compressor blade row performance
Fruit obtains optimal asymmetric wedge-shaped vortex generator design scheme.
2. a kind of asymmetric wedge-shaped vortex generator side applied to compressor blade row flowing control according to claim 1
Method, it is characterised in that: using reduce pitot loss as in step 3 and step 5 to the judge of compressor blade row performance improvement according to
According to.
3. being occurred using the asymmetric wedge shape vortex for being applied to compressor blade row flowing control that claim 1 the method obtains
Device, it is characterised in that: the design parameter value of asymmetric wedge shape vortex generator geometry is radial height 12mm, axial long
Spend 35.6mm, suction surface side width 7.5mm, pressure surface side width 11.1mm.
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| CN110953187A (en) * | 2019-12-19 | 2020-04-03 | 中国航空发动机研究院 | Transonic compressor plane cascade with bionic sawtooth tail edge structure |
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