CN101822855A - Serial cascade stator structure of artificial heart blood pump - Google Patents
Serial cascade stator structure of artificial heart blood pump Download PDFInfo
- Publication number
- CN101822855A CN101822855A CN 201010170698 CN201010170698A CN101822855A CN 101822855 A CN101822855 A CN 101822855A CN 201010170698 CN201010170698 CN 201010170698 CN 201010170698 A CN201010170698 A CN 201010170698A CN 101822855 A CN101822855 A CN 101822855A
- Authority
- CN
- China
- Prior art keywords
- blade
- seat
- back row
- stator
- 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.)
- Granted
Links
Images
Abstract
The invention relates to a serial cascade stator structure of an artificial heart blood pump. The serial cascade stator structure comprises an expanding hub passageway and stator blades thereof; the expanding hub passageway adopts a streamline cubic spline curve passageway; the stator blades are composed of five blades at the front row and five blade at the rear row; a certain clearance is remained between the front edge of the blade at the rear row and the trailing edge of the blade at the front row; and the blades at the front and rear rows of the stator blades are arranged in the circumferential position structure as follows: the root part and the tip part of the front edge of the blade at the rear row are located at 35% of a circumferential angle between the blades at the front row. The structure design of the invention has higher blood-supply and pressure rising capability, can obtain better flow field distribution, improve the anti-hemolysis properties of the blood pump, and meet the requirement for embedding in heart failure patients in a short time or a long time.
Description
Technical field
The present invention relates to a kind of serial cascade stator structure of artificial heart blood pump, belong to the technical field of comprehensive turbomachine technology and Medical Technology.
Background technology
Heart failure is the late stage of various heart disease development, is directly threatening increasing patient's life.The method of treatment heart failure mainly contains at present: Drug therapy, surgical operation, mechanical assistance circulation, heart transplantation, cell transplantation etc.Drug therapy has accounted for the overwhelming majority wherein, but heavier when the state of an illness, or even cardiac function forfeiture time, just must take heart transplantation to give treatment to.Yet the Therapeutic Method of heart transplantation has bigger limitation, mainly is because the healthy heart quantity that is used to transplant seldom and be difficult in time obtain, and may produce rejection and opportunistic infection after the operation.So artificial mechanical blood pump, that is: artificial heart has very big demand.
Artificial mechanical blood pump is divided into according to working mechanism and the different of structure: the vane type blood pump of pulsating blood pump and rotary Continuous Flow.With respect to the pulsating blood pump, that the vane type blood pump of rotary Continuous Flow has is simple in structure, be easy to make, need not to install advantage such as artificial valve.The vane type blood pump is further divided into vane type axial flow blood pump, propeller type centrofugal blood pump and vane type mixed flow blood pump again.Vane type axial flow blood pump is compared the propeller type centrofugal blood pump, has that volume is little, priming volume is little, to advantages such as the blood destructiveness are light, and is more suitable for implant into body.
In the design of vane type axial flow blood pump, not only to consider to satisfy the blood supply voltage rise demand of human body fundamental need, and to consider the anti-hemolysis performance of blood pump, the conveying of oxygen is finished by erythrocyte in the blood circulation process, excessive shearing stress can make the cell membrane of erythrocyte tear, intracellular hemoglobin is free in blood plasma, causes the oxygen carrying capacity forfeiture of erythrocyte, so-called haemolysis that Here it is.A large amount of haemolysis can cause sanguimotor oxygen exchange capacity to decline to a great extent, and causes anemia, the serious entail dangers to life of going back.Cause hemolytic factor to have a lot, but intrinsic reason is the dynamic behavior of blood.Existing studies show that, haemolysis appear in the blood flow that does not meet physiological requirement, as turbulent flow, and eddy current, shearing force district etc.Can the haemolysis quality be successfully applied to the clinical crucial effects that all has for blood pump.
Vane type axial flow blood pump mainly partly is made up of stator part, rotor portion and stator, and wherein the stator part has not only played the effect of rectification blood Way out, and certain effect has been played in the voltage rise that improves blood.In blood flow in the process of blood pump, blood has higher speed and deflection angle after rotor flows out, stator is in the face of abominable condition for import like this, bad flow phenomenons such as eddy current and backflow very easily appear, and then initiation haemolysis problem, this point confirms by numerical simulation result and blood pump zoopery result, so the design quality of stator has very big influence to the anti-hemolysis performance of blood pump.Therefore it is essential to say that structure advanced person, stator reasonable in design can be successfully applied to the clinical artificial heart blood pump one.
The tandem cascade technology that is applied at the axial flow compressor or the centrifugal compressor parts of aero-engine can play inhibition, postpone the isolating effect of flowing, especially under the bigger situation of fluid deflection, effect is more obvious, and it uses efficient and the performance that has improved compressor effectively.In the stator design of vane type axial flow blood pump, so far but not based on the tandem cascade structure Design, substantially all be single general stator structure design, even the outlet of the blood pump behind stator position adds row's blade again, purpose also mainly is further to lead flowing of straight blood outlet, plays the effect of rear guide vane.The blood pump stator of general structure partly adopts row's blade to bear bigger blood flow turning angle, the defective of this structure is by the stator part, the blood flow of the high speed of rotor outlet, large deflection angle is transferred in the process of axial flow stably, have angular deflection near 70 °-80 °, thereby separation problems such as eddy current, refluence very easily appear, thereby can cause the haemolysis problem, have influence on the anti-hemolysis performance of blood pump.
Summary of the invention
The object of the present invention is to provide a kind of serial cascade stator structure of artificial heart blood pump, shown in Fig. 1 b, the tandem cascade structure that five stator blades of general blood pump stator structure design is divided into row's blade behind five front-seat blades and five, runner section has adopted fairshaped cubic spline curve, and the blade tip diameter of two kinds of structures is 12.7mm among the figure.Purpose of design is to make stator part not only can have higher blood supply voltage rise ability, and can obtain Flow Field Distribution preferably, improves the anti-hemolysis performance of blood pump, satisfies it in short-term or implant the intravital requirement of heart failure patient for a long time in future.
Technical scheme of the present invention mainly comprise following some:
A kind of serial cascade stator structure of artificial heart blood pump is characterized in that: this serial cascade stator structure comprises stator wheel hub runner and stator blade thereof:
1, stator wheel hub runner has adopted fairshaped cubic spline curve runner, shown in Fig. 4 a label 8.This streamline channel has prevented the sudden expansion of pressure, help suppressing mobile separation in the stator blade district, the streamlined stator wheel hub of cubic spline axial range is shown in Fig. 4 a label 13, this cubic spline curve interpolation point meridian coordinate is as follows, abscissa is the interpolation knot axial coordinate, vertical coordinate is an interpolation knot in the exhibition of vertical axial to the direction coordinate, and unit is m:
(0.01250，0.00525)，(0.01358，0.00525)，(0.01500，0.00522)，(0.01787，0.00512)，(0.01969，0.00504)，(0.02176，0.00488)，(0.02387，0.00463)，(0.02679，0.00399)，(0.02887，0.00324)，(0.03073，0.00246)，(0.03207，0.00202)，(0.03230，0.00200)；
2, stator blade part is made up of row's blade 3 behind five front-seat blades 2 and five, leave certain interval between back row's blade inlet edge 11 and the front-seat blade trailing edge 10, on meridian and cascade structure view (Fig. 4 a, b), indicated each blade parameter implication, front-seat blade inlet edge 9 and front-seat blade trailing edge 10 are respectively 5.25mm and 5.07mm at the radius of front-seat root of blade 4, and front-seat blade inlet edge 9 and front-seat blade trailing edge 10 are 6.35mm at the radius of front-seat blade tip 6; Back row's blade inlet edge 11 and back row's blade trailing edge 12 are respectively 5.06mm and 4.43mm at the radius of back row's root of blade 5, and back row's blade inlet edge 11 and back row's blade trailing edge 12 are 6.35mm at the radius of back row's blade tip 7.Front-seat blade inlet edge 9 and front-seat blade trailing edge 10 are in the leading edge blade angles of front-seat root of blade 4
1With the trailing edge blade angles
2Be respectively-70.20 ° and-18.70 °, front-seat blade inlet edge 9 and front-seat blade trailing edge 10 are in the leading edge blade angles of front-seat blade tip 6
1With the trailing edge blade angles
2Be respectively-60.3 ° and-31.2 °; Back row's blade inlet edge 11 and back row's blade trailing edge 12 are in the leading edge blade angles of back row's root of blade 5
1With the trailing edge blade angles
2Be respectively-39.1 ° and 11.5 °, back row's blade inlet edge 11 and back row's blade trailing edge 12 are in the leading edge blade angles of back row's blade tip 7
1With the trailing edge blade angles
2Be respectively-30.3 ° and 8.9 °.Front-seat blade angle β
yAt front-seat root of blade 4 is-47.7 °, is-48.8 ° in front-seat blade tip 6; Back row's blade angle β
yRow's root of blade 5 is-13.7 ° in the back, and row's blade tip 7 is-10.6 ° in the back.The axial length of front-seat root of blade 4 is 6.48mm, and the axial length of front-seat blade tip 6 is 6.28mm; The axial length of back row's root of blade 5 is 5.74mm, and the axial length of back row's blade tip 7 is 5.74mm.Forward and backward row's blade parameter value can be referring to table 1.The definition of angle direction with the relative blood pump of this angle direction axially (from the stator importer to pointing to Way out) be the dextrorotation veer for just.
Table 1. serial cascade stator front and rear row blade geometry parameter
Front-seat root of blade blade angles
HubDistribute and adopt two sections cubic spline curve matches to obtain respectively, the meridian axial length value that abscissa is is benchmark with front-seat blade inlet edge point, unit is m; Vertical coordinate is the root blade angles
HubValue, unit is °.At front-seat root of blade: the interpolation knot coordinate of first section cubic spline curve is: (0.00000 ,-70.7), (0.00046 ,-67.2), (0.00092 ,-64.0), (0.00137 ,-59.1); The interpolation knot coordinate of second section cubic spline curve is: (0.00137 ,-59.1), (0.00309 ,-42.2), (0.00480 ,-29.3), (0.00648 ,-18.7).Front-seat blade tip blade angles
TipDistribute and adopt two sections cubic spline curve matches to obtain respectively, the meridian axial length value that abscissa is is benchmark with front-seat blade inlet edge point, unit is m; Vertical coordinate is the tip blade angles
TipValue, unit is °.In front-seat blade tip: the interpolation knot coordinate of first section cubic spline curve is: (0.00000 ,-60.5), (0.00044 ,-59.1), (0.00089 ,-57.7), (0.00133 ,-56.5); The interpolation knot coordinate of second section cubic spline curve is: (0.00133 ,-56.5), (0.00298 ,-48.7), (0.00463 ,-40.7), (0.00628 ,-31.3).
Back row's root of blade blade angles
HubWith the tip blade angles
TipDistribute and adopt the cubic spline curve match to obtain, the meridian axial length value that abscissa is is benchmark with front-seat blade inlet edge point, unit is m; Vertical coordinate is respectively the root blade angles
HubWith the tip blade angles
Tip, unit is °.Arrange root of blade in the back: the interpolation knot coordinate of cubic spline curve is: (0.00676 ,-39.1), (0.00876 ,-20.0), (0.01070 ,-3.7), (0.01254,12.1).Arrange blade tip in the back: the interpolation knot coordinate of cubic spline curve is: (0.00676 ,-30.3), (0.00867 ,-16.5), (0.01059 ,-3.7), (0.01250,9.4).
The stator blade thickness of the present invention also blood pump stator blade than general is thinner, and the stator thickness here is with the vertical dimension definition of blade profile surface point to mean camber line.Stator blade thickness in the general structure is 0.4mm～2.0mm, and front and rear row stator blade thickness is in the structure of the present invention: 0.50mm～0.76mm.The thickness distribution of front-seat blade and back row's blade all adopts the cubic spline curve match to obtain.Abscissa is to be the meridian axial length value of benchmark with the leading edge point, and unit is m; Vertical coordinate is for adopting the vane thickness of blade profile surface point to the vertical dimension definition of mean camber line, and unit is m.Front-seat root of blade interpolation knot coordinate is: (0.00000,0.00055), (0.00087,0.00062), (0.00231,0.00070), (0.00407,0.00069), (0.00549,0.00063), (0.00649,0.00056); Front-seat blade tip interpolation knot coordinate is: (0.00000,0.00060), (0.00138,0.00070), (0.00283,0.00076), (0.00471,0.00072), (0.00628,0.00060).Back row's root of blade interpolation knot coordinate is: (0.00675,0.00048), (0.00804,0.00054), (0.01038,0.00058), (0.01150,0.00056), (0.01256,0.00050); Back row's blade tip interpolation knot coordinate is: (0.00674,0.00052), (0.00854,0.00058), (0.01008,0.00060), (0.01079,0.00059), (0.01250,0.00052).
3, the front and rear row blade of stator blade is in the circumferential position configuration aspects: back row's blade inlet edge is equal circumferential 35% positions of angle between front-seat two blades in root and tip, because wheel hub is a surface of revolution structure, be reflected on the unfolded TWO-DIMENSIONAL CASCADE structure chart (Fig. 5 a, b): along the surface of revolution arc of vertical axial on direction, back row's blade mean camber line leading edge point to the arc of front-seat blade mean camber line extended line to length L
1The arc that accounts for front-seat blade two adjacent blade mean camber lines is 35% to the ratio of distance L: i.e. L
1/ L=0.35 (L
1Be on the same meridian axial location with L, calculate L
1The time get the adjacent back row's blade of pressure face front-seat blade be benchmark).
The present invention is a kind of serial cascade stator structure of artificial heart blood pump, its advantage and effect are: the tandem cascade structure that 5 stator blades of general structural design is divided into front-seat 5 blades and 5 blades of back row designs respectively, stator wheel hub runner in the present invention's design has adopted the streamlined curve of slick cubic spline simultaneously, the wheel hub runner adopts mild interim form, especially in the stator blade district, the expansion of runner is more releived; Structural design of the present invention not only can have higher blood supply voltage rise ability, and can obtain Flow Field Distribution preferably, improves the anti-hemolysis performance of blood pump, satisfies it in short-term or implant the intravital requirement of heart failure patient for a long time in future.
Description of drawings
Fig. 1 a is depicted as the schematic three dimensional views of single stator blade in the prior art
Fig. 1 b is depicted as serial cascade stator structure schematic three dimensional views of the present invention
Fig. 2 a is depicted as prior art and stator part voltage rise of the present invention-rating curve contrast sketch map
Fig. 2 b is depicted as prior art and stator part total pressure recovery coefficient of the present invention-rating curve contrast sketch map
Fig. 3 a1 is depicted as 10% exhibition in prior art stator blade district to the high flow field sketch map of leaf
Fig. 3 a2 is depicted as 50% exhibition in prior art stator blade district to the high flow field sketch map of leaf
Fig. 3 b1 is depicted as 10% exhibition in stator blade of the present invention district to the high flow field sketch map of leaf
Fig. 3 b2 is depicted as 50% exhibition in stator blade of the present invention district to the high flow field sketch map of leaf
Fig. 4 a is depicted as the meridian structure two-dimensional representation of stator part of the present invention
Fig. 4 b is depicted as the TWO-DIMENSIONAL CASCADE channel design sketch map of stator part of the present invention
Fig. 5 a is depicted as the TWO-DIMENSIONAL CASCADE passage root structure sketch map of stator part of the present invention
Fig. 5 b is depicted as the TWO-DIMENSIONAL CASCADE passage tip configuration sketch map of stator part of the present invention
Concrete label and symbol are as follows among the figure:
1: stator blade; 2: front-seat blade; 3: back row's blade; 4: front-seat root of blade; 5: back row's root of blade;
6: front-seat blade tip; 7: back row's blade tip; 8: stator wheel hub runner;
9: front-seat blade inlet edge; 10: front-seat blade trailing edge; 11: back row's blade inlet edge; 12: back row's blade trailing edge;
13: the streamlined stator wheel hub of cubic spline axial range;
β
y: established angle (string of a musical instrument and axial angle, to axial for clockwise direction for just);
β
1: the leading edge blade angle (mean camber line is at leading edge point tangent line and axial angle, to axial for clockwise direction for just);
β
2: the trailing edge blade angle (mean camber line is at trailing edge point tangent line and axial angle, to axial for clockwise direction for just);
β
Hub: the root of blade blade angle (the root of blade mean camber line is at this tangent line and axial angle, to axial for clockwise direction for just);
β
Tip: the blade tip blade angle (the blade tip mean camber line is at this tangent line and axial angle, to axial for clockwise direction for just);
L
1: along the surface of revolution arc of vertical axial on direction, back row's blade mean camber line leading edge point to the arc of front-seat blade mean camber line extended line to length; L: on direction, the arc of front-seat blade two adjacent blade mean camber lines (is annotated: L to distance along the surface of revolution arc of vertical axial
1Be in same axial location with L, calculate L
1The time get the adjacent back row's blade of pressure face front-seat blade be benchmark).
The specific embodiment
Below in conjunction with drawings and Examples technical scheme of the present invention is described further.
A kind of serial cascade stator structure of artificial heart blood pump is characterized in that: this serial cascade stator structure comprises stator wheel hub runner and stator blade thereof
1, stator wheel hub runner has adopted fairshaped cubic spline curve runner, shown in Fig. 4 a label 8.This streamline channel has prevented the sudden expansion of pressure, help suppressing mobile separation in the stator blade district, the streamlined stator wheel hub of cubic spline axial range is shown in Fig. 4 a label 13, this cubic spline curve interpolation point meridian coordinate is as follows, abscissa is the interpolation knot axial coordinate, vertical coordinate is an interpolation knot in the exhibition of vertical axial to the direction coordinate, and unit is m:
(0.01250，0.00525)，(0.01358，0.00525)，(0.01500，0.00522)，(0.01787，0.00512)，(0.01969，0.00504)，(0.02176，0.00488)，(0.02387，0.00463)，(0.02679，0.00399)，(0.02887，0.00324)，(0.03073，0.00246)，(0.03207，0.00202)，(0.03230，0.00200)；
2, stator blade part is made up of row's blade 3 behind five front-seat blades 2 and five, leave certain interval between back row's blade inlet edge 11 and the front-seat blade trailing edge 10, on meridian and cascade structure view (Fig. 4 a, b), indicated each blade parameter implication, front-seat blade inlet edge 9 and front-seat blade trailing edge 10 are respectively 5.25mm and 5.07mm at the radius of front-seat root of blade 4, and front-seat blade inlet edge 9 and front-seat blade trailing edge 10 are 6.35mm at the radius of front-seat blade tip 6; Back row's blade inlet edge 11 and back row's blade trailing edge 12 are respectively 5.06mm and 4.43mm at the radius of back row's root of blade 5, and back row's blade inlet edge 11 and back row's blade trailing edge 12 are 6.35mm at the radius of back row's blade tip 7.Front-seat blade inlet edge 9 and front-seat blade trailing edge 10 are in the leading edge blade angles of front-seat root of blade 4
1With the trailing edge blade angles
2Be respectively-70.20 ° and-18.70 °, front-seat blade inlet edge 9 and front-seat blade trailing edge 10 are in the leading edge blade angles of front-seat blade tip 6
1With the trailing edge blade angles
2Be respectively-60.3 ° and-31.2 °; Back row's blade inlet edge 11 and back row's blade trailing edge 12 are in the leading edge blade angles of back row's root of blade 5
1With the trailing edge blade angles
2Be respectively-39.1 ° and 11.5 °, back row's blade inlet edge 11 and back row's blade trailing edge 12 are in the leading edge blade angles of back row's blade tip 7
1With the trailing edge blade angles
2Be respectively-30.3 ° and 8.9 °.Front-seat blade angle β
yAt front-seat root of blade 4 is-47.7 °, is-48.8 ° in front-seat blade tip 6; Back row's blade angle β
yRow's root of blade 5 is-13.7 ° in the back, and row's blade tip 7 is-10.6 ° in the back.The axial length of front-seat root of blade 4 is 6.48mm, and the axial length of front-seat blade tip 6 is 6.28mm; The axial length of back row's root of blade 5 is 5.74mm, and the axial length of back row's blade tip 7 is 5.74mm.Forward and backward row's blade parameter value can be referring to table 1.The definition of angle direction with the relative blood pump of this angle direction axially (from the stator importer to pointing to Way out) be the dextrorotation veer for just.
Table 1. serial cascade stator front and rear row blade geometry parameter
Front-seat root of blade blade angles
HubDistribute and adopt two sections cubic spline curve matches to obtain respectively, the meridian axial length value that abscissa is is benchmark with front-seat blade inlet edge point, unit is m; Vertical coordinate is the root blade angles
HubValue, unit is °.At front-seat root of blade: the interpolation knot coordinate of first section cubic spline curve is: (0.00000 ,-70.7), (0.00046 ,-67.2), (0.00092 ,-64.0), (0.00137 ,-59.1); The interpolation knot coordinate of second section cubic spline curve is: (0.00137 ,-59.1), (0.00309 ,-42.2), (0.00480 ,-29.3), (0.00648 ,-18.7).Front-seat blade tip blade angles
TipDistribute and adopt two sections cubic spline curve matches to obtain respectively, the meridian axial length value that abscissa is is benchmark with front-seat blade inlet edge point, unit is m; Vertical coordinate is the tip blade angles
TipValue, unit is °.In front-seat blade tip: the interpolation knot coordinate of first section cubic spline curve is: (0.00000 ,-60.5), (0.00044 ,-59.1), (0.00089 ,-57.7), (0.00133 ,-56.5); The interpolation knot coordinate of second section cubic spline curve is: (0.00133 ,-56.5), (0.00298 ,-48.7), (0.00463 ,-40.7), (0.00628 ,-31.3).
Back row's root of blade blade angles
HubWith the tip blade angles
TipDistribute and adopt the cubic spline curve match to obtain, the meridian axial length value that abscissa is is benchmark with front-seat blade inlet edge point, unit is m; Vertical coordinate is respectively the root blade angles
HubWith the tip blade angles
Tip, unit is °.Arrange root of blade in the back: the interpolation knot coordinate of cubic spline curve is: (0.00676 ,-39.1), (0.00876 ,-20.0), (0.01070 ,-3.7), (0.01254,12.1).Arrange blade tip in the back: the interpolation knot coordinate of cubic spline curve is: (0.00676 ,-30.3), (0.00867 ,-16.5), (0.01059 ,-3.7), (0.01250,9.4).
The thickness distribution of front-seat blade and back row's blade all adopts the cubic spline curve match to obtain.Abscissa is to be the meridian axial length value of benchmark with the leading edge point, and unit is m; Vertical coordinate is for adopting the vane thickness of blade profile surface point to the vertical dimension definition of mean camber line, and unit is m.Front-seat root of blade interpolation knot coordinate is: (0.00000,0.00055), (0.00087,0.00062), (0.00231,0.00070), (0.00407,0.00069), (0.00549,0.00063), (0.00649,0.00056); Front-seat blade tip interpolation knot coordinate is: (0.00000,0.00060), (0.00138,0.00070), (0.00283,0.00076), (0.00471,0.00072), (0.00628,0.00060).Back row's root of blade interpolation knot coordinate is: (0.00675,0.00048), (0.00804,0.00054), (0.01038,0.00058), (0.01150,0.00056), (0.01256,0.00050); Back row's blade tip interpolation knot coordinate is: (0.00674,0.00052), (0.00854,0.00058), (0.01008,0.00060), (0.01079,0.00059), (0.01250,0.00052).
3, the front and rear row blade of stator blade is in the circumferential position configuration aspects: back row's blade inlet edge is equal circumferential 35% positions of angle between front-seat two blades in root and tip, because wheel hub is a surface of revolution structure, be reflected on the unfolded TWO-DIMENSIONAL CASCADE structure chart (Fig. 5 a, b): along the surface of revolution arc of vertical axial on direction, back row's blade mean camber line leading edge point to the arc of front-seat blade mean camber line extended line to length L
1The arc that accounts for front-seat blade two adjacent blade mean camber lines is 35% to the ratio of distance L: i.e. L
1/ L=0.35 (L
1Be on the same meridian axial location with L, calculate L
1The time get the adjacent back row's blade of pressure face front-seat blade be benchmark).
Adopt turbomachine computational fluid dynamics (CFD) numerical simulation software NUMECA (NUMECA company commonly used, Belgium) calculating the back confirms, the boost in pressure ability of stator part improves along with the increase of rotor speed, and this is because stator is pressure potential with blood in the Conversion of energy that rotor portion obtains.In the characteristic line contrast of Fig. 2 a, b, in the prior art, be in when rotor speed under the situation of 12000rpm, the voltage rise performance of the serial cascade stator that it is 11000rpm, 10000rpm and 9000rpm that the voltage rise performance of its general structure stator but is lower than rotor rotating speed of the present invention, especially in volume flow hour, the advantage of boosting of serial cascade stator structure is more obvious.And in most flow region scope, the total pressure recovery coefficient of serial cascade stator all is higher than the total pressure recovery coefficient of general structure stator; Fig. 3 a1, a2 are as seen, can flow backwards and the problem of eddy current to the leaf high position to leaf high position and 50% exhibition in 10% exhibition of general structure stator, and these problems have all obtained effective control after using this serial cascade stator invention structure, shown in Fig. 3 b1, b2.
Claims (2)
1. the serial cascade stator structure of an artificial heart blood pump, this serial cascade stator structure comprises stator wheel hub runner and stator blade thereof, it is characterized in that:
Stator wheel hub runner, adopted fairshaped cubic spline curve runner, this streamline channel has prevented the sudden expansion of pressure, help suppressing mobile separation in the stator blade district, this cubic spline curve interpolation point meridian coordinate is as follows, abscissa is the interpolation knot axial coordinate, and vertical coordinate is an interpolation knot in the exhibition of vertical axial to the direction coordinate, and unit is m:
(0.01250，0.00525)，(0.01358，0.00525)，(0.01500，0.00522)，(0.01787，0.00512)，(0.01969，0.00504)，(0.02176，0.00488)，(0.02387，0.00463)，(0.02679，0.00399)，(0.02887，0.00324)，(0.03073，0.00246)，(0.03207，0.00202)，(0.03230，0.00200)；
Stator blade part is formed by arranging blade (3) behind five front-seat blades (2) and five, leave certain interval between back row's blade inlet edge (11) and the front-seat blade trailing edge (10), front-seat blade inlet edge (9) and front-seat blade trailing edge (10) are respectively 5.25mm and 5.07mm at the radius of front-seat root of blade (4), and front-seat blade inlet edge (9) and front-seat blade trailing edge (10) are 6.35mm at the radius of front-seat blade tip (6); Back row's blade inlet edge (11) and back row's blade trailing edge (12) are respectively 5.06mm and 4.43mm at the radius of back row's root of blade (5), and back row's blade inlet edge (11) and back row's blade trailing edge (12) are 6.35mm at the radius of back row's blade tip (7); Front-seat blade inlet edge (9) and front-seat blade trailing edge (10) are in the leading edge blade angles of front-seat root of blade (4)
1With the trailing edge blade angles
2Be respectively-70.20 ° and-18.70 °, front-seat blade inlet edge (9) and front-seat blade trailing edge (10) are in the leading edge blade angles of front-seat blade tip (6)
1With the trailing edge blade angles
2Be respectively-60.3 ° and-31.2 °; Back row's blade inlet edge (11) and back row's blade trailing edge (12) are in the leading edge blade angles of back row's root of blade (5)
1With the trailing edge blade angles
2Be respectively-39.1 ° and 11.5 °, back row's blade inlet edge (11) and back row's blade trailing edge (12) are in the leading edge blade angles of back row's blade tip (7)
1With the trailing edge blade angles
2Be respectively-30.3 ° and 8.9 °, front-seat blade angle β
yAt front-seat root of blade (4) is-47.7 °, is-48.8 ° in front-seat blade tip (6); Back row's blade angle β
yAt back row's root of blade (5) is-13.7 °, is-10.6 ° in back row's blade tip (7), and the axial length of front-seat root of blade (4) is 6.48mm, and the axial length of front-seat blade tip (6) is 6.28mm; The axial length of back row's root of blade (5) is 5.74mm, and the axial length of back row's blade tip (7) is 5.74mm.
2. the serial cascade stator structure of artificial heart blood pump according to claim 1, it is characterized in that: the front and rear row blade of described stator blade is on the circumferential position structure: back row's blade inlet edge is equal circumferential 35% positions of angle between front-seat two blades in root and tip, because wheel hub is a surface of revolution structure, be reflected on the unfolded TWO-DIMENSIONAL CASCADE structure chart: along the surface of revolution arc of vertical axial on direction, back row's blade mean camber line leading edge point to the arc of front-seat blade mean camber line extended line to length L
1The arc that accounts for front-seat blade two adjacent blade mean camber lines is 35% to the ratio of distance L, wherein, and L
1Be on the same meridian axial location with L, calculate L
1The time the front-seat blade got be the front-seat blade of the adjacent back of pressure face row's blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101706983A CN101822855B (en) | 2010-05-06 | 2010-05-06 | Serial cascade stator structure of artificial heart blood pump |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2010101706983A CN101822855B (en) | 2010-05-06 | 2010-05-06 | Serial cascade stator structure of artificial heart blood pump |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN101822855A true CN101822855A (en) | 2010-09-08 |
| CN101822855B CN101822855B (en) | 2012-09-19 |
Family
ID=42687157
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN2010101706983A Expired - Fee Related CN101822855B (en) | 2010-05-06 | 2010-05-06 | Serial cascade stator structure of artificial heart blood pump |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN101822855B (en) |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103206402A (en) * | 2013-04-02 | 2013-07-17 | 武汉科技大学 | Embeddable two-stage axial flow blood pump rotor structure |
| US10722631B2 (en) | 2018-02-01 | 2020-07-28 | Shifamed Holdings, Llc | Intravascular blood pumps and methods of use and manufacture |
| US11185677B2 (en) | 2017-06-07 | 2021-11-30 | Shifamed Holdings, Llc | Intravascular fluid movement devices, systems, and methods of use |
| US11511103B2 (en) | 2017-11-13 | 2022-11-29 | Shifamed Holdings, Llc | Intravascular fluid movement devices, systems, and methods of use |
| WO2023280245A1 (en) * | 2021-07-07 | 2023-01-12 | 上海焕擎医疗科技有限公司 | Impeller of cardiac assistance device, and cardiac assistance device |
Families Citing this family (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2022540616A (en) | 2019-07-12 | 2022-09-16 | シファメド・ホールディングス・エルエルシー | Intravascular blood pump and methods of manufacture and use |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5588812A (en) * | 1995-04-19 | 1996-12-31 | Nimbus, Inc. | Implantable electric axial-flow blood pump |
| US5707218A (en) * | 1995-04-19 | 1998-01-13 | Nimbus, Inc. | Implantable electric axial-flow blood pump with blood cooled bearing |
| WO2000043054A2 (en) * | 1999-01-26 | 2000-07-27 | Nimbus, Inc. | Blood pump with profiled outflow region |
| JP2003260128A (en) * | 2002-03-07 | 2003-09-16 | Mitsubishi Heavy Ind Ltd | Artificial cardiac pump |
| CN201150675Y (en) * | 2007-12-29 | 2008-11-19 | 同济大学附属东方医院 | Pump and machine unifying implanted axial flow blood pump channel structure |
| CN201437016U (en) * | 2009-03-26 | 2010-04-14 | 同济大学附属东方医院 | Implanted ventricular assist device |
-
2010
- 2010-05-06 CN CN2010101706983A patent/CN101822855B/en not_active Expired - Fee Related
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5588812A (en) * | 1995-04-19 | 1996-12-31 | Nimbus, Inc. | Implantable electric axial-flow blood pump |
| US5707218A (en) * | 1995-04-19 | 1998-01-13 | Nimbus, Inc. | Implantable electric axial-flow blood pump with blood cooled bearing |
| WO2000043054A2 (en) * | 1999-01-26 | 2000-07-27 | Nimbus, Inc. | Blood pump with profiled outflow region |
| JP2003260128A (en) * | 2002-03-07 | 2003-09-16 | Mitsubishi Heavy Ind Ltd | Artificial cardiac pump |
| CN201150675Y (en) * | 2007-12-29 | 2008-11-19 | 同济大学附属东方医院 | Pump and machine unifying implanted axial flow blood pump channel structure |
| CN201437016U (en) * | 2009-03-26 | 2010-04-14 | 同济大学附属东方医院 | Implanted ventricular assist device |
Non-Patent Citations (3)
| Title |
|---|
| 《中国生物医学工程学报》 20070220 张岩等 运用三维数值模拟对人工心脏轴流血泵的设计和改进 35-41 1-2 第26卷, 第01期 2 * |
| 《中国生物医学工程学报》 20080220 张岩等 一种新型轴流式心脏辅助血泵的研制和初步的动物实验 97-101 1-2 第27卷, 第01期 2 * |
| 《航空动力学报》 20091015 冯秀莲等 叶片弯掠对压气机静子叶片气动性能影响的三维数值模拟 2338-2343 1-2 第24卷, 第10期 2 * |
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103206402A (en) * | 2013-04-02 | 2013-07-17 | 武汉科技大学 | Embeddable two-stage axial flow blood pump rotor structure |
| CN103206402B (en) * | 2013-04-02 | 2015-11-25 | 武汉科技大学 | A kind of implantable two-stage axial flow blood pump rotor structure |
| US11185677B2 (en) | 2017-06-07 | 2021-11-30 | Shifamed Holdings, Llc | Intravascular fluid movement devices, systems, and methods of use |
| US11511103B2 (en) | 2017-11-13 | 2022-11-29 | Shifamed Holdings, Llc | Intravascular fluid movement devices, systems, and methods of use |
| US10722631B2 (en) | 2018-02-01 | 2020-07-28 | Shifamed Holdings, Llc | Intravascular blood pumps and methods of use and manufacture |
| US11229784B2 (en) | 2018-02-01 | 2022-01-25 | Shifamed Holdings, Llc | Intravascular blood pumps and methods of use and manufacture |
| WO2023280245A1 (en) * | 2021-07-07 | 2023-01-12 | 上海焕擎医疗科技有限公司 | Impeller of cardiac assistance device, and cardiac assistance device |
Also Published As
| Publication number | Publication date |
|---|---|
| CN101822855B (en) | 2012-09-19 |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN101822854B (en) | Front diversing flow rotor structure with tapping splitter blades for artificial heart blood pump | |
| CN101822855B (en) | Serial cascade stator structure of artificial heart blood pump | |
| CN103206402B (en) | A kind of implantable two-stage axial flow blood pump rotor structure | |
| EP1996252B1 (en) | Heart assist device with expandable impeller pump | |
| US20170087288A1 (en) | Non-occluding intravascular blood pump providing reduced hemolysis | |
| EP4190376A1 (en) | Catheter pump assembly including a stator | |
| CN105498002A (en) | Blood pumping impeller | |
| CN212651227U (en) | Magnetic suspension blood pump device | |
| US20230330410A1 (en) | Impeller and ventricular assist device | |
| CN111637090A (en) | Pump rotor | |
| CN108661947A (en) | Using the axial flow compressor blade of Condar jet and using its axial flow compressor | |
| CN2754637Y (en) | Impeller of heart pump for preventing hemolysis and thrombus | |
| CN111643755A (en) | Low-hemolysis-rate heart pump based on three-base point-line bearing | |
| CN115999044B (en) | Pump impeller and auxiliary blood circulation device | |
| CN2558386Y (en) | Spiral mixed-flow impeller for auxiliary ventricle blood pump | |
| CN106122107A (en) | Complex bend stator blade for multi stage axial flow compressor | |
| CN212490962U (en) | Low-hemolysis-rate heart pump based on three-base point-line bearing | |
| Throckmorton et al. | Twisted cardiovascular cages for intravascular axial flow blood pumps to support the Fontan physiology | |
| CN212940997U (en) | Pump rotor | |
| CN114432588A (en) | Aorta puncture type axial flow type blood pump with folded edge blade structure | |
| CN218220816U (en) | Impeller and ventricle auxiliary device | |
| CN201209588Y (en) | Pump and machine two-in-one embedded axial blood pump rotor blade structure | |
| CN107456617B (en) | Implanted axial flow blood pump without rear guide vane | |
| Kuban et al. | Total artificial heart incorporating novel stacked motor; first in vivo results | |
| CN213116830U (en) | Pump rotor |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C10 | Entry into substantive examination | ||
| SE01 | Entry into force of request for substantive examination | ||
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20120919 Termination date: 20170506 |
|
| CF01 | Termination of patent right due to non-payment of annual fee |