CN105650032A - Pressure expander of centrifugal compressor - Google Patents
Pressure expander of centrifugal compressor Download PDFInfo
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- CN105650032A CN105650032A CN201610189431.6A CN201610189431A CN105650032A CN 105650032 A CN105650032 A CN 105650032A CN 201610189431 A CN201610189431 A CN 201610189431A CN 105650032 A CN105650032 A CN 105650032A
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- 238000000926 separation method Methods 0.000 abstract description 13
- 230000002411 adverse Effects 0.000 abstract description 4
- 230000000149 penetrating effect Effects 0.000 abstract 1
- 238000009792 diffusion process Methods 0.000 description 6
- 238000009434 installation Methods 0.000 description 3
- 240000004859 Gamochaeta purpurea Species 0.000 description 1
- 241001397306 Proales Species 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
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- 238000005516 engineering process Methods 0.000 description 1
- 230000008676 import Effects 0.000 description 1
- 239000000411 inducer Substances 0.000 description 1
- 238000012423 maintenance Methods 0.000 description 1
- 238000005272 metallurgy Methods 0.000 description 1
- 238000005086 pumping Methods 0.000 description 1
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Classifications
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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
- F04D29/40—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
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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
- F04D29/40—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
- F04D29/46—Fluid-guiding means, e.g. diffusers adjustable
- F04D29/462—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps
- F04D29/464—Fluid-guiding means, e.g. diffusers adjustable especially adapted for elastic fluid pumps adjusting flow cross-section, otherwise than by using adjustable stator blades
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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
- F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
- F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
- F04D29/663—Sound attenuation
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- 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
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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 invention discloses a pressure expander of a centrifugal compressor. The structure of the pressure expander is improved, and high application value is achieved for further improving working performance of the pressure expander. A short blade is arranged in runners of every two adjacent long blades; the front edges of the long blades are curved surfaces and are arranged obliquely, and the included angles between front edge lines and the central axis of a wheel disc are 6 degrees to 8 degrees; the radius of curvature of the front edges of the long blades is gradually increased from the wheel disc to a wheel cover; each long blade is provided with three broken-line-shaped channels penetrating through a corresponding pressure surface and a corresponding suction surface; tail edge wing tips are arranged on the portions, located on the pressure surfaces, of the rear edges of the long blades. Occurrence of separation of airflow on the surfaces of the blades is restrained through the short blades in the runners of the adjacent long blades; the pressure differences between the pressure surfaces and the suction surfaces are reduced through the broken-line-shaped channels, the adverse pressure gradient is reduced, and separate airflow on boundary layers of the suction surfaces at the tails of part of the blades is effectively blown away; increase of wing tip vortexes generated by the pressure differences between the suction surfaces and the pressure surfaces on the rear edges of traditional wing-type blades can be restrained through parabola-shaped winglets on the tail edges.
Description
Technical field
The invention belongs to field of ventilation equipment, relate to centrifugal fan, be specifically related to the diffuser of a kind of centrifugal compressor.
Background technology
Centrifugal compressor is as a kind of energy conversion device, and it is mainly through the rotation of impeller, thus the motion of gas in impeller runner, is the energy of gas the changes mechanical energy of prime mover. Centrifugal compressor has high pressure, steady working condition wide ranges, simple in construction due to it, the feature such as is easily maintained, and is widely used in the industries such as oil, Aero-Space, metallurgy, chemical industry and mine, and plays an important role.
In centrifugal compressor, diffuser is generally divided into vaneless diffuser and vane diffuser two kinds. Vaneless diffuser is commonly constituted circular passage by two planomurals and is formed. Vaneless diffuser simple structure, cost is low, performance curve is mild, steady working condition is wider, and inefficient still inconspicuous when Mach number is higher, but in vaneless diffuser, flow angle is basically unchanged, air-flow moves substantially along helical line, flow path is longer, and friction loss is relatively big, and under design conditions efficiency lower than vane diffuser. General vaneless diffuser is everlasting to press in smaller compressor and is adopted. It is big that vane diffuser has diffusion degree, the feature that size is little, less than vaneless diffuser in the loss of design conditions downstream, thus efficiency is higher. Vane diffuser can pass through radius and increase deceleration diffusion, and radial blade can make flow angle desirably angular deflection simultaneously, makes circulation area strengthen further to improve diffusion ability; And it is improving efficiency and the level pressure ratio of centrifugal compressor, changes optimal working point position, expands stable operation range and play a very important role.
But vane diffuser is due to the existence of blade, variable working condition impact loss is relatively big, and efficiency declines substantially. Compressor is generally all operated under low discharge state, and under low discharge, diffuser vane inlet air flow forms high incidence, when the angle of attack reaches certain value, serious flow separation very easily occurs in runner. And once suction surface boundary-layer air-flow occurrence of large-area separates, very easily make compressor enter stall flutter state, thus having a strong impact on the job stability of electromotor. If flow is more than design discharge, easily there is choking phenomenon in vane diffuser throat again, make vane diffuser lose diffusion ability.
Generally for improving diffuser service behaviour, compressor can adopt airfoil blade, although wing blades is better than general version type Blade Properties, but the angle of attack becomes big and causes that efficiency declines when being still unavoidable from inhomogeneities and variable working condition due to impeller outlet air-flow, therefore, the basis of wing blades is improved the structure of diffuser, improves its service behaviour further and there is highly important using value and work prospect.
Summary of the invention
It is an object of the invention to the problem excessive for the diffuser intake air-flow angle of attack under low flow rate condition, the diffuser of a kind of centrifugal compressor is provided, this diffuser is arranged in the short blade of adjacent linear leaf runner and airflow direction can be guided to change, change the flow angle distribution in diffuser runner, more air-flow is enable to flow along air stream surface, suppress the generation of blade surface flow separation, so not only increase the work efficiency of diffuser, also increase working range. Fold-line-shaped conduit in diffuser can reduce 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 that the pressure differential of traditional airfoil trailing edge suction surface and pressure face produces, and makes the position that wingtip vortex comes off 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; Arranging a piece of short blade in the runner of adjacent two panels linear leaf, short blade is near the suction surface side of linear leaf. On same cross section, the costa section place of short blade suction surface is to take turns the radius of a circle 15��20mm less of the costa section place radius of a circle of linear leaf suction surface that disk center is the center of circle, and respectively 5 �� and 25 �� of central angle folded by the costa section of short blade suction surface and the costa section of adjacent two panels linear leaf suction surface; The entrance established angle of linear leaf is 32��36 ��, and the entrance established angle of short blade is 36��40 ��.
Described linear leaf adopts wing-shaped structure, and the linear leaf screwed hole that bolt is offered with linear leaf is connected, and is fixed on wheel disc by linear leaf; The leading edge of linear leaf is curved surface and is obliquely installed, and the angle of costa and wheel disc central axis is 6��8 ��; The leading edge radius of curvature of linear leaf is gradually increased along wheel disc to wheel cap direction. Linear leaf offers three fold-line-shaped conduits running through pressure face and suction surface. The shape of three fold-line-shaped conduits is identical, and the length direction along linear leaf is arranged side by side, and the length of three fold-line-shaped conduits is gradually reduced to trailing edge direction by the leading edge of linear leaf. Described fold-line-shaped conduit is two-part groove, and leading portion is air inlet section, and the groove width that back segment is air outlet section, air inlet section and air outlet section is equal, is 8��10mm; The air inlet section of three fold-line-shaped conduits enters arc length shared between the centrage of opening's edge linear leaf short transverse and linear leaf suction surface costa and accounts for 1/3,1/2 and the 2/3 of linear leaf suction surface arc length respectively.
On the longitudinal section of linear leaf, the air inlet section centrage relative vane molded line of fold-line-shaped conduit is 45 �� at the inclination angle with air inlet section centrage point of intersection tangent line, and air outlet section centrage relative vane molded line is 30 �� at the inclination angle with air outlet section centrage point of intersection tangent line.
The upper wall surface of fold-line-shaped conduit and distance is linear leaf height the 45��50% of linear leaf blade root, lower wall surface and distance is linear leaf height the 5��10% of linear leaf blade root.
The trailing edge of linear leaf is positioned at pressure face and is provided with trailing edge wingtip; The side of described trailing edge wingtip and the pressure face angle between the tangent plane at trailing edge place is 90 ��; The width value of trailing edge wingtip, along wheel disc to wheel cap direction regular increase parabolically, is 0 near wheel disc position width, and Breadth Maximum is less than the 5% of linear leaf chord length.
Described short blade adopts wedge structure, and short blade is welded on wheel disc; Short blade chord length is the 0.45��0.5 of linear leaf chord length, is highly the 0.6��0.7 of linear leaf; Suction surface at short blade all offers two arc shaped wing grooves with pressure face; Two arc shaped wing groove center lines of same side lay respectively at 1/3 and 2/3 place of short blade height; Described arc shaped wing groove near short blade leading edge end face and short blade costa distance is short blade chord length 1/8, arc shaped wing groove is near the end face of short blade trailing edge and distance is short blade chord length the 1/6 of short blade trailing edge; Described arc shaped wing groove is uiform section groove, and cross section semicircular in shape.
Improved by the long and short blade inlet angle of attack, the design of the fold-line-shaped conduit of linear leaf, the trailing edge wingtip of linear leaf and the arc shaped wing groove design of short blade optimize interior boundary layers and separate and the eddy airstream of afterbody, thus promoting diffuser efficiency.
Beneficial effects of the present invention:
The present invention can improve the problem of diffuser inlet air-flow angle of attack change under variable working condition, the short blade being arranged in adjacent linear leaf runner can guide airflow direction to change, change the flow angle distribution in diffuser runner, more air-flow is enable to flow along air stream surface, suppress the generation of blade surface flow separation, it is prevented that the generation of surge. The so not only reasonable range of operation of centrifugal fan, can improve diffusion ability and the operational efficiency of diffuser simultaneously. The incline structure of linear leaf leading edge makes the diffuser inlet diverse location in leaf height direction and impeller outlet keep different distance, adjusts from impeller high speed ternary air-flow out, especially reduces the gasflow mach number at diffuser inlet place, reduce impact loss. And the existence of short blade can effectively improve incident air flow angle when variable working condition. After air-flow enters diffuser runner, fold-line-shaped conduit in diffuser 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, thus reducing the area of boundary-layer Disengagement zone, increase the real area size of blade path, improve the flow of compressor. The parabola shaped winglet of trailing edge can suppress the growth of the wingtip vortex that the pressure differential of traditional airfoil trailing edge suction surface and pressure face produces, make the position that wingtip vortex comes off successively mobile, reduce the intensity of wingtip vortex, reduce aerodynamic noise, improve the performance that diffuser is overall.
Accompanying drawing explanation
Fig. 1 is the overall structure axonometric chart of the present invention;
Fig. 2 is long and short blade distribution schematic diagram 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 the partial enlarged drawing of Fig. 4;
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.
Detailed description of the invention
Below in conjunction with drawings and Examples, 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; Linear leaf 1 has 12, is evenly distributed on wheel disc; Arranging a piece of short blade 2 in the runner of adjacent two panels linear leaf 1, short blade 2 is near the suction surface side of linear leaf 1. On same cross section, the costa section place of short blade 2 suction surface is to take turns the radius of a circle 15mm less of the costa section place radius of a circle of linear leaf 1 suction surface that disk center is the center of circle, and central angle respectively ��=5 �� and ��=25 �� folded by the costa section of short blade 2 suction surface and the costa section of adjacent two panels linear leaf 1 suction surface;The entrance established angle of linear leaf 1 is ��3A1=32 ��, the entrance established angle of short blade 2 is ��3A2=36 ��.
Such as Fig. 3, shown in 4 and 5, linear leaf 1 adopts wing-shaped structure, and the linear leaf screwed hole 1-2 that bolt is offered with linear leaf 1 is connected, and is fixed on wheel disc 3 by linear leaf 1; The leading edge 1-1 of linear leaf is curved surface and is obliquely installed, and the angle of costa and wheel disc central axis is 6 ��; The leading edge radius of curvature of linear leaf is gradually increased along wheel disc to wheel cap direction. Linear leaf 1 offers three fold-line-shaped conduit 1-3 running through pressure face and suction surface. The shape of three fold-line-shaped conduits is identical, and the length direction along linear leaf 1 is arranged side by side, and the length of three fold-line-shaped conduits is gradually reduced to trailing edge direction by the leading edge of linear leaf 1. Fold-line-shaped conduit is two-part groove, and leading portion is air inlet section, and the groove width that back segment is air outlet section, air inlet section and air outlet section is 10mm; The air inlet section of three fold-line-shaped conduits enters arc length shared between the centrage of opening's edge linear leaf short transverse and linear leaf suction surface costa and accounts for 1/3,1/2 and the 2/3 of linear leaf 1 suction surface arc length respectively.
As shown in Figure 6, on the longitudinal section of linear leaf 1, the air inlet section centrage relative vane molded line of fold-line-shaped conduit is 45 �� at the inclination angle with air inlet section centrage point of intersection tangent line, and air outlet section centrage relative vane molded line is 30 �� at the inclination angle with air outlet section centrage point of intersection tangent line.
The upper wall surface of fold-line-shaped conduit and distance is linear leaf 1 height the 45% of linear leaf 1 blade root, lower wall surface and distance is linear leaf 1 height the 5% of linear leaf 1 blade root.
As it is shown in figure 5, the trailing edge of linear leaf is positioned at pressure face is provided with trailing edge wingtip 1-4; The side of trailing edge wingtip 1-4 and the pressure face angle between the tangent plane at trailing edge place is 90 ��; The width value of trailing edge wingtip 1-4, along wheel disc to wheel cap direction regular increase parabolically, is 0 near wheel disc position width, and Breadth Maximum is less than the 5% of linear leaf 1 chord length.
As it is shown in fig. 7, short blade 2 adopts wedge structure, short blade 2 is welded on wheel disc 3. Short blade 2 chord length is the 0.5 of linear leaf chord length, is highly the 0.7 of linear leaf 1; Suction surface at short blade 2 all offers two arc shaped wing groove 2-1 with pressure face; Two arc shaped wing groove center lines of same side lay respectively at 1/3 and 2/3 place of short blade 2 height; Arc shaped wing groove near short blade 2 leading edge end face and short blade 2 costa distance is short blade chord length 1/8, arc shaped wing groove is near the end face of short blade 2 trailing edge and distance is short blade 2 chord length the 1/6 of short blade 2 trailing edge; Arc shaped wing groove is uiform section groove, and cross section semicircular in shape.
Improved by the long and short blade inlet angle of attack, the design of the fold-line-shaped conduit of linear leaf, the trailing edge wingtip of linear leaf and the arc shaped wing groove design of short blade optimize interior boundary layers and separate and the eddy airstream of afterbody, thus promoting diffuser efficiency, specific as follows:
1, the long and short blade inlet angle of attack improves:
From diffuser efficiency computing formula, the efficiency of diffuser and the entrance of blade, exit installation angle, and blade inlet, outlet flow angle have in close relations, the entrance of usual blade, exit installation angle are changeless after having designed, and inlet air flow angle ��3Then change along with the change of flow rate working conditions, when flow increases, ��3Increase; When the flow if reduced, ��3Reduce. Now, existing for an entrance angle of attack i in diffuser inlet, the definition of entrance angle of attack i is as follows:
I=��3A-��3
In formula, ��3AEntrance established angle for blade;No matter i is just or is negative, and deviation 0 is more big, at blade surface, boundary layer separation all can occur. So in order to reduce flow separation in diffuser as far as possible, it should entrance angle of attack i is controlled in certain scope. Under low flow rate condition, due to inlet air flow angle ��3Only small, so entrance angle of attack i is very big, causes that the boundary layer separation district of blade suction surface expands rapidly, cause bigger eddy loss, time serious, cause surge phenomenon.
The present invention utilizes the design adding short blade in linear leaf runner to adjust inlet air flow angle ��3, under low discharge, especially relax the degree of entrance angle of attack i change. Diametrically, before short blade is positioned at linear leaf, in the circumferential near long diffuser suction surface. The entrance established angle �� of linear leaf3A1Entrance established angle �� than short blade3A2Little certain angle.
2, 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, particularly in nearly pumping point and nearly choke point, in diffuser, there is substantial amounts of flow separation and Secondary Flow phenomenon, windage loss is extremely serious, and diffuser efficiency declines to a great extent. The present invention provides a kind of design of fluting between linear leaf pressure face and suction surface, import and export under the effect of two ends differential static pressure at conduit, pressure face fraction can be inhaled in groove, after conduit accelerates, flowing out from suction surface channel outlet, this strand of air-flow can blow down certain blade suction surface boundary-layer separation bubble, controls and delay the extension of boundary-layer Disengagement zone, conduit be shaped as broken line type, be 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 distribution situation in diffuser runner. What conduit adopted is broken line type, air inlet section is front, air outlet section is rear, meet the proal feature of air-flow, and conduit UNICOM diffuser pressure face and suction surface, thus reduce the pressure differential of pressure face and suction surface, reduces adverse pressure gradient, not only increase the flow of compressor, and eddy current crack can be reduced.
3, the trailing edge wingtip of linear leaf and the arc shaped wing groove of short blade design:
Linear leaf trailing edge wingtip: due to the differential pressure action of airfoil fan afterbody suction surface and pressure face, the air-flow of pressure face can walk around trailing edge wingtip, produces eddy airstream at afterbody, and extends to blade surface, bring very big energy loss.
As shown in Figures 4 and 5, linear leaf trailing edge wingtip is distributed along leaf height parabolically type, top width, narrow base, mainly take into account exit flow and also has inhomogeneities along the distribution of leaf height. Wingtip structure can suppress the increase of wingtip vortex, reduces the intensity of wingtip vortex, reduces resistance. And the suppression of wingtip vortex also makes runner exit flowing more uniform, reduce flow losses. The present invention imitates the way of aircraft wing winglet, arranges trailing edge wingtip at linear leaf trailing edge, and trailing edge wingtip keeps vertical, according to diffuser vane surface pressure distribution feature with trailing edge.
Short blade arc shaped wing groove: same in order to control the boundary layer thickness on short blade surface, suppress the boundary layer separation on surface, reduce and separate whirlpool, suction surface at short blade is respectively provided with twice arc shaped wing groove with pressure face, arc shaped wing groove be shaped as circular arc, more conform to the feature of air motion, impact to prevent from inlet air flow is formed, make arc shaped wing groove be placed in the position of distance short blade leading edge certain distance.
Present invention is generally directed to the problem that under variable working condition state, the diffuser inlet air-flow angle of attack changes greatly, the short blade being arranged in adjacent linear leaf runner can guide airflow direction to change, change the flow angle distribution in diffuser runner, more air-flow is enable to flow along air stream surface, suppress the generation of blade surface flow separation, it is prevented that the generation of surge. So not only improve the reasonable range of operation of centrifugal fan, diffusion ability and the operational efficiency of diffuser can be improved simultaneously.
The incline structure that linear leaf leading edge adopts makes the distance that the diffuser inlet diverse location in leaf height direction is different from impeller outlet maintenance, have adjusted from impeller uneven air-flow out, greatly reduce the free stream Mach number at diffuser inlet place, improve the distribution of inlet air flow, reduce the impact loss of diffuser inlet, thus 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 has 12, is evenly distributed on wheel disc; Arranging a piece of short blade in the runner of adjacent two panels linear leaf, short blade is near the suction surface side of linear leaf; On same cross section, the costa section place of short blade suction surface is to take turns the radius of a circle 15��20mm less of the costa section place radius of a circle of linear leaf suction surface that disk center is the center of circle, and respectively 5 �� and 25 �� of central angle folded by the costa section of short blade suction surface and the costa section of adjacent two panels linear leaf suction surface; The entrance established angle of linear leaf is 32��36 ��, and the entrance established angle of short blade is 36��40 ��;
Described linear leaf adopts wing-shaped structure, and the linear leaf screwed hole that bolt is offered with linear leaf is connected, and is fixed on wheel disc by linear leaf; The leading edge of linear leaf is curved surface and is obliquely installed, and the angle of costa and wheel disc central axis is 6��8 ��; The leading edge radius of curvature of linear leaf is gradually increased along wheel disc to wheel cap direction; Linear leaf offers three fold-line-shaped conduits running through pressure face and suction surface; The shape of three fold-line-shaped conduits is identical, and the length direction along linear leaf is arranged side by side, and the length of three fold-line-shaped conduits is gradually reduced to trailing edge direction by the leading edge of linear leaf; Described fold-line-shaped conduit is two-part groove, and leading portion is air inlet section, and the groove width that back segment is air outlet section, air inlet section and air outlet section is equal, is 8��10mm; The air inlet section of three fold-line-shaped conduits enters arc length shared between the centrage of opening's edge linear leaf short transverse and linear leaf suction surface costa and accounts for 1/3,1/2 and the 2/3 of linear leaf suction surface arc length respectively;
On the longitudinal section of linear leaf, the air inlet section centrage relative vane molded line of fold-line-shaped conduit is 45 �� at the inclination angle with air inlet section centrage point of intersection tangent line, and air outlet section centrage relative vane molded line is 30 �� at the inclination angle with air outlet section centrage point of intersection tangent line;
The upper wall surface of fold-line-shaped conduit and distance is linear leaf height the 45��50% of linear leaf blade root, lower wall surface and distance is linear leaf height the 5��10% of linear leaf blade root;
The trailing edge of linear leaf is positioned at pressure face and is provided with trailing edge wingtip; The side of described trailing edge wingtip and the pressure face angle between the tangent plane at trailing edge place is 90 ��; The width value of trailing edge wingtip, along wheel disc to wheel cap direction regular increase parabolically, is 0 near wheel disc position width, and Breadth Maximum is less than the 5% of linear leaf chord length;
Described short blade adopts wedge structure, and short blade is welded on wheel disc; Short blade chord length is the 0.45��0.5 of linear leaf chord length, is highly the 0.6��0.7 of linear leaf; Suction surface at short blade all offers two arc shaped wing grooves with pressure face; Two arc shaped wing groove center lines of same side lay respectively at 1/3 and 2/3 place of short blade height; Described arc shaped wing groove near short blade leading edge end face and short blade costa distance is short blade chord length 1/8, arc shaped wing groove is near the end face of short blade trailing edge and distance is short blade chord length the 1/6 of short blade trailing edge; Described arc shaped wing groove is uiform section groove, and cross section semicircular in shape;
Improved by the long and short blade inlet angle of attack, the design of the fold-line-shaped conduit of linear leaf, the trailing edge wingtip of linear leaf and the arc shaped wing groove design of short blade optimize interior boundary layers and separate and the eddy airstream of afterbody, thus promoting diffuser efficiency.
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|---|---|---|---|
| CN201610189431.6A CN105650032B (en) | 2016-03-29 | 2016-03-29 | The diffuser of centrifugal compressor |
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| CN201610189431.6A CN105650032B (en) | 2016-03-29 | 2016-03-29 | The diffuser of centrifugal compressor |
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| CN105650032A true CN105650032A (en) | 2016-06-08 |
| CN105650032B CN105650032B (en) | 2017-11-07 |
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| CN106837867A (en) * | 2016-12-07 | 2017-06-13 | 浙江理工大学 | Axial flow blower 3 d impeller with leaf vein texture and splitterr vanes |
| CN107050542A (en) * | 2017-04-28 | 2017-08-18 | 浙江理工大学 | Minitype centrifugal blood pump and its circulation blood supply method that a kind of anti-haemocyte is damaged |
| CN107524630A (en) * | 2017-10-19 | 2017-12-29 | 江苏国泉泵业制造有限公司 | A kind of open type non-isometric blade impeller |
| KR20180007542A (en) * | 2016-07-13 | 2018-01-23 | 한화파워시스템 주식회사 | Diffuser for centrifugal compressor |
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| CN110230609A (en) * | 2018-03-05 | 2019-09-13 | 三菱重工业株式会社 | Impeller and centrifugal compressor with the impeller |
| CN112343864A (en) * | 2020-11-10 | 2021-02-09 | 江西省子轩科技有限公司 | Industrial application compressor unit |
| CN112955661A (en) * | 2019-07-22 | 2021-06-11 | 开利公司 | Centrifugal or mixed flow compressor comprising a suction diffuser |
| CN113187729A (en) * | 2021-04-29 | 2021-07-30 | 合肥工业大学 | Axial-flow pump for controlling eddy current and improving performance |
| CN113202789A (en) * | 2021-06-09 | 2021-08-03 | 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 |
| CN114856717A (en) * | 2022-06-02 | 2022-08-05 | 西安交通大学 | Novel exhaust diffuser structure with splitter plate and capable of enhancing pneumatic performance |
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| KR20180007542A (en) * | 2016-07-13 | 2018-01-23 | 한화파워시스템 주식회사 | Diffuser for centrifugal compressor |
| KR102560686B1 (en) | 2016-07-13 | 2023-07-27 | 한화파워시스템 주식회사 | Diffuser for centrifugal compressor |
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| CN107524630A (en) * | 2017-10-19 | 2017-12-29 | 江苏国泉泵业制造有限公司 | A kind of open type non-isometric blade impeller |
| 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 |
| CN110230609B (en) * | 2018-03-05 | 2020-12-15 | 三菱重工业株式会社 | Impeller and centrifugal compressor with same |
| CN110230609A (en) * | 2018-03-05 | 2019-09-13 | 三菱重工业株式会社 | Impeller and centrifugal compressor with the impeller |
| CN109026830A (en) * | 2018-08-16 | 2018-12-18 | 泛仕达机电股份有限公司 | A kind of centrifugal impeller |
| CN112955661A (en) * | 2019-07-22 | 2021-06-11 | 开利公司 | Centrifugal or mixed flow compressor comprising a suction diffuser |
| CN112343864A (en) * | 2020-11-10 | 2021-02-09 | 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 |
| CN113187729A (en) * | 2021-04-29 | 2021-07-30 | 合肥工业大学 | Axial-flow pump for controlling eddy current and improving performance |
| CN113202789A (en) * | 2021-06-09 | 2021-08-03 | 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 |
| CN114856717A (en) * | 2022-06-02 | 2022-08-05 | 西安交通大学 | Novel exhaust diffuser structure with splitter plate and capable of enhancing pneumatic performance |
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