CN105650032B - The diffuser of centrifugal compressor - Google Patents
The diffuser of centrifugal compressor Download PDFInfo
- Publication number
- CN105650032B CN105650032B CN201610189431.6A CN201610189431A CN105650032B CN 105650032 B CN105650032 B CN 105650032B CN 201610189431 A CN201610189431 A CN 201610189431A CN 105650032 B CN105650032 B CN 105650032B
- Authority
- CN
- China
- Prior art keywords
- linear leaf
- short blade
- line
- blade
- trailing edge
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Active
Links
- 238000000926 separation method Methods 0.000 claims abstract description 16
- 230000002411 adverse Effects 0.000 abstract description 4
- 239000010410 layer Substances 0.000 description 11
- 238000009792 diffusion process Methods 0.000 description 7
- 238000009434 installation Methods 0.000 description 3
- 230000015572 biosynthetic process Effects 0.000 description 2
- 238000009423 ventilation Methods 0.000 description 2
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 230000007423 decrease Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 238000005516 engineering process Methods 0.000 description 1
- 230000003116 impacting effect Effects 0.000 description 1
- 239000000411 inducer Substances 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
- 230000002040 relaxant effect Effects 0.000 description 1
- 230000003068 static effect Effects 0.000 description 1
- 239000000126 substance Substances 0.000 description 1
- 230000001629 suppression Effects 0.000 description 1
- 239000002344 surface layer Substances 0.000 description 1
Classifications
-
- 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
- F04D29/40—Casings; Connections of working fluid
- F04D29/42—Casings; Connections of working fluid for radial or helico-centrifugal pumps
- F04D29/44—Fluid-guiding means, e.g. diffusers
- F04D29/441—Fluid-guiding means, e.g. diffusers especially adapted for elastic fluid pumps
- F04D29/444—Bladed diffusers
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2250/00—Geometry
- F05D2250/50—Inlet or outlet
- F05D2250/52—Outlet
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses the diffuser of centrifugal compressor.The structure of diffuser is improved, further improving its service behaviour has important application value.A piece of short blade is arranged in the runner of the adjacent two panels linear leaf of the present invention；The leading edge of linear leaf is curved surface and is obliquely installed that the angle of costa and wheel disc central axis is 6~8 °；The leading edge radius of curvature of linear leaf gradually increases along wheel disc to wheel cap direction；Linear leaf offers three through pressure face and the fold-line-shaped conduit of suction surface；The trailing edge of linear leaf is located at pressure face and is provided with trailing edge wingtip.The short blade that the present invention is located in adjacent linear leaf runner suppresses the generation of blade surface air-flow separation；Fold-line-shaped conduit reduces the pressure differential of pressure face and suction surface, reduces adverse pressure gradient, effectively blows down partial blade afterbody suction surface boundary-layer separation bubble；The parabola shaped winglet of trailing edge can suppress the growth of the wingtip vortex of the pressure differential generation of traditional airfoil trailing edge suction surface and pressure face.
Description
Technical field
The invention belongs to field of ventilation equipment, it is related to centrifugal fan, and in particular to a kind of diffuser of centrifugal compressor.
Background technology
Centrifugal compressor is as a kind of energy conversion device, and it is mainly by the rotation of impeller, so that impeller runner
The motion of interior gas, is converted into the mechanical energy of prime mover the energy of gas.Centrifugal compressor has high pressure, stably due to it
Condition range is wide, simple in construction, it is easy to maintain the features such as, be widely used in oil, Aero-Space, metallurgy, chemical industry and mine
Etc. industry, and play an important role.
In centrifugal compressor, diffuser is generally divided into two kinds of vaneless diffuser and vane diffuser.Vaneless diffuser is normal
That sees constitutes circular passage by two planomurals and is constituted.Vaneless diffuser simple structure, low cost, performance curve is gentle, surely
Determine operating mode wider, and it is less efficient still unobvious when Mach number is higher, but vaneless diffuser interior air-flow angle is basically unchanged, gas
Stream is moved substantially along helical line, and flow path is longer, and friction loss is larger, and efficiency is less than blade under design conditions
Diffuser.General vaneless diffuser is often used in the less compressor of pressure ratio.Vane diffuser has diffusion degree big, size
Small the characteristics of, lose smaller than vaneless diffuser in design conditions downstream, thus efficiency is higher.Vane diffuser can pass through half
Footpath increases deceleration diffusion, while radial blade can make flow angle by angular deflection is wished, makes circulation area further increase to carry
High diffusion ability；And it is improving the efficiency and level pressure ratio of centrifugal compressor, changes optimal working point position, expand stable work
Played a very important role as scope.
But vane diffuser, due to the presence of blade, variable working condition impact loss is larger, efficiency declines obvious.Compressor one
As be all operated under low discharge state, and under low discharge, diffuser vane inlet air flow formation high incidence, when the angle of attack reaches one
Serious air-flow separation easily occurs during definite value, in runner.And once suction surface boundary-layer air-flow occurrence of large-area is separated, easily
Compressor is set to enter stall flutter state, so as to have a strong impact on the job stability of engine.If flow is more than design discharge,
Easily occur choking phenomenon in vane diffuser throat again, vane diffuser is lost diffusion ability.
Generally for diffuser service behaviour is improved, compressor can use airfoil blade, although wing blades compare one
As version type Blade Properties to get well, but be still unavoidable from angle of attack when inhomogeneities and variable working condition due to impeller outlet air-flow
Become big and cause efficiency to decline, therefore, the structure of diffuser is improved on the basis of wing blades, further improve its work
Performance has highly important application value and work prospect.
The content of the invention
The purpose of the present invention is for there is provided one kind the problem of the diffuser intake air-flow angle of attack is excessive under low flow rate condition
The diffuser of centrifugal compressor, the short blade that the diffuser is located in adjacent linear leaf runner can guide airflow direction to become
Change, change the flow angle distribution in diffuser runner, more air-flows is flowed along air stream surface, suppress blade surface
The generation of air-flow separation, so not only increases the operating efficiency of diffuser, also increases working range.Broken line in diffuser
Shape conduit can reduce the pressure differential of pressure face and suction surface, reduce adverse pressure gradient, effectively blow down partial blade afterbody suction surface
Boundary-layer separation bubble.The parabola shaped winglet of trailing edge can suppress traditional airfoil trailing edge suction surface and pressure face
The growth for the wingtip vortex that pressure differential is produced, makes the position of wing tip vortex shedding successively mobile, reduces the intensity of wingtip vortex.
The present invention includes linear leaf, short blade, wheel disc and wheel cap；Described linear leaf has 12, is evenly distributed
On wheel disc；A piece of short blade is arranged in the runner of adjacent two panels linear leaf, short blade is close to the suction surface side of linear leaf.It is same
On cross section, to take turns radius of a circle of the disk center as the center of circle than linear leaf suction surface where the costa section of short blade suction surface
Costa section where the small 15~20mm of radius of a circle, and the costa section of short blade suction surface and adjacent two panels linear leaf
Central angle folded by the costa section of suction surface is respectively 5 ° and 25 °；The entrance established angle of linear leaf is 32~36 °, short blade
Entrance established angle be 36~40 °.
Described linear leaf uses wing-shaped structure, and bolt is connected with the linear leaf screwed hole that linear leaf is opened up, by linear leaf
It is fixed on wheel disc；The leading edge of linear leaf is curved surface and is obliquely installed that the angle of costa and wheel disc central axis is 6~8 °；
The leading edge radius of curvature of linear leaf gradually increases along wheel disc to wheel cap direction.Linear leaf offers three and runs through pressure face and suction
The fold-line-shaped conduit in face.The shape of three fold-line-shaped conduits is identical, is arranged side by side along the length direction of linear leaf, and three broken lines
The length of shape conduit is gradually reduced by leading edge to the trailing edge direction of linear leaf.Described fold-line-shaped conduit is two-part groove, leading portion
For air inlet section, back segment is air outlet section, and the groove width of air inlet section and air outlet section is equal, is 8~10mm；Three fold-line-shaped conduits enter
Gas section enters camber line segment length difference shared between the center line of opening's edge linear leaf short transverse and linear leaf suction surface costa
Account for 1/3,1/2 and the 2/3 of linear leaf suction surface arc length.
On the longitudinal section of linear leaf, the air inlet section center line relative vane molded line of fold-line-shaped conduit with air inlet section center
The inclination angle of line point of intersection tangent line be 45 °, air outlet section center line relative vane molded line with air outlet section center line point of intersection tangent line
Inclination angle is 30 °.
The upper wall surface of fold-line-shaped conduit is the 45~50% of linear leaf height with the distance of linear leaf blade root, lower wall surface and length
The distance of blade root is the 5~10% of linear leaf height.
The trailing edge of linear leaf is located at pressure face and is provided with trailing edge wingtip；The side of the trailing edge wingtip is with pressure face in trailing edge
Angle between the tangent plane at place is 90 °；The width value of trailing edge wingtip is close along wheel disc to wheel cap direction parabolically regular increase
Wheel disc position width is 0, and Breadth Maximum is no more than the 5% of linear leaf chord length.
Described short blade uses wedge structure, and short blade is welded on wheel disc；Short blade chord length is linear leaf chord length
0.45~0.5, highly 0.6~0.7 for linear leaf；Two arc shaped wings are offered in the suction surface and pressure face of short blade
Groove；Two arc shaped wing groove center lines of same side are respectively at the 1/3 and 2/3 of short blade height；The arc shaped wing groove is leaned on
The end face of nearly short blade leading edge is the 1/8 of short blade chord length with the distance of short blade costa, and arc shaped wing groove is after short blade
The end face of edge is the 1/6 of short blade chord length with the distance of short blade trailing edge；Described arc shaped wing groove is uiform section groove, and section is in
It is semicircle.
Improved by the long and short blade inlet angle of attack, the fold-line-shaped conduit of linear leaf is designed, the trailing edge wingtip of linear leaf and short
The arc shaped wing groove of blade designs to optimize the eddy airstream of interior boundary layers separation and afterbody, so as to lift diffuser efficiency.
Beneficial effects of the present invention：
The present invention can improve the problem of diffuser inlet air-flow angle of attack changes under variable working condition, positioned at adjacent linear leaf stream
Short blade in road can guide airflow direction to change, and change the flow angle distribution in diffuser runner, make more gas
Stream can flow along air stream surface, suppress the generation of blade surface air-flow separation, prevent the generation of surge.So not only centrifuge
The reasonable range of operation of ventilation blower, while the diffusion ability and operational efficiency of diffuser can be improved.The bevelled junction of linear leaf leading edge
Structure makes diffuser inlet in the diverse location in the high direction of the leaf distance different from impeller outlet holding, adjusts the height come out from impeller
Fast ternary air-flow, especially reduces the gasflow mach number at diffuser inlet, reduces impact loss.And the presence energy of short blade
Enough improvement incident air flow angles effective in variable working condition.After air-flow enters diffuser runner, the fold-line-shaped conduit in diffuser
The pressure differential of pressure face and suction surface can be reduced, reduce adverse pressure gradient, effectively blow down partial blade afterbody suction surface boundary-layer
Separation bubble, so as to reduce the area of boundary-layer Disengagement zone, increases the real area size of blade path, improves compression
The flow of machine.The parabola shaped winglet of trailing edge can suppress the pressure differential of traditional airfoil trailing edge suction surface and pressure face
The growth of the wingtip vortex of generation, makes the position of wing tip vortex shedding successively mobile, reduces the intensity of wingtip vortex, reduce pneumatic make an uproar
Sound, improves the overall performance of diffuser.
Brief description of the drawings
Fig. 1 is overall structure stereogram of the invention；
Fig. 2 is distribution schematic diagram of the long and short blade on wheel disc in the present invention；
Fig. 3 is a side isometric view of linear leaf in the present invention；
Fig. 4 is another side isometric view of linear leaf in the present invention；
Fig. 5 is Fig. 4 partial enlarged drawing；
Fig. 6 is the fold-line-shaped conduit schematic cross-section of linear leaf in the present invention；
Fig. 7 is the structural perspective of short blade in the present invention.
Embodiment
Below in conjunction with the accompanying drawings and embodiment the invention will be further described.
As illustrated in fig. 1 and 2, the diffuser of centrifugal compressor, including linear leaf 1, short blade 2, wheel disc 3 and wheel cap；Come into leaves
Piece 1 has 12, is evenly distributed on wheel disc；A piece of short blade 2 is arranged in the runner of adjacent two panels linear leaf 1, short blade 2 is leaned on
The suction surface side of nearly linear leaf 1.On same cross section, where the costa section of the suction surface of short blade 2 using take turns disk center as
The radius of a circle in the center of circle is than the small 15mm of radius of a circle where the costa section of the suction surface of linear leaf 1, and short blade 2 suction surface
Costa section is respectively θ=5 ° and β=25 ° with central angle folded by the costa section of the adjacent suction surface of two panels linear leaf 1；It is long
The entrance established angle of blade 1 is α3A1=32 °, the entrance established angle of short blade 2 is α3A2=36 °.
As shown in Fig. 3,4 and 5, linear leaf 1 uses wing-shaped structure, the linear leaf screwed hole 1-2 that bolt is opened up with linear leaf 1
Connection, linear leaf 1 is fixed on wheel disc 3；The leading edge 1-1 of linear leaf is curved surface and is obliquely installed that costa is with taking turns disk center
The angle of axis is 6 °；The leading edge radius of curvature of linear leaf gradually increases along wheel disc to wheel cap direction.Linear leaf 1 offers three
Through pressure face and the fold-line-shaped conduit 1-3 of suction surface.The shape of three fold-line-shaped conduits is identical, along the length side of linear leaf 1
To being arranged side by side, and the length of three fold-line-shaped conduits is gradually reduced by leading edge to the trailing edge direction of linear leaf 1.Fold-line-shaped conduit
For two-part groove, leading portion is air inlet section, and back segment is air outlet section, and the groove width of air inlet section and air outlet section is 10mm；Three fold-line-shapeds
The air inlet section of conduit enters arc shared between the center line of opening's edge linear leaf short transverse and linear leaf suction surface costa
Length accounts for 1/3,1/2 and the 2/3 of the suction surface arc length of linear leaf 1 respectively.
As shown in fig. 6, on the longitudinal section of linear leaf 1, the air inlet section center line relative vane molded line of fold-line-shaped conduit exists
Be 45 ° with the inclination angle of air inlet section center line point of intersection tangent line, air outlet section center line relative vane molded line with air outlet section center line
The inclination angle of point of intersection tangent line is 30 °.
The upper wall surface of the fold-line-shaped conduit and distance of the blade root of linear leaf 1 is the height of linear leaf 1 45%, lower wall surface is with coming into leaves
The distance of the blade root of piece 1 is the 5% of the height of linear leaf 1.
As shown in figure 5, the trailing edge of linear leaf, which is located at pressure face, is provided with trailing edge wingtip 1-4；Trailing edge wingtip 1-4 side with
Angle of the pressure face between the tangent plane at trailing edge is 90 °；Trailing edge wingtip 1-4 width value presses parabolic along wheel disc to wheel cap direction
Line regular increase, is 0 close to wheel disc position width, and Breadth Maximum is no more than the 5% of the chord length of linear leaf 1.
As shown in fig. 7, short blade 2 uses wedge structure, short blade 2 is welded on wheel disc 3.The chord length of short blade 2 is to come into leaves
The 0.5 of piece chord length, highly 0.7 for linear leaf 1；Two arc shaped wing grooves are offered in the suction surface and pressure face of short blade 2
2-1；Two arc shaped wing groove center lines of same side are respectively at the 1/3 and 2/3 of the height of short blade 2；Arc shaped wing groove is close
The end face of the leading edge of the short blade 2 and distance of the costa of short blade 2 is short blade chord length 1/8, arc shaped wing groove is after short blade 2
The end face of edge is the 1/6 of the chord length of short blade 2 with the distance of the trailing edge of short blade 2；Arc shaped wing groove is uiform section groove, and section is in semicircle
Shape.
Improved by the long and short blade inlet angle of attack, the fold-line-shaped conduit of linear leaf is designed, the trailing edge wingtip of linear leaf and short
The arc shaped wing groove of blade designs to optimize the eddy airstream of interior boundary layers separation and afterbody, so that diffuser efficiency is lifted,
It is specific as follows：
1st, the long and short blade inlet angle of attack is improved：
From diffuser efficiency calculation formula, the efficiency of diffuser and the entrance of blade, exit installation angle, and blade
Entrance, outlet flow angle have in close relations, are changeless after the completion of the entrance of usual blade, exit installation angle design, and
Inlet air flow angle α3Then change with the change of flow rate working conditions, when flow increases, α3Increase；When the flow if reduced, α3Subtract
It is small.Now, an entrance angle of attack i is there is in diffuser inlet, entrance angle of attack i is defined as follows：
I=α3A-α3
In formula, α3AFor the entrance established angle of blade；No matter i is just or is negative, and deviation 0 is bigger, can be sent out in blade surface
Raw boundary layer separation.So in order to reduce flow separation in diffuser as far as possible, it should by entrance angle of attack i controls in certain scope
It is interior.Under low flow rate condition, due to inlet air flow angle α3Very little, so entrance angle of attack i is very big, causes the border of blade suction surface
Layer Disengagement zone expands rapidly, causes larger eddy loss, triggers surge phenomenon when serious.
The present invention adjusts inlet air flow angle α using the design of short blade is added in linear leaf runner3, especially in rill
The lower degree for relaxing entrance angle of attack i changes of amount.Diametrically, short blade is located at before linear leaf, in the circumferential close to long diffusion
Device suction surface.The entrance established angle α of linear leaf3A1Than the entrance established angle α of short blade3A2Small certain angle.
2nd, the fold-line-shaped conduit design of linear leaf：
The design of usual diffuser installation dimension can only make it keep high efficiency under Part load, when working conditions change,
Especially there is substantial amounts of air-flow separation and secondary flow phenomenon, windage loss ten in nearly pumping point and nearly choke point, diffuser
Divide serious, diffuser efficiency declines to a great extent.The present invention provides a kind of design slotted between linear leaf pressure face and suction surface,
Conduit is imported and exported in the presence of the static pressure difference of two ends, and pressure face fraction can be inhaled into groove, after accelerating through conduit, from suction surface
Channel outlet flows out, and this strand of air-flow can blow down certain blade suction surface boundary-layer separation bubble, control and delay boundary-layer
The extension of Disengagement zone, conduit is shaped as broken line type, is divided into inducer and outlet section.
As shown in figs. 3 and 6, the channel structure side by side in diffuser further improves air-flow in diffuser runner
Distribution situation.Conduit uses broken line type, and air inlet section is preceding, and air outlet section meets the feature that air-flow travels forward rear, and
Conduit UNICOM diffuser pressure face and suction surface, are so reduced by the pressure differential of pressure face and suction surface, reduce adverse pressure gradient, no
The flow of compressor is improve only, and eddy current crack can be reduced.
3rd, the arc shaped wing groove design of the trailing edge wingtip of linear leaf and short blade：
Linear leaf trailing edge wingtip：Due to airfoil fan afterbody suction surface and the differential pressure action of pressure face, the air-flow of pressure face
Trailing edge wingtip can be bypassed, eddy airstream is produced in afterbody, and extends to blade surface, very big energy loss is brought.
As shown in Figures 4 and 5, linear leaf trailing edge wingtip is distributed along the high parabolically type of leaf, and top is wide, narrow base, mainly
Take into account exit flow also has inhomogeneities along leaf height distribution.Wingtip structure can suppress the increase of wingtip vortex, reduce the wing
The intensity in sharp whirlpool, reduces resistance.And the suppression of wingtip vortex also make it that runner exit flowing is more uniform, flow losses are reduced.
The present invention imitates the way of aircraft wing winglet, and trailing edge wingtip is set in linear leaf trailing edge, and trailing edge wingtip is kept with trailing edge
Vertically, according to the pressure distribution feature on diffuser vane surface.
Short blade arc shaped wing groove：For the purposes of the boundary layer thickness on control short blade surface, suppress the boundary layer point on surface
From reducing separation whirlpool, twice arc shaped wing groove set respectively in suction surface and the pressure face of short blade, arc shaped wing groove is shaped as
Circular arc, the characteristics of more conforming to air motion, in order to prevent impacting to inlet air flow formation, makes arc shaped wing groove be placed in distance
The position of short blade leading edge certain distance.
Present invention is generally directed to the problem of the diffuser inlet air-flow angle of attack is changed greatly under variable working condition state, positioned at adjacent length
Short blade in blade passage can guide airflow direction to change, and change the flow angle distribution in diffuser runner, make
More air-flows can flow along air stream surface, suppress the generation of blade surface air-flow separation, prevent the generation of surge.So not
The reasonable range of operation of centrifugal fan is only improved, while the diffusion ability and operational efficiency of diffuser can be improved.
The incline structure that linear leaf leading edge is used makes diverse location of the diffuser inlet in the high direction of leaf be protected with impeller outlet
Different distances are held, the uneven air-flow come out from impeller is have adjusted, greatly reduces the free stream Mach number at diffuser inlet,
The distribution of inlet air flow is improved, the impact loss of diffuser inlet is reduced, so as to improve the operational efficiency of diffuser.
Claims (1)
1. the diffuser of centrifugal compressor, including linear leaf, short blade, wheel disc and wheel cap, it is characterised in that：Described linear leaf
There are 12, be evenly distributed on wheel disc；A piece of short blade is arranged in the runner of adjacent two panels linear leaf, short blade is close to long
The suction surface side of blade；On same cross section, to take turns disk center as the center of circle where the costa section of short blade suction surface
Radius of a circle is than the small 15~20mm of radius of a circle, and the leading edge of short blade suction surface where the costa section of linear leaf suction surface
Line section is respectively 5 ° and 25 ° with central angle folded by the costa section of adjacent two panels linear leaf suction surface；The entrance of linear leaf
Established angle is 32~36 °, and the entrance established angle of short blade is 36~40 °；
Described linear leaf uses wing-shaped structure, and bolt is connected with the linear leaf screwed hole that linear leaf is opened up, linear leaf is fixed
On wheel disc；The leading edge of linear leaf is curved surface and is obliquely installed that the angle of costa and wheel disc central axis is 6~8 °；Come into leaves
The leading edge radius of curvature of piece gradually increases along wheel disc to wheel cap direction；Linear leaf offers three through pressure face and suction surface
Fold-line-shaped conduit；The shape of three fold-line-shaped conduits is identical, is arranged side by side along the length direction of linear leaf, and three fold-line-shaped grooves
The length in road is gradually reduced by leading edge to the trailing edge direction of linear leaf；Described fold-line-shaped conduit be two-part groove, leading portion be into
Gas section, back segment is air outlet section, and the groove width of air inlet section and air outlet section is equal, is 8~10mm；The air inlet section of three fold-line-shaped conduits
Enter camber line segment length shared between the center line of opening's edge linear leaf short transverse and linear leaf suction surface costa and account for length respectively
1/3,1/2 and the 2/3 of blade suction surface arc length；
On the longitudinal section of linear leaf, the air inlet section center line relative vane molded line of fold-line-shaped conduit is handed over air inlet section center line
The inclination angle of tangent line is 45 ° at point, and air outlet section center line relative vane molded line is at the inclination angle with air outlet section center line point of intersection tangent line
For 30 °；
The upper wall surface of fold-line-shaped conduit is the 45~50% of linear leaf height with the distance of linear leaf blade root, lower wall surface and linear leaf
The distance of blade root is the 5~10% of linear leaf height；
The trailing edge of linear leaf is located at pressure face and is provided with trailing edge wingtip；The side of the trailing edge wingtip is with pressure face at trailing edge
Angle between tangent plane is 90 °；The width value of trailing edge wingtip is along wheel disc to wheel cap direction parabolically regular increase, close to wheel disc
Position width is 0, and Breadth Maximum is no more than the 5% of linear leaf chord length；
Described short blade uses wedge structure, and short blade is welded on wheel disc；Short blade chord length for linear leaf chord length 45~
50%, highly 60~70% for linear leaf；Two arc shaped wing grooves are offered in the suction surface and pressure face of short blade；It is same
Two arc shaped wing groove center lines of side are respectively at the 1/3 and 2/3 of short blade height；The arc shaped wing groove is close to short blade
The end face of leading edge and the distance of short blade costa is short blade chord length 1/8, end face of the arc shaped wing groove close to short blade trailing edge
Distance with short blade trailing edge is the 1/6 of short blade chord length；Described arc shaped wing groove is uiform section groove, and section semicircular in shape；
Improved by the long and short blade inlet angle of attack, the fold-line-shaped conduit of linear leaf is designed, the trailing edge wingtip and short blade of linear leaf
Arc shaped wing groove design optimize interior boundary layers separation and afterbody eddy airstream, so as to lift diffuser efficiency.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610189431.6A CN105650032B (en) | 2016-03-29 | 2016-03-29 | The diffuser of centrifugal compressor |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610189431.6A CN105650032B (en) | 2016-03-29 | 2016-03-29 | The diffuser of centrifugal compressor |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN105650032A CN105650032A (en) | 2016-06-08 |
| CN105650032B true CN105650032B (en) | 2017-11-07 |
Family
ID=56496515
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201610189431.6A Active CN105650032B (en) | 2016-03-29 | 2016-03-29 | The diffuser of centrifugal compressor |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN105650032B (en) |
Families Citing this family (14)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| KR102560686B1 (en) * | 2016-07-13 | 2023-07-27 | 한화파워시스템 주식회사 | Diffuser for centrifugal compressor |
| CN106837867B (en) * | 2016-12-07 | 2023-05-30 | 浙江理工大学 | Axial flow fan ternary impeller with vein structure and splitter blades |
| CN106762824B (en) * | 2016-12-07 | 2023-05-30 | 浙江理工大学 | Axial flow fan ternary impeller with vein structure and gull-shaped splitter blades |
| WO2018131167A1 (en) * | 2017-01-16 | 2018-07-19 | 三菱重工エンジン＆ターボチャージャ株式会社 | Turbine wheel, turbine, and turbocharger |
| CN107050542B (en) * | 2017-04-28 | 2023-07-04 | 浙江理工大学 | Miniature centrifugal blood pump capable of preventing blood cells from being damaged and circulating blood supply method thereof |
| CN107524630B (en) * | 2017-10-19 | 2024-04-19 | 江苏国泉泵业制造有限公司 | Open non-equidistant blade impeller |
| JP6740271B2 (en) * | 2018-03-05 | 2020-08-12 | 三菱重工業株式会社 | Impeller and centrifugal compressor equipped with this impeller |
| CN109026830B (en) * | 2018-08-16 | 2021-02-12 | 泛仕达机电股份有限公司 | Centrifugal impeller |
| EP4004375A1 (en) * | 2019-07-22 | 2022-06-01 | Carrier Corporation | Centrifugal or mixed-flow compressor including aspirated diffuser |
| CN112343864B (en) * | 2020-11-10 | 2022-11-04 | 江西省子轩科技有限公司 | Industrial application compressor unit |
| CN113187729B (en) * | 2021-04-29 | 2022-12-16 | 合肥工业大学 | Axial-flow pump for controlling eddy current and improving performance |
| CN113202789B (en) * | 2021-06-09 | 2022-09-30 | 清华大学 | Impeller for centrifugal compressor and centrifugal compressor |
| CN114688084A (en) * | 2022-05-23 | 2022-07-01 | 山东建筑大学 | Reverse lower-airfoil blade leading edge slotting configuration for reducing aerodynamic noise of centrifugal compressor |
| CN114856717B (en) * | 2022-06-02 | 2023-05-09 | 西安交通大学 | Novel exhaust diffuser structure with splitter plate capable of enhancing aerodynamic performance |
Family Cites Families (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1456020A (en) * | 1972-12-06 | 1976-11-17 | Lucas Industries Ltd | Centrifugal pumps for liquids method of making a drained floor |
| NL7302867A (en) * | 1973-03-01 | 1974-09-03 | ||
| JP3110205B2 (en) * | 1993-04-28 | 2000-11-20 | 株式会社日立製作所 | Centrifugal compressor and diffuser with blades |
| US8602728B2 (en) * | 2010-02-05 | 2013-12-10 | Cameron International Corporation | Centrifugal compressor diffuser vanelet |
| CN103486078A (en) * | 2013-10-23 | 2014-01-01 | 株洲联诚集团有限责任公司 | Bidirectional diffusion centrifugal fan |
| CN204476855U (en) * | 2015-01-27 | 2015-07-15 | 浙江理工大学 | Low noise with conduit is without spiral case centrifugal blower |
| CN204692190U (en) * | 2015-02-04 | 2015-10-07 | 浙江理工大学 | A kind of vane diffuser with deviated splitter vane |
-
2016
- 2016-03-29 CN CN201610189431.6A patent/CN105650032B/en active Active
Also Published As
| Publication number | Publication date |
|---|---|
| CN105650032A (en) | 2016-06-08 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN105650032B (en) | The diffuser of centrifugal compressor | |
| CN205559366U (en) | Centrifugal compressor's diffuser | |
| KR101885402B1 (en) | Gas turbine diffuser blowing method and corresponding diffuser | |
| CN106704261A (en) | Axial flow fan ternary impeller with vein-shaped structure and nonuniform empennage | |
| CN106050736B (en) | A kind of centrifugal blower noise reduction leaf blade structure | |
| CN107313860A (en) | A kind of blade profile for cooling system of prewhirling receives pore structure | |
| CN104165158A (en) | Centrifugal fan of extractor hood | |
| CN109026830B (en) | Centrifugal impeller | |
| CN106762840A (en) | Half vane diffuser high and its method for designing of a kind of both sides arrangement | |
| CN106762824A (en) | Axial flow blower 3 d impeller with leaf vein texture and sea-gull type splitterr vanes | |
| CN108980103B (en) | Design method of forward multi-wing centrifugal ventilator impeller with inlet winglet | |
| CN108953223A (en) | A kind of centrifugal impeller | |
| CN106368741A (en) | Blade with small wing rib blade tip and turbine utilizing blade | |
| CN206929130U (en) | Axial flow blower 3 d impeller with leaf vein texture and sea-gull type splitterr vanes | |
| CN207004920U (en) | Axial flow blower 3 d impeller with leaf vein texture and circular arc post splitterr vanes | |
| CN108953222B (en) | Centrifugal impeller | |
| CN207004919U (en) | Axial flow blower 3 d impeller with leaf vein texture and splitterr vanes | |
| CN114109895B (en) | Circumferential offset high-speed centrifugal impeller for inhibiting boundary layer separation | |
| CN110219829A (en) | A kind of anticentripetal spiral casing export structure | |
| CN109931290B (en) | Backward centrifugal impeller | |
| CN115182892A (en) | Bionic multi-factor coupling volute-free centrifugal fan | |
| CN205639001U (en) | Axial fan that winglet and ye ding have air -blowing structure is worn to blade pressure | |
| CN106837867A (en) | Axial flow blower 3 d impeller with leaf vein texture and splitterr vanes | |
| CN204082659U (en) | A kind of centrifugal blower of range hood | |
| CN209724796U (en) | A kind of return channel blade |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| EE01 | Entry into force of recordation of patent licensing contract |
Application publication date: 20160608 Assignee: ZHEJIANG SCI-TECH UNIVERSITY SHANGYU INDUSTRIAL TECHNOLOGY RESEARCH INSTITUTE Co.,Ltd. Assignor: ZHEJIANG SCI-TECH University Contract record no.: X2020330000077 Denomination of invention: Diffuser of centrifugal compressor Granted publication date: 20171107 License type: Common License Record date: 20201022 |
|
| EE01 | Entry into force of recordation of patent licensing contract | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220107 Address after: Room 503, building 3, No. 133, development avenue, Tongxiang Economic Development Zone, Tongxiang City, Jiaxing City, Zhejiang Province Patentee after: ZHEJIANG MAIZHI NETWORK TECHNOLOGY CO.,LTD. Address before: 310018 No. 2 street, Xiasha Higher Education Park, Hangzhou, Zhejiang, 928 Patentee before: ZHEJIANG SCI-TECH University |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20221221 Address after: 314500 Room 635-24, Fengrun International Business Center, Zhenxing East Road, wutong Street, Tongxiang City, Jiaxing City, Zhejiang Province Patentee after: JIAXING YUNSHIJIAO ELECTRONIC COMMERCE Co.,Ltd. Address before: Room 503, building 3, No. 133, development avenue, Tongxiang Economic Development Zone, Tongxiang City, Jiaxing City, Zhejiang Province Patentee before: ZHEJIANG MAIZHI NETWORK TECHNOLOGY CO.,LTD. |
|
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20231120 Address after: 314500 Room 306, Building 7, No. 333, Gongmao Avenue, Puyuan Town, Tongxiang, Jiaxing, Zhejiang Province Patentee after: Tongxiang Zhimeng Intellectual Property Operation Co.,Ltd. Address before: 314500 Room 635-24, Fengrun International Business Center, Zhenxing East Road, wutong Street, Tongxiang City, Jiaxing City, Zhejiang Province Patentee before: JIAXING YUNSHIJIAO ELECTRONIC COMMERCE Co.,Ltd. |