CN101173680A - Forward-sweeping big and small blade transonic impeller and axial flow air compressor and inclined flow air compressor - Google Patents
Forward-sweeping big and small blade transonic impeller and axial flow air compressor and inclined flow air compressor Download PDFInfo
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- CN101173680A CN101173680A CNA2007101784020A CN200710178402A CN101173680A CN 101173680 A CN101173680 A CN 101173680A CN A2007101784020 A CNA2007101784020 A CN A2007101784020A CN 200710178402 A CN200710178402 A CN 200710178402A CN 101173680 A CN101173680 A CN 101173680A
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Abstract
The invention discloses a transonic impeller with forward-swept big and small blades and an axial-flow compressor and a diagonal-flow compressor; wherein, the transonic impeller with forward-swept big and small blades comprises a plurality of big blades. The invention is characterized in that: a small blade is arranged between the adjacent two big blades, and the front of the small blade is arranged at the rear end of the front of the big blade; the proportion between the string length of the small blade and the string length of the big blade is 0.3 to 0.85, and the apex of the front of the small blade is more protrudent forward than the root section. The invention has the advantages of not only inhibiting the separation of the rear end of the suction surface of the blade without influencing the circulation ability of the compressor, but also greatly improving the pressure ratio and the efficiency compared with the compressor of the prior art, and also improving the stalling margin.
Description
Technical field
The present invention relates to a kind of forward-sweeping big and small blade transonic impeller machine, relate in particular to a kind of forward-sweeping big and small blade transonic impeller and gas compressor.
Background technique
Gas compressor is a classification of turbomachine, and vane compressor generally is used for to gas boosting.The static impeller of a row that has the impeller of rotation of row's blade and back is called the one-level of gas compressor, when needs give gas boosting higher, usually adopt the mode of multistage compressor, for certain one-level wherein, can be divided into axial flow, centrifugal and diagonal flow type gas compressor by the gas flow form.Axial-flow compressor gas flow mode is axial admission, axial exhaust; Centrifugal-flow compressor gas flow mode is an axial admission, radially exhaust; The diagonal flow type gas compressor is the compromise of axial flow and centrifugal compressor, and axial admission and axially has the several angle exhaust.
As shown in Figure 1, gas compressor of the prior art is to adopt the identical blade of size along the circumferential direction evenly to distribute, and the passage that forms between blade and the blade is identical.In order to improve the boosting capability of axial flow compressor, need to increase the rotating speed of impeller of rotor, improve the flow velocity Supersonic that rotating speed causes the relative blade of compressor inlet place air-flow, thereby generation shock wave, the existence of shock wave can be played the effect of supercharging, but too strong shock wave can cause the blade face boundary layer separation to cause compressor efficiency to descend.
Therefore, mainly increase the gas compressor boosting capability in the prior art by adding the corner that flow of ambient air crosses behind the blade row.
Above-mentionedly have following shortcoming at least: the conduit degrees of expansion that forms between the adjacent blades is big, and the rear portion of blade suction surface is separated, and compressor efficiency is descended.Though increase the number of blade can eliminate or suppress the blade suction surface rear section from, the increase blade can make reducing of specific surface, thereby causes the decline of gas compressor negotiability.
Summary of the invention
The purpose of this invention is to provide a kind of rear section that can effectively suppress blade suction surface from, do not influence forward-sweeping big and small blade transonic impeller and the axial flow compressor and the inclined flow air compressor of gas compressor negotiability again.
The objective of the invention is to be achieved through the following technical solutions:
Forward-sweeping big and small blade transonic impeller of the present invention comprises a plurality of big blades, is provided with small leaf between adjacent two described big blades, and the leading edge of described small leaf is positioned at the rear portion of the leading edge of described big blade.
Axial flow compressor of the present invention, the driving wheel of this axial flow compressor are above-mentioned forward-sweeping big and small blade transonic impeller.
Inclined flow air compressor of the present invention, the driving wheel of this inclined flow air compressor are above-mentioned forward-sweeping big and small blade transonic impeller.
As seen from the above technical solution provided by the invention, forward-sweeping big and small blade transonic impeller of the present invention and axial flow compressor and inclined flow air compressor, because be provided with small leaf between adjacent two described big blades on the forward-sweeping big and small blade transonic impeller, the leading edge of described small leaf is positioned at the rear portion of the leading edge of described big blade.The rear section that can effectively suppress blade suction surface from, do not influence the gas compressor negotiability again.
Description of drawings
Fig. 1 is a stream condition schematic representation between the forward-sweeping big and small blade transonic impeller blade in the prior art;
Fig. 2 is a stream condition schematic representation between forward-sweeping big and small blade transonic impeller blade of the present invention;
Fig. 3 is the structural representation of forward-sweeping big and small blade transonic impeller of the present invention;
Fig. 4 is the large and small vane collocation schematic representation of forward-sweeping big and small blade transonic impeller of the present invention;
Fig. 5 is the structural representation of axial flow compressor of the present invention;
Fig. 6 is the structural representation of inclined flow air compressor of the present invention;
Fig. 7 is the performance comparison schematic representation of gas compressor of the present invention and gas compressor of the prior art.
Embodiment
Forward-sweeping big and small blade transonic impeller of the present invention, the embodiment that it is preferable such as Fig. 2, shown in Figure 3, forward-sweeping big and small blade transonic impeller is provided with a plurality of big blades 1, is provided with small leaf 2 between adjacent two big blades 1, and the leading edge of small leaf 2 is positioned at the rear portion of the leading edge of big blade 1.The trailing edge of small leaf 2 can be concordant with the trailing edge of big blade 1, also can omit trailing edge leading or backward and big blade 1.
The number of blade that is equivalent to make the forward-sweeping big and small blade transonic impeller rear portion like this doubles and the anterior number of blade is constant, can not reduce anterior actual internal area when control blade rear portion suction surface separates.There is inhibitory action at 2 pairs of big blades of small leaf, 1 suction surface rear portion because of the separation that diffusion causes.As can be seen from Figure 2, behind the adding small leaf, the unborn separation in big blade suction surface rear portion disappears.
As shown in Figure 4, the chord length of small leaf 2 is 0.3～0.85 with the ratio of the chord length of big blade 1, i.e. ratio 0.3＜Cs/C＜0.85 can be 0.3,0.4,0.5,0.65,0.85 etc.
In the different leaf eminences of blade, ratio C s/C can be different, can be optimized definite through pneumatic design software according to the gas compressor designing requirement.
The tip of the leading edge of small leaf 2 can be more outstanding forward than root, also can be more outstanding forward than the middle part, and also can be all outstanding forward form of tip and root.
Make the leading edge point of blade tip be called the sweepforward technology than root or than the structural feature that stretch out forward at the middle part, the sweepforward technology can make near the shock wave the leading edge more oblique, be equivalent to weaken shock strength, and can reduce near the load the blade tip leading edge, reduce leakage flow and suppress local boundary layer separation.
The leading edge of big blade also can adopt the sweepforward mode, and can adopt different sweepforward modes respectively with the leading edge that makes small leaf, and more Control Parameter make the gas compressor design more flexible, can design the better gas compressor of performance.
Axial flow compressor of the present invention, its preferable embodiment as shown in Figure 5, the driving wheel 4 of this axial flow compressor is above-mentioned forward-sweeping big and small blade transonic impeller, is installed in the casing 3 of axial flow compressor.
Inclined flow air compressor of the present invention, its preferable embodiment as shown in Figure 6, the driving wheel 6 of this inclined flow air compressor is above-mentioned forward-sweeping big and small blade transonic impeller, is installed in the casing 5 of inclined flow air compressor.
The present invention inserts small leaf between big blade, all bring the potentiality that rise appreciably for several critical performance parameters of gas compressor:
Aspect flow, have only big blade because of forward-sweeping big and small blade transonic impeller of the present invention front portion, the gas compressor of the prior art of the more identical boosting capability of circulation area is big, so negotiability is big.In addition, being positioned at big blade inlet edge small leaf afterwards adopts the sweepforward technology can allow the inlet air flow relative Mach number reduce perpendicular to the component on shock wave corrugated, interfere the boundary layer thickness that causes to increase even the local detachment bubble thereby weakened shock wave-boundary layer, this also can increase the negotiability of gas compressor.
Aspect pressure ratio, the existence of rear portion small leaf has suppressed the boundary layer separation at big blade suction surface rear portion, thereby can design the stronger gas compressor of the bigger expanding ability of corner, pressure ratio gas compressor height more of the prior art.
Aspect efficient, foregoing Mach number ahead of shock reduces reduces shock loss; Shock wave-boundary layer interferes the local detachment that causes to weaken, thereby separation losses is reduced; Boundary layer separation reduced near the existence of rear portion small leaf made big blade suction surface trailing edge, and separation losses reduces.The loss of these three aspects reduces to make the efficient gas compressor height more of the prior art of big and small blade compressor, though the long-pending increase of the blade of big and small blade compressor and air-flow contact surface can cause the frictional loss that some are extra, but to account for the ratio of total losses very little in this part loss, do not play a major role.
As shown in Figure 7, be the gas compressor performance curve of a specific embodiment of the present invention and the performance curve comparison diagram of gas compressor of the prior art, the pressure ratio of gas compressor of the present invention as can be seen and efficient all have significantly raising than gas compressor of the prior art, and stall margin also increases.
The above; only for the preferable embodiment of the present invention, but protection scope of the present invention is not limited thereto, and anyly is familiar with those skilled in the art in the technical scope that the present invention discloses; the variation that can expect easily or replacement all should be encompassed within protection scope of the present invention.
Claims (10)
1. a forward-sweeping big and small blade transonic impeller comprises a plurality of big blades, it is characterized in that, is provided with small leaf between adjacent two described big blades, and the leading edge of described small leaf is positioned at the rear portion of the leading edge of described big blade.
2. forward-sweeping big and small blade transonic impeller according to claim 1 is characterized in that, the chord length of described small leaf is 0.3～0.85 with the ratio of the chord length of described big blade.
3. forward-sweeping big and small blade transonic impeller according to claim 1 is characterized in that, the chord length of described small leaf is 0.5～0.65 with the ratio of the chord length of described big blade.
4. forward-sweeping big and small blade transonic impeller according to claim 1 is characterized in that, the tip of the leading edge of described small leaf is more outstanding forward than root.
5. forward-sweeping big and small blade transonic impeller according to claim 1 is characterized in that, the tip of the leading edge of described small leaf is more outstanding forward than the middle part.
6. forward-sweeping big and small blade transonic impeller according to claim 1 is characterized in that, the tip of the leading edge of described small leaf and root are more outstanding forward than the middle part.
7. according to claim 4,5 or 6 described forward-sweeping big and small blade transonic impellers, it is characterized in that the tip of the leading edge of described big blade is than root or more outstanding forward than the middle part.
8. according to each described forward-sweeping big and small blade transonic impeller of claim 1 to 6, it is characterized in that the trailing edge of described small leaf is concordant with described big vane trailing edge.
9. an axial flow compressor is characterized in that, the driving wheel of this axial flow compressor is each described forward-sweeping big and small blade transonic impeller of claim 1 to 8.
10. an inclined flow air compressor is characterized in that, the driving wheel of this inclined flow air compressor is each described forward-sweeping big and small blade transonic impeller of claim 1 to 8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007101784020A CN100494696C (en) | 2007-11-29 | 2007-11-29 | Forward-sweeping big and small blade transonic impeller and axial flow air compressor and inclined flow air compressor |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNB2007101784020A CN100494696C (en) | 2007-11-29 | 2007-11-29 | Forward-sweeping big and small blade transonic impeller and axial flow air compressor and inclined flow air compressor |
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| Publication Number | Publication Date |
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| CN101173680A true CN101173680A (en) | 2008-05-07 |
| CN100494696C CN100494696C (en) | 2009-06-03 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNB2007101784020A Expired - Fee Related CN100494696C (en) | 2007-11-29 | 2007-11-29 | Forward-sweeping big and small blade transonic impeller and axial flow air compressor and inclined flow air compressor |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102889237A (en) * | 2012-06-12 | 2013-01-23 | 中国科学院工程热物理研究所 | Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor |
| CN105090098A (en) * | 2014-05-09 | 2015-11-25 | 贵州航空发动机研究所 | Transonic fan rotor blade |
| CN106321508A (en) * | 2016-10-28 | 2017-01-11 | 广东威灵电机制造有限公司 | Mixed flow impeller, mixed flow fan and vacuum cleaner |
-
2007
- 2007-11-29 CN CNB2007101784020A patent/CN100494696C/en not_active Expired - Fee Related
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102889237A (en) * | 2012-06-12 | 2013-01-23 | 中国科学院工程热物理研究所 | Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor |
| CN102889237B (en) * | 2012-06-12 | 2015-04-22 | 中国科学院工程热物理研究所 | Blade wheel with large blades and small blades applying front edges with sharp corners and air compressor |
| CN105090098A (en) * | 2014-05-09 | 2015-11-25 | 贵州航空发动机研究所 | Transonic fan rotor blade |
| CN106321508A (en) * | 2016-10-28 | 2017-01-11 | 广东威灵电机制造有限公司 | Mixed flow impeller, mixed flow fan and vacuum cleaner |
Also Published As
| Publication number | Publication date |
|---|---|
| CN100494696C (en) | 2009-06-03 |
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Granted publication date: 20090603 Termination date: 20101129 |