CN114135521A - Centrifugal Compressor Stage Tandem Diffuser - Google Patents
Centrifugal Compressor Stage Tandem Diffuser Download PDFInfo
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- CN114135521A CN114135521A CN202111545119.3A CN202111545119A CN114135521A CN 114135521 A CN114135521 A CN 114135521A CN 202111545119 A CN202111545119 A CN 202111545119A CN 114135521 A CN114135521 A CN 114135521A
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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
- F04D29/52—Casings; Connections of working fluid for axial pumps
- F04D29/54—Fluid-guiding means, e.g. diffusers
- F04D29/541—Specially adapted for elastic fluid pumps
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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
- F04D17/00—Radial-flow pumps, e.g. centrifugal pumps; Helico-centrifugal pumps
- F04D17/08—Centrifugal pumps
- F04D17/10—Centrifugal pumps for compressing or evacuating
- F04D17/12—Multi-stage pumps
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Abstract
The invention relates to a centrifugal compressor stage serial diffuser which is sequentially provided with a diffuser radial front row blade, a diffuser axial rear row main blade and a diffuser axial rear row splitter blade which are fixedly connected with a diffuser hub and a diffuser casing respectively along the airflow direction; the tail edge of a radial front row of blades of the diffuser extends to the bending section of the meridian flow channel, and the radial front row of blades of the diffuser is used for changing radial flow into axial flow in the bending section in advance; the tail edge of the radial front row of blades of the diffuser is close to the front edge of the axial rear row of main blades of the diffuser, and a flow channel gap is arranged between the tail edge of the radial front row of blades of the diffuser and the front edge of the axial rear row of main blades of the diffuser; the invention obviously inhibits the backflow at the outlet casing of the centrifugal impeller, and the flow field is more uniform.
Description
Technical Field
The invention belongs to the field of miniature turbojet centrifugal compressors, and particularly relates to a diffuser structure of a compressor.
Background
The stationary elements of a multistage centrifugal compressor have a significant impact on the overall aerodynamic performance. With the continuous and intensive research on the centrifugal compressor, researchers find that when a static element is not properly designed, the flow loss is large, and sometimes the total pressure recovery coefficient of a diffuser of the centrifugal compressor is even 0.85. Further improvements in the performance of centrifugal compressor stages require that flow losses in the stationary elements be minimized, and therefore the design and optimization of stationary component passages is also one of the issues that have been the focus of research to improve the aerodynamic performance of centrifugal compressors.
The conventional micro-turbojet centrifugal compressor stage diffuser is generally configured in such a way that a radial diffuser and an axial diffuser are separately arranged, flow separation and the like exist behind a blunt trailing edge of the radial diffuser, and if the axial diffuser is not ideal in design, the flow loss is usually large.
The conventional centrifugal compressor stage radial diffuser and the conventional centrifugal compressor stage axial diffuser of the small turbojet engine are two-dimensional blades, and the blade profiles at the upper end wall and the lower end wall are basically the same. The radial diffuser is generally wedge-shaped, and the axial diffuser is generally constrained by the axial size, so that the torsion of the airflow is large, and the difference of the inlet angle and the outlet angle is large. Therefore, flow separation and the like often exist behind the radial diffuser, flow in the passage of the axial diffuser is very complex, and the flow separation, the large velocity gradient and the like can generate adverse effects on the flow field. In addition, the traditional centrifugal compressor stage has the conditions that the flow separation at the impeller outlet casing is large, the radial direction of the meridian flow channel is converted into the radial direction of the axial section, the curvature radius is small, and the direction is severe. Both of these conditions can result in a centrifugal compressor stage with a low efficiency.
Disclosure of Invention
The invention aims to avoid the defects of the prior art and provide a serial diffuser of a centrifugal compressor stage, which obviously inhibits the flow separation at the outlet casing of a centrifugal impeller, has more uniform flow field and reduces the loss.
In order to achieve the purpose, the invention adopts the technical scheme that: a centrifugal compressor stage serial diffuser comprises a diffuser casing and an axial section casing which are sequentially connected in the air inlet direction of the diffuser, and further comprises a diffuser hub and an axial section hub which is connected behind the diffuser hub; the diffuser casing and the diffuser hub are matched to form a diffuser meridian flow channel, and a diffuser radial front row blade, a diffuser axial rear row main blade and a diffuser axial rear row splitter blade which are respectively fixedly connected with the diffuser hub and the diffuser casing are sequentially arranged in the meridian flow channel along the airflow direction;
the tail edge of the radial front row of blades of the diffuser extends to the curved section of the meridian flow channel, and the radial front row of blades of the diffuser is used for changing radial flow into axial flow in the curved section in advance; the tail edge of the radial front row of blades of the diffuser is close to the front edge of the axial rear row of main blades of the diffuser, and a flow channel gap is arranged between the tail edge of the radial front row of blades of the diffuser and the front edge of the axial rear row of main blades of the diffuser;
the diffuser radial front-row blades are uniformly distributed on the circumferential surface of the diffuser hub, and the diffuser axial back-row main blades and the diffuser axial back-row splitter blades are alternately and uniformly distributed on the axial circumferential surface of the diffuser hub.
Further, the flow passage gap is a gap between a trailing edge pressure surface of the radial front row of blades of the diffuser and a leading edge suction surface of the axial rear row of main blades of the diffuser.
Furthermore, the diffuser axial back row main blades and the adjacent diffuser axial back row splitter blades are a group of diffuser axial back row blades, and an airflow channel formed by the group of diffuser axial back row blades is used for reducing an included angle between airflow and the axial direction; the number of the groups of the blades in the axial back row of the diffuser is the same as that of the blades in the radial front row of the diffuser.
Furthermore, the diffuser casing and the axial section casing, the diffuser hub and the axial section hub form the meridian flow channel, and the meridian flow channel is a composite curve formed by matching a straight line and a Bezier curve; the casing at the axial section of the inlet of the meridian flow passage has a casing contraction section which contracts 1.5-2.5mm towards the direction of the diffuser hub, and the backflow at the diffuser inlet casing is obviously inhibited.
Furthermore, an air inlet channel hub and a diffuser hub are sequentially arranged in the air inlet direction of the diffuser, a centrifugal impeller disc hub is arranged between the air inlet channel hub and the diffuser hub, centrifugal impeller main blades and centrifugal impeller splitter blades are alternately arranged on the windward circumferential surface of the centrifugal impeller disc hub, and the centrifugal impeller disc hub and the centrifugal impeller main blades jointly form a centrifugal impeller and work and rotate at a constant speed;
diffuser air inlet direction is last, still connects gradually and is equipped with intake duct machine casket, centrifugal impeller machine casket, intake duct wheel hub and centrifugal impeller dish wheel hub set up intake duct machine casket and centrifugal impeller machine casket in.
Furthermore, the main blades of the centrifugal impeller and the splitter blades of the centrifugal impeller are uniformly distributed in the circumferential direction.
The blade profile of the radial front row of blades of the diffuser is obtained by the following method steps:
1) determining the leading edge point and the trailing edge point of a vane profile of a radial front row of vanes of the diffuser: firstly, equally dividing the blade height profile of the radial front row of blades of the diffuser into n layers which are respectively H1、H2、…HnWherein H is1The blade profile is the interface between hub and blade, HnThe blade-height blade profile is an interface between a casing and blades, the front edges of the n blade-height blade profiles are straight lines in a plane vertical to the rotating shaft direction of the diffuser, the blades are stacked in a straight line mode along the front edges of the n blade-height blade profiles, and when the blades are stacked, the inclined angle of the front edges relative to the radial direction in the plane vertical to the rotating shaft direction is L degrees;
selecting a cylindrical coordinate system, wherein only two dimensions of Z and R are involved, Z is an abscissa, and R is an ordinate; according to the stacking mode, each high-profile leading edge point of the n high-profile is limited by an R coordinate, each high-profile trailing edge point is limited by a Z coordinate, and then the R coordinate of the n high-profile leading edge points is R1、R2、…Rn(ii) a The Z coordinate of the n blade-height profile tail edge points is Z1、Z2、…Zn；
Obtaining the leading edge point and the trailing edge point of the vane high profile of the radial front row of vanes of the diffuser in the Z-R meridian plane;
2) determining a mean camber line of the high profile: in the n blade-height profiles, the arc line is formed by a two-dimensional coordinate system in the curve plane of the corresponding blade-height profile
Definition, which is a Bezier curve defined by m points; abscissa of the circle
The meridian point is the integral of the ratio of the length increment of the mean arc line to the radius in the meridian plane by taking the leading edge point as a starting point, wherein the m-2 point abscissas of points between the leading edge point and the trailing edge point of the arc line are uniformly distributed at equal distance; the ordinate is a circumferential angle theta, and a value theta is obtained through pneumatic analysis of fluid simulation software;
the process obtains the mean camber line corresponding to the blade height profile of the front row of radial blades (1) of the diffuser;
3) determining the half thickness distribution of the blade height profile: the blade profile pressure surface and the suction surface of the radial front row of blades of the diffuser are symmetrical and are defined by half thicknesses which are distributed in the same way, in the distribution process of the half thicknesses, the abscissa represents the abscissa by equal division with the total length as unit 1, namely the relative position of the leading edge is 0, the relative position of the trailing edge is 1, and the ordinate is a half thickness value; the half thickness value of the blade profile at the nth blade height is respectively T from the leading edge to the trailing edge along a Bezier curve defined by m pointsn-1，Tn-2…，Tn-mObtaining corresponding T through pneumatic analysis of fluid simulation softwaren-1，Tn-2…，Tn-mA value of (d); in the high-leaf profile, a pressure surface and a suction surface are respectively formed on two sides in a vertical camber line mode;
4) determining a preliminary blade profile of the radial front row of blades of the diffuser: further obtaining a blade height blade profile through the blade height blade profile half-thickness distribution obtained in the third step, and forming a primary blade profile through the point stacking of the front edges of the n blade height blade profiles;
5) determining the final blade profile of the radial front row blades of the diffuser: the leading edge of the radial front row of blades of the diffuser is a sharp leading edge, and the generation mode is as follows: on each blade profile, taking the front edge point of an arc line as a starting point, drawing a circle in a plane vertical to a rotating shaft of the centrifugal compressor at the center of the circle, and intersecting the circle with a pressure surface and a suction surface of the blade profile respectively to form two intersection points; connecting the two intersection points, the pressure surface and the suction surface are closed at the front edge;
the tail edge of the radial front row of blades of the diffuser is an ellipse, and the ellipse is respectively tangent to the pressure surface and the suction surface of the blade profile; the pressure and suction sides are closed at the trailing edge.
The invention has the beneficial effects that: the centrifugal compressor stage serial diffuser provided by the invention reduces the speed and expands the airflow, and simultaneously changes the airflow flowing direction in the radial section and the axial section successively, thereby changing the condition that most of the turning function of the traditional scheme is borne by the axial diffuser, reducing the load of the second row (axial section) of the serial diffuser, leading the load to be closer to the axial direction, greatly reducing the backflow and the speed gradient in the channel of the axial section, reducing the loss under the condition of giving the requirement of the axial air outlet angle, converting the meridian channel from the radial direction to the axial section with increased curvature radius, relieving the problem of violent turning, and obviously inhibiting the flow separation at the outlet of the centrifugal impeller by the contraction section (14) of the casing at the outlet of the impeller; the advantages are verified by the steady CFD calculation, and the practical loss reduction and the efficiency improvement can be completely realized.
Drawings
FIG. 1 is a schematic structural view of the present invention;
FIG. 2 is a meridian plane sectional structural schematic of the present invention;
FIG. 3 shows the diffuser of the present invention with radial front row vanes H1And HnA schematic diagram of a middle camber line of the leaf height;
FIG. 4 shows the diffuser radial front row of vanes H of the present invention1And HnA schematic diagram of a high leaf profile;
FIG. 5 shows the diffuser of the present invention with radial front row vanes H1And HnThe blade height is respectively the structure schematic diagram of the front edge with the same radius;
FIG. 6 is a schematic view of the vane profile of the leading radial row of the diffuser formed by the ruled surface method of the present invention;
FIG. 7 is a schematic view of a diffuser of the present invention at 50% blade height streamlines;
FIG. 8 is a schematic meridional flow chart of the present invention;
figure 9 is a schematic view of a meridian flow channel construction of the present invention;
FIG. 10 is a high section of the leading radial row of vanes H1 of the diffuser of the present invention
A schematic view under a coordinate system;
FIG. 11 shows the camber line of the vane height H1 in the front radial row of the diffuser according to the present invention
A definition schematic diagram under a coordinate system;
FIG. 12 is a schematic view of the diffuser radial forward row vanes H1 vane height thickness definition of the present invention;
FIG. 13 is a high vane section of the front radial row of vanes Hn of the diffuser of the present invention
A schematic view under a coordinate system;
FIG. 14 shows the camber line of the high vane of the front radial row of vanes Hn of the diffuser according to the present invention
A definition schematic diagram under a coordinate system;
FIG. 15 is a schematic view of the diffuser radial leading row vane Hn vane height vane thickness definition of the present invention;
FIG. 16 shows the diffuser axial aft row of vanes H of the present invention1High section of the blade
A schematic view under a coordinate system;
FIG. 17 shows the camber line of the axial aft row of vanes H1 of the diffuser of the present invention
A definition schematic diagram under a coordinate system;
FIG. 18 is a schematic view of the diffuser axial aft row of vanes H1 defining vane height thickness according to the present invention;
FIG. 19 is a high vane section of the axial aft row of vanes Hn of a diffuser according to the present invention
A schematic view under a coordinate system;
FIG. 20 shows the camber line of the high blade of the Hn blade of the diffuser in the axial rearward row of blades of the invention
A definition schematic diagram under a coordinate system;
FIG. 21 is a schematic view of the axial aft row of vanes Hn of a diffuser according to the present invention defining vane height.
In the figure: 1. diffuser radial front row blades; 2. the diffuser is axially arranged at the back of the main blade; 3. the diffuser is axially arranged with splitter blades at the back row; 4. a centrifugal impeller main blade; 5. a centrifugal impeller splitter blade; 6. an inlet hub; 7. a centrifugal impeller disc hub; 8. a diffuser hub; 9. an axial segment hub; 10. an air inlet casing; 11. a centrifugal impeller casing; 12. a diffuser casing; 13. an axial section casing, 14 and a casing contraction section.
Detailed Description
The principles and features of this invention are described below in conjunction with the following drawings, which are set forth by way of illustration only and are not intended to limit the scope of the invention.
Example 1: as shown in fig. 1-8, a centrifugal compressor stage serial diffuser comprises a diffuser casing 12 and an axial section casing 13 which are sequentially connected in the air inlet direction of the diffuser, and further comprises a diffuser hub 8 and an axial section hub 9 which is connected behind the diffuser hub 8; the diffuser casing 12 and the diffuser hub 8 are matched to form a diffuser meridian flow channel, the diffuser casing 12, the axial section casing 13, the diffuser hub 8 and the axial section hub 9 form a meridian flow channel, and the meridian flow channel is a composite curve formed by matching a straight line and a Bessel curve; in the meridian flow passage, a diffuser radial front row blade 1, a diffuser axial rear row main blade 2 and a diffuser axial rear row splitter blade 3 which are respectively fixedly connected with a diffuser hub 8 and a diffuser casing 12 are sequentially arranged along the airflow direction; the casing 13 at the inlet of the meridian flow passage has a casing contraction section 14 which contracts 1.5-2.5mm towards the diffuser hub 8, so that backflow at the diffuser inlet casing is remarkably inhibited.
An air inlet channel hub 6 and a diffuser hub 8 are sequentially arranged in the air inlet direction of the diffuser, a centrifugal impeller disc hub 7 is arranged between the air inlet channel hub 6 and the diffuser hub 8, centrifugal impeller main blades 4 and centrifugal impeller splitter blades 5 are alternately arranged on the windward circumferential surface of the centrifugal impeller disc hub 7, and the centrifugal impeller disc hub 7, the centrifugal impeller main blades 4 and the centrifugal impeller splitter blades 5 jointly form a centrifugal impeller which rotates at a constant speed; the main blades 4 of the centrifugal impeller and the splitter blades 5 of the centrifugal impeller are uniformly distributed in the circumferential direction; in the air inlet direction of the diffuser, an air inlet casing 10 and a centrifugal impeller casing 11 are sequentially connected, and an air inlet hub 6 and a centrifugal impeller disc hub 7 are arranged in the air inlet casing 10 and the centrifugal impeller casing 11;
the tail edge of the radial front row of blades 1 of the diffuser extends to the bending section of the meridian flow channel, and the radial front row of blades 1 of the diffuser is used for changing radial flow into axial flow in the bending section in advance; a flow channel gap is arranged between the trailing edge of the radial front-row blades 1 of the diffuser and the leading edge of the axial rear-row main blades 2 of the diffuser, and the flow channel gap is a gap between the trailing edge pressure surface of the radial front-row blades 1 of the diffuser and the leading edge suction surface of the axial rear-row main blades 2 of the diffuser; the flow passage gap enables high-energy fluid on the pressure surface of the radial front-row blades 1 of the diffuser to blow to the suction surface of the axial back-row main blades 2 of the diffuser, which is easy to separate, after being accelerated, so that the separation of the suction surface of the axial back-row main blades 2 of the diffuser is inhibited or delayed;
the radial front row blades 1 of the diffuser are uniformly distributed on the circumferential surface of the hub 8 of the diffuser, and the axial back row main blades 2 and the axial back row splitter blades 3 of the diffuser are alternately and uniformly distributed on the axial circumferential surface of the hub 8 of the diffuser; the diffuser axial back row main blades 2 and the adjacent diffuser axial back row splitter blades 3 are a group of diffuser axial back row blades, and an airflow channel formed by the group of diffuser axial back row blades is used for reducing the included angle between airflow and the axial direction; the number of the groups of the blades in the axial back row of the diffuser is the same as that of the blades 1 in the radial front row of the diffuser.
The working process of the invention is as follows: when the centrifugal compressor works, a centrifugal impeller consisting of a centrifugal impeller main blade 4, a centrifugal impeller splitter blade 5 and a centrifugal impeller disc hub 7 rotates at a high speed, and due to the action of the high speed of rotation, gas in a gas flow channel formed by adjacent blades is thrown out of the centrifugal impeller and enters a rear structure along the radial direction. The air in the impeller is thrown out, and the air at the inlet of the impeller is sucked into the airflow channel of the centrifugal impeller under the action of pressure. The air at the front end of the centrifugal impeller flows at a high speed, and the pressure is reduced, so that the air in the air inlet formed by the air inlet hub 6 and the air inlet casing 10 flows into the centrifugal impeller, and the outside air flows into the air inlet.
After being thrown out of the centrifugal impeller, gas sequentially enters a diffuser radial front-row blade 1 and a diffuser axial rear-row blade of the diffuser along a certain angle with the radial direction, the radial flow in a meridian plane is changed into the axial flow in the meridian plane in a bending section by a channel formed by the diffuser radial front-row blades 1 of the diffuser, and meanwhile, the gas is decelerated and pressurized, and the diffuser axial rear-row blade further enables the gas to be closer to the direction of a Z axis to change the direction of the gas flow and finally enters a subsequent combustion chamber and other parts.
As shown in fig. 7 and 8, at the gap between the front radial row of blades 1 of the diffuser and the rear axial row of blades of the diffuser, the rear axial row of blades of the diffuser limits the development of a low-speed region of fluid on the suction surface of the front radial row of blades 1 of the diffuser, the backflow is significantly reduced, and a meridional average flow chart can show that the flow field of the diffuser is very uniform.
The centrifugal compressor stage with the structure can obviously improve the efficiency, the pressure ratio and the like of the centrifugal compressor stage. The centrifugal compressor stage with the structure is used for a small turbojet engine, so that the rated rotating speed can be reduced under the condition of ensuring that the thrust does not change much, and the stable work of the bearing is facilitated. And because the efficiency of the air compressor is greatly improved, the range of the aircraft is increased and the consumption rate of fuel is saved under the condition of carrying fuel oil with the same quality.
The blade profile of the radial front row of blades 1 of the diffuser, which can achieve the technical effects, is obtained by the following method steps:
1) determining the leading edge point and the trailing edge point of a vane profile of a radial front row of vanes of the diffuser: firstly, equally dividing the blade height profile of the radial front row of blades of the diffuser into n layers which are respectively H1、H2、…HnWherein H is1The blade profile is the interface between hub and blade, HnThe vane-height vane profile is an interface between a casing and vanes, the leading edges of the n vane-height vane profiles are straight lines in a plane vertical to the rotating shaft direction of the diffuser, the vanes 1 in the radial front row of the diffuser are stacked in a straight line mode along the leading edges of the n vane-height vane profiles, and the inclined angle of the leading edges relative to the radial direction is L degrees in the plane vertical to the rotating shaft direction during stacking;
selecting a cylindrical coordinate system, wherein only two dimensions of Z and R are involved, Z is an abscissa, and R is an ordinate; according to the stacking mode, each high-profile leading edge point of the n high-profile is limited by an R coordinate, each high-profile trailing edge point is limited by a Z coordinate, and then the R coordinate of the n high-profile leading edge points is Rn(ii) a The Z coordinate of the n blade-height profile tail edge points is Zn；
Obtaining the leading edge point and the trailing edge point of the vane high profile of the radial front row of vanes of the diffuser in the Z-R meridian plane;
2) determining a mean camber line of the high profile: as shown in FIG. 3, in the n blade-height profiles, the arc line is defined by a two-dimensional coordinate system in the corresponding blade-height profile curve
Definition, abscissa
The method comprises the following steps of taking a leading edge point as a starting point, integrating the ratio of the increment of the mean camber line length to the radius in the meridian plane, taking the ordinate as a circumferential angle theta, and obtaining a proper theta value through pneumatic analysis of fluid simulation software; the mean camber line is a Bezier curve defined by m points in the nth leaf height profileThe horizontal coordinates of other points of the arc except the front edge point and the tail edge point are uniformly distributed at equal intervals;
obtaining a mean camber line corresponding to the blade height profile of the radial front row of blades of the diffuser;
3) determining the half thickness distribution of the blade height profile: as shown in fig. 4, the pressure surface and the suction surface of the blade profile of the radially front row of blades of the diffuser are symmetrical and defined by half thicknesses which are distributed in the same manner, and in the distribution process of the half thicknesses, the abscissa represents the abscissa by the equal division of the total length as unit 1, that is, the leading edge relative position is 0, the trailing edge relative position is 1, and the ordinate is the half thickness value; the half thickness value of the blade profile at the nth blade height is respectively T from the leading edge to the trailing edge along a Bezier curve defined by m pointsn-1，Tn-2…，Tn-mObtaining corresponding T through pneumatic analysis of fluid simulation softwaren-1，Tn-2…，Tn-mA value of (d); in the high-leaf profile, a pressure surface and a suction surface are respectively formed on two sides in a vertical camber line mode;
4) determining a preliminary blade profile of the radial front row of blades of the diffuser: as shown in fig. 6, a blade height profile is further obtained through the blade height profile half-thickness distribution obtained in the third step, and a preliminary blade profile is formed by dot-stacking the leading edges of n blade height profiles;
5) determining the final blade profile of the radial front row blades of the diffuser: as shown in fig. 5, the leading edge of the radial front row blade 1 of the diffuser is a sharp leading edge, and the generation mode is as follows: on each blade profile, taking the front edge point of an arc line as a starting point, drawing a circle in a plane vertical to a rotating shaft of the centrifugal compressor at the center of the circle, and intersecting the circle with a pressure surface and a suction surface of the blade profile respectively to form two intersection points; connecting the two intersection points, the pressure surface and the suction surface are closed at the front edge;
the tail edge of the radial front row of blades 1 of the diffuser is an ellipse, and the ellipse is respectively tangent to the pressure surface and the suction surface of the blade profile; the pressure and suction sides are closed at the trailing edge.
The specific construction example of the invention:
as shown in fig. 9, in a meridian plane, the whole formed by the diffuser hub 8 and the axial section hub (9) is formed by four sequentially connected end-to-end bezier curves and straight lines, and the formed line is a hub curve; the diffuser casing 12 and the axial section casing 13 are also composed of four sequential end-to-end Bezier curves and straight lines, and the formed line is a casing curve; the straight line segment is a connecting line of two points, the two points of the straight line are defined as end points, and the end points of each line are in the same point with the end points of the adjacent connecting line;
the hub curve has 11 points in total, is defined by coordinates (Z, R), has the unit of mm, and is respectively H1(-1.81988,75.5), H2(-1.75764,76.09788), H3(-1.62944,77.24358), H4(-1.66,78), H5(-1.66,86), H6(-1.66,88.73052), H7(-0.85340,91.90025), H8(1.36475,93.95851), H9(4.19905,94.75), H10(6.5,94.75) and H11(69.78012, 94.75).
The total of 9 points of the casing curve are defined by coordinates (Z, R), the unit is mm, and the curves are S1(-11.11104,75.06780), S2(-9.75,79), S3(-9.75,86), S4(-9.75,90.11920), S5(-7.95969,96.42843), S6(-2.73330,100.47639), S7(2.80244,101.5), S8(6.5,101.5) and S9(69.78012,101.5).
The casing contraction section 14 formed by S1 and S2 is arranged at the diffuser inlet, namely the inlet casing of the radial flow passage of the diffuser, so that backflow at the diffuser inlet casing can be obviously inhibited.
The radial front row blades 1 of the diffuser are composed of H1Leaf height, HnHigh leaf profile of the leaf, H1The blade profile is the interface between hub and blade, HnThe blade profile with the high blade is the interface between the hub and the casing, the stacking rule is stacking along the front edge of the blade profile, and the relative inclination angle is 0 when the two sectional areas are stacked;
in a meridian plane, the radial front row of blades 1 of the diffuser convert fluid from radial flow to axial flow, a front edge point is limited by an R coordinate, and H is1The R coordinate of the leaf height leading edge point is 81.835mm, HnThe R coordinate of the leaf height leading edge point is 81.835 mm; the trailing edge point being limited by the Z coordinate, H1The Z coordinate of the leaf height tail edge point is 5mm, HnThe Z coordinate of the leaf height trailing edge point is 5.75 mm. The front edge and the tail edge are straight lines, and the whole radial front row of blades 1 of the diffuser is a ruled surface;
as shown in fig. 10-15H of radial front row blade 1 of diffuser1、HnThe blade height profile is defined by parameters such as mean camber line, blade thickness distribution and the like, and is specifically H1、HnThe camber line of the blade profile is defined by a two-dimensional coordinate system
Definition, abscissa
The longitudinal coordinate is a circumferential angle, the horizontal coordinate is an integral of a ratio of a length increment and a radius in a meridian plane with the leading edge as a starting point, the defining method is that the camber lines of two sections are superposed on the thickness of each blade profile, the camber lines are Bezier curves and are defined by 9 points, as shown in FIGS. 11 and 14, the two section leading edge end points are the two-dimensional coordinate system starting points which are respectively C0-1(0,0) and C100-1(0,0), and dmr is that the leading edge is used as the starting point
Integrating the obtained values, wherein the dmr coordinate value is determined by the positions of the leading edge and the trailing edge of the blade profile, and the dmr values of 7 points in the middle are uniformly distributed in an equal division manner;
H1the theta coordinates of the rest points of the section of the leaf height are C0-2(0.05958), C0-3(0.10317), C0-4(0.16261), C0-5(0.22319), C0-6(0.27258), C0-7(0.32211), C0-8(0.36657) and C0-9 (0.41426).
HnThe coordinates of the rest points of the section of the leaf height are C100-2(0.09847), C100-3(0.17282), C100-4(0.22295), C100-5(0.27568), C100-6(0.31904), C100-7(0.35333), C100-8(0.38056) and C100-9 (0.39972);
the front edge of the front row of radial blades 1 of the diffuser is a sharp front edge, and the tail edge is an ellipse;
as shown in fig. 12 and 15, the thickness definition pressure plane is symmetrical to the suction plane, and the bezier curve defined by 8 uniformly distributed points is used. H1The thicknesses of the high-section blades are respectively T0-1(0.096), T0-2(0.30565), T0-3(0.56063), T0-4(0.75186), T0-5(0.94309), T0-6(1.04406), T0-7(0.94323) and T0-8 (0.89282); hnThe thicknesses of the high-section blades are respectively T100-1(0.096), T100-2(0.36624), T100-3(0.65735), T100-4(1), T100-5(1), T100-6(1), T100-7(0.86738) and T100-8 (0.74918);
the number of blades in the front radial row of the diffuser 1 is 22, and the relative angle of the defined blades in a coordinate system is 90.63 degrees.
As shown in FIGS. 16-21, the diffuser axial trailing row main blade (2) and the diffuser axial trailing row splitter blade (3) have completely identical geometries and are also represented by H1Leaf height, HnThe blade height profile is defined by the stacking rule of the blades along the leading edge of the blade profile, H1、HnThe relative inclination angle of the two overlapped high sectional areas of the two blades is 0;
in the meridian plane, the axial back row of blades of the diffuser only develops in the axial direction, the leading edge point is limited by the Z coordinate, H1The Z coordinate of the leaf height leading edge point is 6.5mm, HnThe Z coordinate of the leaf height leading edge point is 6.5 mm; the trailing edge point is limited by the Z coordinate, the Z coordinate of the 0% blade height trailing edge point is 21.4mm, and the Z coordinate of the 100% blade height trailing edge point is 21.4 mm. The front edge and the tail edge are straight lines, and the whole of the axial back row of blades of the diffuser is a ruled surface;
diffuser axial back row blade H1、HnThe blade height profile is defined by parameters such as mean camber line, blade thickness distribution and the like, and is specifically H1、HnThe camber line of the blade profile is defined by a two-dimensional coordinate system
Definition, abscissa
Which may be abbreviated as dmr, the ordinate is the axial angle, the abscissa is the integral of the ratio of the length increment to the radius in the meridian plane from the leading edge as the starting point, the definition method is that the mean camber lines of the two cross sections are superimposed on the thickness of the respective blade profile, the mean camber lines are bezier curves and are defined by 9 points, as shown in fig. 17 and 20, the above H is the above1、HnThe leading edge of the blade height has fixed end points C0-1(0,0) and C100-1(0,0), respectively, and the coordinate value of the end point dmr is determined by the position of the trailing edge of the leading edge of the blade profile, whereinThe coordinate values of 7 points dmr are uniformly distributed in equal parts;
H1the theta coordinates of the rest points of the section of the leaf height are C0-2(0.04187), C0-3(0.05436), C0-4(0.06632), C0-5(0.07869), C0-6(0.08044), C0-7(0.08090), C0-8(0.07625) and C0-9 (0.06789). HnThe coordinates of the rest points of the section of the leaf height are C100-2(0.01660), C100-3(0.03071), C100-4(0.04436), C100-5(0.05262), C100-6(0.05704), C100-7(0.05742), C100-8(0.05320) and C100-9 (0.04743);
the front edge and the tail edge of the axial back row of blades of the diffuser are both elliptical, the thickness defines that a pressure surface is symmetrical to a suction surface, and the pressure surface and the suction surface are bezier curves defined by using 5 uniformly distributed points. As shown in fig. 18 and 21, H1The thicknesses of the high-section blades are respectively T0-1(0.5), T0-2(0.7), T0-3(1.0), T0-4(0.7) and T0-5 (0.5). HnThe thicknesses of the high-section blades are respectively T100-1(0.5), T100-2(0.7), T100-3(1.0), T100-4(0.7) and T100-5 (0.5);
the number of blades on the whole circumference of the blades on the axial back row of the diffuser is 44, and the relative angle of the defined blades in a coordinate system is 112 degrees.
The above description is only for the purpose of illustrating the preferred embodiments of the present invention and is not to be construed as limiting the invention, and any modifications, equivalents, improvements and the like that fall within the spirit and principle of the present invention are intended to be included therein.
Claims (7)
1. A centrifugal compressor stage serial diffuser is characterized by comprising a diffuser casing (12) and an axial section casing (13) which are sequentially connected in the air inlet direction of the diffuser, and further comprising a diffuser hub (8) and an axial section hub (9) which is connected behind the diffuser hub (8); the radial front row diffuser blades (1), the axial back row diffuser main blades (2) and the axial back row diffuser splitter blades (3) which are fixedly connected with the diffuser hub (8) and the diffuser casing (12) respectively are sequentially arranged in the radial flow channel along the airflow direction;
the tail edge of the radial front row of blades (1) of the diffuser extends to the curved section of the meridian flow channel, and the radial front row of blades (1) of the diffuser are used for changing radial flow into axial flow in the curved section in advance; the tail edge of the front radial row of blades (1) of the diffuser is close to the front edge of the rear axial row of main blades (2) of the diffuser, and a flow channel gap is arranged between the tail edge of the front radial row of blades (1) of the diffuser and the front edge of the rear axial row of main blades (2), so that high-energy fluid on the pressure surface of the front radial row of blades (1) of the diffuser is accelerated and then blown to the suction surface of the rear axial row of main blades (2) of the diffuser, which is easy to separate, so that the separation of the suction surface of the rear axial row of main blades (2) of the diffuser is inhibited or delayed;
the radial front row blades (1) of the diffuser are uniformly distributed on the circumferential surface of the diffuser hub (8), and the axial back row main blades (2) and the axial back row splitter blades (3) of the diffuser are alternately and uniformly distributed on the axial circumferential surface of the diffuser hub (8).
2. The centrifugal compressor stage diffuser according to claim 1, wherein the flow path gap is a gap between a trailing edge pressure surface of a radially front row of blades (1) of the diffuser and a leading edge suction surface of an axially rear row of main blades (2) of the diffuser.
3. The centrifugal compressor stage diffuser according to claim 1, wherein the diffuser axial trailing row main blades (2) and the adjacent diffuser axial trailing row splitter blades (3) are a set of diffuser axial trailing row blades, and the set of diffuser axial trailing row blades form an airflow channel for reducing an included angle between an airflow and an axial direction; the number of the groups of the blades in the axial back row of the diffuser is the same as that of the blades (1) in the radial front row of the diffuser.
4. The centrifugal compressor stage diffuser according to claim 1, wherein the diffuser casing (12), the axial section casing (13), the diffuser hub (8) and the axial section hub (9) form the meridian flow path, and the meridian flow path is a compound curve formed by matching a straight line and a Bezier curve; the diffuser casing (12) at the inlet of the meridian flow path has a casing constriction (14) which constricts 1.5-2.5mm towards the diffuser hub (8), significantly suppressing flow separation at the diffuser inlet casing.
5. The centrifugal compressor stage serial diffuser according to claim 1, wherein an air inlet channel hub (6) and a diffuser hub (8) are sequentially arranged in an air inlet direction of the diffuser, a centrifugal impeller disc hub (7) is arranged between the air inlet channel hub (6) and the diffuser hub (8), centrifugal impeller main blades (4) and centrifugal impeller splitter blades (5) are alternately arranged on a windward circumferential surface of the centrifugal impeller disc hub (7), and the centrifugal impeller disc hub (7), the centrifugal impeller main blades (4) and the centrifugal impeller splitter blades (5) jointly form a centrifugal impeller which rotates at a constant speed;
diffuser air inlet direction is last, still connects gradually and is equipped with intake duct machine casket (10), centrifugal impeller machine casket (11), intake duct wheel hub (6) and centrifugal impeller dish wheel hub (7) set up intake duct machine casket (10) and centrifugal impeller machine casket (11) in.
6. The centrifugal compressor stage diffuser according to claim 5, wherein the centrifugal impeller main blades (4) and the centrifugal impeller splitter blades (5) are circumferentially equispaced.
7. A centrifugal compressor stage cascade diffuser according to any of claims 1 to 6, characterized in that the blade profile of the diffuser radially front row of blades (1) is obtained by the following method steps:
1) determining the leading edge point and the trailing edge point of the blade height profile of the radial front row of blades (1) of the diffuser: firstly, equally dividing the blade height profile of the radial front row of blades (1) of the diffuser into n layers which are respectively H1、H2、…HnWherein H is1The blade profile is the interface between hub and blade, HnThe blade profile is the interface of the casing and the blades, the front edges of the n blade profiles are straight lines in the plane vertical to the rotating shaft direction of the diffuser, the blades are stacked in a straight line mode along the front edges of the n blade profiles, and when the blades are stacked, the front edges are inclined relative to the radial direction in the plane vertical to the rotating shaft directionThe angle is L degrees;
selecting a cylindrical coordinate system, wherein only two dimensions of Z and R are involved, Z is an abscissa, and R is an ordinate; according to the stacking mode, each high-profile leading edge point of the n high-profile is limited by an R coordinate, each high-profile trailing edge point is limited by a Z coordinate, and then the R coordinate of the n high-profile leading edge points is R1、R2、…Rn(ii) a The Z coordinate of the n blade-height profile tail edge points is Z1、Z2、…Zn；
Namely, the leading edge point and the trailing edge point of the vane height profile of the front radial row of vanes (1) of the diffuser in the Z-R meridian plane are obtained;
2) determining a mean camber line of the high profile: in the n blade-height profiles, the arc line is formed by a two-dimensional coordinate system in the curve plane of the corresponding blade-height profile
Definition, which is a Bezier curve defined by m points; abscissa of the circle
The meridian point is the integral of the ratio of the length increment of the mean arc line to the radius in the meridian plane by taking the leading edge point as a starting point, wherein the m-2 point abscissas of points between the leading edge point and the trailing edge point of the arc line are uniformly distributed at equal distance; the ordinate is a circumferential angle theta, and a value theta is obtained through pneumatic analysis of fluid simulation software;
the process obtains the mean camber line corresponding to the blade height profile of the front row of radial blades (1) of the diffuser;
3) determining the half thickness distribution of the blade height profile: the blade profile pressure surface and the suction surface of the radial front row of blades (1) of the diffuser are symmetrical and are defined by half thicknesses which are distributed in the same way, in the distribution process of the half thicknesses, the abscissa represents the abscissa by equal division with the total length as unit 1, namely the relative position of the leading edge is 0, the relative position of the trailing edge is 1, and the ordinate is a half thickness value; in the nth blade profile, the half thickness values are respectively T from the leading edge to the trailing edge along the Bezier curve defined by m pointsn-1，Tn-2…，Tn-mObtaining corresponding T through pneumatic analysis of fluid simulation softwaren-1，Tn-2…，Tn-mA value of (d); in the high-leaf profile, a pressure surface and a suction surface are respectively formed on two sides in a vertical camber line mode;
4) determining a preliminary blade profile of the radial front row of blades (1) of the diffuser: further obtaining a blade height blade profile through the blade height blade profile half-thickness distribution obtained in the third step, and forming a primary blade profile through the point stacking of the front edges of the n blade height blade profiles;
5) determining the final blade profile of the radial front row blades (1) of the diffuser: the leading edge of the radial front row of blades of the diffuser is a sharp leading edge, and the generation mode is as follows: on each blade profile, taking the front edge point of an arc line as a starting point, drawing a circle in a plane vertical to a rotating shaft of the centrifugal compressor at the center of the circle, and intersecting the circle with a pressure surface and a suction surface of the blade profile respectively to form two intersection points; connecting the two intersection points, the pressure surface and the suction surface are closed at the front edge;
the tail edge of the radial front row of blades of the diffuser is an ellipse, and the ellipse is respectively tangent to the pressure surface and the suction surface of the blade profile; the pressure and suction sides are closed at the trailing edge.
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| CN114718907A (en) * | 2022-04-21 | 2022-07-08 | 珠海格力电器股份有限公司 | Two-stage axial diffuser, pneumatic component, dust collector and compressor |
| CN114754023A (en) * | 2022-03-28 | 2022-07-15 | 约克广州空调冷冻设备有限公司 | Blade, impeller and backward centrifugal fan |
| CN115045722A (en) * | 2022-05-27 | 2022-09-13 | 中国航发湖南动力机械研究所 | Transonic speed guider applied to centripetal turbine and centripetal turbine |
| CN115095549A (en) * | 2022-06-20 | 2022-09-23 | 淮安威灵电机制造有限公司 | Diffuser structure, air supply device and household appliances |
| CN115370592A (en) * | 2022-09-22 | 2022-11-22 | 杭州华翊科技有限公司 | Centrifugal compressor |
| WO2025040107A1 (en) * | 2023-08-23 | 2025-02-27 | 南昌华勤电子科技有限公司 | Dual-profile strong-suction vortex fan blade, fan and electronic device |
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