CN102889237A - Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor - Google Patents
Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor Download PDFInfo
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- CN102889237A CN102889237A CN2012101933897A CN201210193389A CN102889237A CN 102889237 A CN102889237 A CN 102889237A CN 2012101933897 A CN2012101933897 A CN 2012101933897A CN 201210193389 A CN201210193389 A CN 201210193389A CN 102889237 A CN102889237 A CN 102889237A
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Abstract
The invention discloses a blade wheel with large blades and small blades applying front edges with sharp corners and an air compressor. The blade wheel comprises the large blades and the small blades, wherein the front edges of the large blades and the front edges of the small blades have sharp corner structures; the blade wheel is of an axial flow type or a radial flow type; the blades comprise the large blades and the small blades; and the front edges of the large blades are the sharp corners, or the small blades can be also provided with the sharp corners, or the front edges of the large blades and the front edges of the small edges are the sharp corners. The front edges of the blades are the sharp corners, the sizes and the strength of a horseshoe vortex and a channel vortex can be reduced, secondary flow loss is reduced, total pressure loss is reduced, and the flow efficiency is improved; and moreover, stress concentration at the front edges of the blades is reduced.
Description
Technical field
The invention belongs to pneumatic, the structural design of turbomachine of field of fluid machinery, relate to a kind of blade impellers mechanical device, relate in particular to a kind of big and small blade impeller and gas compressor thereof of application band wedge angle leading edge.
Background technique
Miniature gas turbine is the low profile thermal force engine, its single-machine capacity scope is 25～500kW, its basic principle is identical with conventional gas turbine, and basic technical features is to adopt radial flow impeller machinery (centrifugal-flow compressor and inward flow turbine) and backheat circulation.Modern miniature gas turbine is as the major impetus machine of distributing-supplying-energy system, compares with other power equipment to have many advantages.That modern advanced micro fuel engine has is simple in structure, can separate unit use or many integrated, be fit to a series of advanced technology features such as pluralities of fuel, the high and low discharging of the thermal efficiency, low noise, low vibration, low maintenance rate, automaticity height, provide cleaning, safety, reliably and the best mode of high quality energy supply.
On the basis of guaranteeing the stable effectively work of miniature gas turbine, the efficient that improves gas turbine becomes gas turbine research outline.In several large parts of gas turbine, the efficient of gas compressor is relatively low, also is a key factor that affects overall efficiency.There is the clearance leakage loss usually in compressor part, secondary flow loss etc., because the gas compressor internal flow is relatively complicated, the efficient that how to improve gas compressor is a great problem that the artificer faces.At present, the working speed of miniature gas turbine is relatively high, so that compressor blade is subject to the strength problem that centrifugal force causes when bearing Pneumatic immpacting, root of blade and this problem of wheel disc jointing place are especially outstanding.
The secondary flow loss that exists in the gas compressor is caused by horseshoe vortex, Passage Vortex etc. usually.Because main flow field and place, near wall boundary layer, there is certain pressure gradient radially, radially mobile towards wall at the effect next part air-flow of this pressure gradient, form horseshoe vortex, cause secondary flow loss, horseshoe vortex produces in the jointing place of blade and wall usually.Because the pressure of pressure side has caused along circumferential pressure gradient greater than the pressure of suction surface in the gas compressor.When moving along passage, air-flow produces certain centrifugal force, when air-flow velocity is larger, this centrifugal force can the balance pressure gradient, and at the near wall place because the impact in boundary layer, airspeed is relatively low, and the centrifugal force of generation can't the balance pressure gradient, thereby causes the circumferential lateral flow in edge of air-flow, namely form Passage Vortex, caused secondary flow loss.
As fully visible, reduce secondary flow loss, improve circulation efficiency, improving blade strength is the problem that gas compressor is pneumatic and structural design is mainly considered.The present invention proposes one to the impeller of blade inlet edge and wall joint appropriate design, at blade inlet edge a wedge angle is set.The existence of this wedge angle has improved the airspeed in blade and wall jointing place, and the raising of the airspeed of blade and wall jointing place has suppressed along the formation of blade surface pressure gradient, and this pressure gradient namely is to cause the main cause of horseshoe vortex and Passage Vortex.Thereby this invention can reduce intensity and the size of the horseshoe vortex of blade profile leading edge, can reduce simultaneously the intensity of Passage Vortex, improves flow efficiency, reduces secondary flow loss, thereby so that since the pitot loss that Passage Vortex causes can reduce accordingly.
Summary of the invention
Purpose of the present invention is to lack for domestic miniature gas turbine radial-flow type Machine Design experience, for improving the impeller flow efficiency, reduces aerodynamic loss, increases blade strength, and effectively increasing the service life provides a kind of Impeller Design scheme.
The present invention has designed a kind of impeller with the wedge angle leading edge, in described compressor blade leading edge a kind of horn structure is set.Because the existence of this horn structure has improved the airspeed of blade and wall jointing place on the one hand, has reduced intensity and the size of horseshoe vortex, can reduce the intensity of Passage Vortex simultaneously, thereby so that the pitot loss that causes owing to Passage Vortex can reduce accordingly; The jointing place of blade inlet edge and wall also is the weakness zone of Intensity Design on the other hand, and the intensity of blade inlet edge and wall jointing place has been strengthened in the existence of this structure, and the stress concentration phenomenon is improved.
In order to achieve the above object, the present invention adopts following technical solution:
A kind of big and small blade impeller of application band wedge angle leading edge comprises a plurality of large and small blades and wheel disc, and described large blade and small leaf space are arranged, it is characterized in that,
Extend a wedge angle in the leading edge of described large blade and/or small leaf and the jointing place of wheel disc, described wedge angle comprises pressure side and suction surface, and it is arc that the pressure side of described wedge angle and suction surface all are:
The jointing place that the pressure side of described wedge angle originates in described wedge angle and wheel disc is extended a segment distance and is intersected to the pressure side place of blade, and it is crossing to the suction surface place of blade that a segment distance is extended in the jointing place that the suction surface of described wedge angle originates in described wedge angle and wheel disc;
The length of described wedge angle is greater than its height, its highly be the leaf of blade high 5%～10%.
Preferably, when the leading edge of only having small leaf arranged wedge angle, the leading edge of described large blade can be common rounding.Or when the leading edge of only having large blade arranged wedge angle, the leading edge of described small leaf can be common rounding.
Preferably, the pressure side of described wedge angle and the suction surface projection plane on the wheel card all is incomplete ellipse, and namely pressure side and the suction surface projection plane on the wheel card all is an oval-shaped part.
Further, the pressure side of described wedge angle and the separating surface between the suction surface are arranged on leaf development stagnation place, and namely described separating surface is crossed the stagnation line of blade.
Further, the suction surface of described wedge angle is long at the oval-shaped major axis at projection plane its place of oval-shaped major axis specific pressure face on the wheel card at its place, projection plane on the wheel card, and the suction surface of described wedge angle is long at the oval-shaped minor axis at projection plane its place of oval-shaped minor axis specific pressure face on the wheel card at its place, projection plane on the wheel card.
Further, be connected with the suction surface leading edge place smooth transition of wedge angle of the pressure side of described wedge angle connects.
Further, the pressure side of described wedge angle and suction surface, the separating surface place smooth transition between the two connects.
Further, the pressure side of described wedge angle is at the ellipse at its place, projection plane on the wheel card and the ellipse at projection plane its place of suction surface on the wheel card, and two oval-shaped elliptical center points do not overlap.
Preferably, the big and small blade impeller of described application band wedge angle leading edge is axial flow or radial flow impeller.
The present invention is claimed a kind of gas compressor also, and it comprises the big and small blade impeller of above-mentioned application band wedge angle leading edge.
Advantage of the present invention:
(1) blade inlet edge pointed design of the present invention is simple in structure, and design is convenient, is fit to engineering and uses.
(2) the present invention suppresses the Secondary Flow effect significantly, to the improvement of root stress situation obviously.By in impeller, using the blade with the wedge angle leading edge, reduced on the one hand size and the intensity of horseshoe vortex, Passage Vortex, reduced Secondary Flow, improved the flow efficiency of impeller; The stress that has reduced on the other hand root of blade is concentrated, and has improved the intensity of root of blade, has improved the useful working life of blade.
Description of drawings
Fig. 1 centrifugal compressor meridian schematic cross-section;
The axles such as Fig. 2 centrifugal compressor are surveyed view and with the CONSTRUCTED SPECIFICATION figure of wedge angle leading edge blade;
Fig. 3 sharp corner details enlarged view.
Embodiment
For making purpose of the present invention, technological scheme and advantage clearer, referring to the accompanying drawing embodiment that develops simultaneously, the present invention is described in more detail.
The invention provides a kind of big and small blade impeller and gas compressor of application band wedge angle leading edge, the meridian schematic cross-section of described centrifugal compressor rotor, as shown in Figure 1.Described gas compressor is by mainly being comprised of blade 1, impeller 2.Described gas compressor is at when work and the certain blade tip clearance of casing 3 formation.Described compressor blade 1 is divided into large blade 101 and small leaf 102, and large blade 101 and small leaf 102 spaces are arranged, extend a wedge angle 7 at the blade inlet edge of described small leaf 102 and the jointing place of wheel disc.Described small leaf 102 is divided into pressure side 11 and suction surface 12 by stagnation line 42.Described wedge angle 7 is divided into wedge angle pressure side 72 and wedge angle suction surface 74 by separating surface 76.
In actual applications, can adopt wedge angle 7 longitudinally to extend in the leading edge of small leaf 102, the leading edge at small leaf 102 extends along short transverse equally.Separating surface 76 designs usually at leaf development stagnation place, i.e. the common stagnation line 42 of crossing small leaf of separating surface.The pressure side 72 of wedge angle 7 is arc, and place, outside extension one segment distance that originates in wedge angle 7 intersects to pressure side 11 places of small leaf 102.The suction surface 74 of wedge angle 7 also is arc, and place, outside extension one segment distance that originates in wedge angle 7 intersects to suction surface 12 places of small leaf 10.The length of wedge angle 7 is greater than its height, and the height of wedge angle 7 can be in 5%～10% high value of leaf.
Shown in Figure 3, the projection on the wheel card of the pressure side 72 of wedge angle 7 and suction surface 74 in fact all is incomplete ellipse, all is an oval-shaped part.The elliptical center point (Css) of suction surface 74 projections, minor axis length (Sss), long axis length (Lss).The elliptical center point (Cps) of pressure side 72 projections, minor axis length (Sps), long axis length (Lps).The suction surface 74 of wedge angle and the main axis of pressure side 72 are on separating surface 76.The major axis of the major axis specific pressure face 72 of suction surface 74 will be grown (Lss＞Lps).The minor axis length on the projection plane of the minor axis specific pressure face 72 on the projection plane of suction surface 74 (Sss＞Sps).Oval-shaped pressure side 72 and suction surface 74 be at place, the outside of wedge angle 7, i.e. leading edge place, and smooth transition connects.In actual mechanical process, do mid point with Css and Cps respectively and make elliptic arc, adopt identical curvature in two oval jointing places, get final product to guarantee their tangent.
The above only is preferred embodiment of the present invention, and is in order to limit the present invention, within the spirit and principles in the present invention not all, any modification of making, is equal to replacement, improvement etc., all should be included within the scope of the present invention.
Claims (10)
1. an application comprises a plurality of large and small blades and wheel disc with the big and small blade impeller of wedge angle leading edge, and described large blade and small leaf space are arranged, it is characterized in that,
Extend a wedge angle in the leading edge of described large blade and/or small leaf and the jointing place of wheel disc, described wedge angle comprises pressure side and suction surface, and it is arc that the pressure side of described wedge angle and suction surface all are:
The jointing place that the pressure side of described wedge angle originates in described wedge angle and wheel disc is extended a segment distance and is intersected to the pressure side place of blade, and it is crossing to the suction surface place of blade that a segment distance is extended in the jointing place that the suction surface of described wedge angle originates in described wedge angle and wheel disc;
The length of described wedge angle is greater than its height, its highly be the leaf of blade high 5% ~ 10%.
2. the big and small blade impeller of application band wedge angle leading edge according to claim 1 is characterized in that, when the leading edge of only having small leaf arranged wedge angle, the leading edge of described large blade can be common rounding.
3. the big and small blade impeller of application band wedge angle leading edge according to claim 1 is characterized in that, when the leading edge of only having large blade arranged wedge angle, the leading edge of described small leaf can be common rounding.
4. according to claim 1 to the big and small blade impeller of 3 each described application band wedge angle leading edges, it is characterized in that, the pressure side of described wedge angle and the suction surface projection plane on the wheel card all is incomplete ellipse, and namely pressure side and the suction surface projection plane on the wheel card all is an oval-shaped part.
5. according to claim 1 to the big and small blade impeller of 3 each described application band wedge angle leading edges, it is characterized in that the pressure side of described wedge angle and the separating surface between the suction surface are arranged on leaf development stagnation place, namely described separating surface is crossed the stagnation line of blade.
6. the big and small blade impeller of application band wedge angle leading edge according to claim 4, it is characterized in that, the suction surface of described wedge angle is long at the oval-shaped major axis at projection plane its place of oval-shaped major axis specific pressure face on the wheel card at its place, projection plane on the wheel card, and the suction surface of described wedge angle is long at the oval-shaped minor axis at projection plane its place of oval-shaped minor axis specific pressure face on the wheel card at its place, projection plane on the wheel card.
7. the big and small blade impeller of application band wedge angle leading edge according to claim 4 is characterized in that, be connected with the suction surface leading edge place smooth transition of wedge angle of the pressure side of described wedge angle connects.
8. the big and small blade impeller of application band wedge angle leading edge according to claim 4 is characterized in that, the pressure side of described wedge angle and suction surface, and the separating surface place smooth transition between the two connects.
9. the big and small blade impeller of application band wedge angle leading edge according to claim 4, it is characterized in that, the pressure side of described wedge angle is at the ellipse at its place, projection plane on the wheel card and the ellipse at projection plane its place of suction surface on the wheel card, and two oval-shaped elliptical center points do not overlap.
10. a gas compressor is characterized in that, comprises the big and small blade impeller of each described application band wedge angle leading edge of claim 1 to 9.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201210193389.7A CN102889237B (en) | 2012-06-12 | 2012-06-12 | Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor |
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| Application Number | Priority Date | Filing Date | Title |
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| CN201210193389.7A CN102889237B (en) | 2012-06-12 | 2012-06-12 | Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor |
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| CN102889237A true CN102889237A (en) | 2013-01-23 |
| CN102889237B CN102889237B (en) | 2015-04-22 |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104989672B (en) * | 2015-06-19 | 2017-06-23 | 中国航空动力机械研究所 | A kind of treated casing structure and compressor for improving one-stage centrifugal compressor surge nargin |
| CN110185631A (en) * | 2019-04-18 | 2019-08-30 | 西安热工研究院有限公司 | The symmetrical overcritical working medium closed centrifugal compressor set of partial admission and method |
| CN110185632A (en) * | 2019-04-18 | 2019-08-30 | 西安热工研究院有限公司 | The overcritical working medium semi-open type centrifugal compressed device and method of changeable flow |
| CN114963483A (en) * | 2021-02-20 | 2022-08-30 | 浙江盾安人工环境股份有限公司 | Liquid separator |
| CN115977996A (en) * | 2023-03-17 | 2023-04-18 | 潍柴动力股份有限公司 | Impeller of air compressor, air compressor and turbocharger |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104989672B (en) * | 2015-06-19 | 2017-06-23 | 中国航空动力机械研究所 | A kind of treated casing structure and compressor for improving one-stage centrifugal compressor surge nargin |
| CN110185631A (en) * | 2019-04-18 | 2019-08-30 | 西安热工研究院有限公司 | The symmetrical overcritical working medium closed centrifugal compressor set of partial admission and method |
| CN110185632A (en) * | 2019-04-18 | 2019-08-30 | 西安热工研究院有限公司 | The overcritical working medium semi-open type centrifugal compressed device and method of changeable flow |
| CN110185632B (en) * | 2019-04-18 | 2024-05-17 | 西安热工研究院有限公司 | Variable-flow supercritical working medium semi-open centrifugal compression device and method |
| CN110185631B (en) * | 2019-04-18 | 2024-05-28 | 西安热工研究院有限公司 | Symmetrical local air inlet supercritical working medium closed centrifugal compressor unit and method |
| CN114963483A (en) * | 2021-02-20 | 2022-08-30 | 浙江盾安人工环境股份有限公司 | Liquid separator |
| CN115977996A (en) * | 2023-03-17 | 2023-04-18 | 潍柴动力股份有限公司 | Impeller of air compressor, air compressor and turbocharger |
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| CN102889237B (en) | 2015-04-22 |
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