CN113094833B - Diffuser design method with dovetail leading edge and radial and axial blade integration - Google Patents
Diffuser design method with dovetail leading edge and radial and axial blade integration Download PDFInfo
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Abstract
The invention provides a modeling method of a diffuser with a dovetail front edge and integrated radial and axial blades, wherein the diffuser prepared by the method has a tubular diffuser front edge structure, and the radial and axial diffuser blades are integrally designed; compared with a common blade diffuser, the special three-dimensional fan-shaped structure of the front edge of the blade can better cope with complex unsteady flow of the impeller outlet; meanwhile, the radial and axial diffuser blades are integrally molded by adopting smooth transition molded lines at the runner part, so that the pressure ratio, the efficiency and the stable working margin of the centrifugal compressor with high pressure ratio are greatly improved in a limited flow space, and the centrifugal compressor is particularly suitable for the centrifugal compressors of medium and small aeroengines and miniature gas turbines.
Description
Technical Field
The invention provides a diffuser design method with a dovetail-shaped front edge structure of a pipe diffuser and integrally modeling radial and axial diffuser blades, which combines the advantages of the pipe diffuser and the blade diffuser: compared with a tubular diffuser, the blade diffuser has the advantages of convenient modeling, simple processing and low manufacturing cost; compared with a common blade diffuser, the special three-dimensional fan-shaped structure of the front edge of the blade can better cope with complex unsteady flow of the impeller outlet; meanwhile, the radial and axial diffuser blades are integrally molded by adopting a molded line with a certain curvature at the runner part, so that the pressure ratio, the efficiency and the stable working margin of the centrifugal compressor with high pressure ratio are greatly improved in a limited flow space, and the centrifugal compressor is particularly suitable for centrifugal compressor parts of medium and small aeroengines and miniature gas turbines.
Background
The centrifugal compressor has the advantages of compact structure, high pressure ratio, high reliability, convenient manufacture, low cost, good manufacturability, wider stable working margin and the like, so that the centrifugal compressor is widely applied to a supercharging device for fluid working media in aviation, petrochemical and other industries, and in the past decades, along with industry requirements, the performance requirements of people on the centrifugal compressor are higher and higher, and the centrifugal compressor is hoped to have better pneumatic performance and wider working margin. In order to further improve the thrust-weight ratio of the engine and perfect the performance of the engine in various flying states at high altitude, the centrifugal compressor has higher requirement on the pressure ratio of the centrifugal compressor. The high-pressure ratio centrifugal compressor has the advantages that the air flow speed at the impeller outlet of the high-pressure ratio centrifugal compressor is high and uneven, the width of the impeller outlet of the high-pressure ratio centrifugal compressor is small, the diffuser inlet is very close to the impeller outlet, strong unsteady interaction exists between the impeller inlet and the impeller outlet, the matching between the centrifugal impeller and the diffuser is deteriorated, the efficiency and the stable working range of the centrifugal compressor are greatly reduced, the design of the diffuser with low loss rate due to the compact structure is very challenging, and the design becomes a main technical obstacle for restricting the application of the high-pressure ratio centrifugal compressor to engineering practice.
The tubular diffuser is formed by a series of diffuser pipes which are uniformly distributed along the circumferential direction, two adjacent tubular diffuser channels are mutually penetrated at the inlet, so that a dovetail-shaped front edge is formed, and the special three-dimensional structure of the front edge has good applicability to high Mach number incoming flows and is very suitable for being used in a high-pressure ratio centrifugal compressor. However, the pipe diffuser is difficult to process and has high cost, so that the pipe diffuser is difficult to be used in engineering practice at present. Therefore, a new diffuser that can ensure the aerodynamic performance of a high pressure ratio centrifugal compressor while reducing the processing cost is needed. Chinese patent CN201610608677.2 discloses a vane diffuser with dovetail leading-trailing edge structure and its modeling method, which comprises a split design built-in radial diffuser vane and built-in axial diffuser vane, the diffuser can be creatively modified by traditional vane diffuser, and has the advantages of convenient modeling, low cost and simple processing, and its special dovetail leading-trailing edge can improve the adaptability of the diffuser to the high-speed unordered flow of centrifugal impeller outlet, thereby improving the efficiency and stable working margin of high-pressure ratio centrifugal compressor. However, the vane diffuser disclosed in the patent has the defects that the section of the passage is elliptical, so that the vortex strength of the passage is enhanced; meanwhile, after the air flow passes through the 90-degree bent pipe at the outlet of the radial diffuser, the air flow cannot be finely controlled by the wheel cover of the wheel disc, so that the air flow is more chaotic and has larger loss.
Disclosure of Invention
Aiming at the defects and shortcomings of the prior art, the technical problem to be solved by the invention is to provide a diffuser modeling method which has a dovetail-shaped front edge structure of a pipe diffuser and integrates radial diffuser blades and axial diffuser blades, and compared with the pipe diffuser, the vane diffuser has the advantages of convenient modeling, simple processing and low manufacturing cost by integrating the radial diffuser blades and the axial diffuser blades; compared with a common blade diffuser, the special three-dimensional fan-shaped structure of the front edge of the blade can better cope with complex unsteady flow of the impeller outlet; meanwhile, the radial and axial diffuser blades are integrally molded by adopting smooth transition molded lines at the runner part, so that the pressure ratio, the efficiency and the stable working margin of the centrifugal compressor with high pressure ratio are greatly improved in a limited flow space, and the centrifugal compressor is particularly suitable for the centrifugal compressors of medium and small aeroengines and miniature gas turbines.
In order to achieve the above purpose, the technical scheme provided by the invention is as follows:
a diffuser design method with dovetail leading edge and radial and axial blade integration, the diffuser includes a diffuser wheel disc, a diffuser shroud and a plurality of integrated diffuser blades arranged between the diffuser wheel disc and the diffuser shroud and uniformly distributed along the circumferential direction, the diffuser wheel disc and the diffuser shroud each include a radial segment and an axial segment, each integrated diffuser blade includes a radial blade segment and an axial blade segment, each radial blade segment is distributed between the radial segments of the diffuser wheel disc and the diffuser shroud, each axial blade segment is distributed between the axial segments of the diffuser wheel disc and the diffuser shroud, and a diffusion flow channel is formed between two adjacent integrated diffuser blades, the integrated modeling method of the integrated diffuser blades is characterized in that:
SS1, using the diffuser wheel disc or the diffuser wheel cover as a basal disc, machining a plurality of basic diffuser blades uniformly distributed along the circumferential direction on the basal disc in a machining mode, wherein each basic diffuser blade is molded by taking a blade of an existing vane type diffuser as a primitive blade, the radial blade segment of each basic diffuser blade is turned to the axial blade segment in a smooth transition mode, the front end of the radial blade segment is formed into the front edge of the basic diffuser blade, and the rear end of the axial blade segment is formed into the rear edge of the basic diffuser blade;
SS2, processing a fan-shaped curved surface structure on the front edge part of each basic diffuser blade, wherein the fan-shaped curved surface is tangent to a suction surface molded line of a blade channel throat part on the suction surface side of each basic diffuser blade, the fan-shaped curved surface is bent from the suction surface side of the blade towards the pressure surface side so as to adapt to the high-speed incoming flow Mach number of an impeller outlet, and the cutting depth of the fan-shaped curved surface from the suction surface side of the blade towards the pressure surface side is not greater than the length of the blade channel throat part so as to ensure that the area of the blade channel throat part is kept basically unchanged before and after cutting.
Preferably, in step SS2, when the fan-shaped curved surface structure is processed, a smooth Bezier curve is adopted on the basis of the front edge part of the blade of the base diffuser, and the curved surface is tangent to the line of the suction surface where the throat part of the blade channel is located, and the curved surface is curved towards the pressure side so as to adapt to the high-speed incoming flow mach number of the impeller outlet.
Preferably, in step SS2, in order to ensure that the base diffuser blade is introduced into the leading edge fan-shaped structure while ensuring that the throat area of the diffuser is not changed, the parameters of the throat length are introduced while performing the shaping of the primitive blade, but since the throat length is too long, the expansion capability of the diffuser is insufficient, and too short, the rectifying effect is poor, the throat length with a proper length needs to be determined according to the condition of the incoming flow.
Further, the leading edge of each primitive diffuser blade is controlled by a multipoint Bezier curve, and the size of the fan-shaped structure is determined according to the incoming flow condition, so that the throat area of the diffuser is basically unchanged before and after sectioning, and the sectioning depth cannot be longer than the throat length.
Preferably, in step SS1, the radial blade segment and the axial blade segment are smoothly connected by a Bezier curve, and the line of the suction surface and the pressure surface of the base diffuser blade are offset at a certain angle along the circumferential direction, and the channel center line is taken as an axisymmetric shape, so that the overall flow channel is ensured to be in a horn shape.
Further, the center line of the channel is controlled by a certain curvature, so that the molded lines of the suction surface and the pressure surface have better diffusion and diversion capability and lower loss.
Preferably, the shroud and the diffuser disk of the diffuser each include a radial portion and an axial portion, and the axial portions are disposed on an outer circumferential portion of the radial portion and are in smooth transition connection with each other. The diffuser shroud, diffuser disk and diffuser blades together comprise an integrated blade diffuser.
Preferably, the diffuser is arranged at the airflow outlet part of the centrifugal compressor, and the inlet radius R of the diffuser 3 The ratio of the centrifugal impeller to the centrifugal impeller outlet radius R2 is 1.03-1.1.
The present invention provides a radial/axial integrated vane diffuser having a tubular diffuser dovetail leading edge geometry at the diffuser inlet, with a vane-like diffuser-like passage formed in the diffuser passage.
Preferably, in step SS1, the expansion half angle of the base diffuser vanes for shaping is not more than 6 °, the ratio of the throat length L to the throat width of the vane passages is 1/3 to 1, and the number of diffuser vanes is 17 to 29.
Further, the size of the diffuser leading edge fan can be obtained by adjusting the leading edge Bezier control line; the cross-sectional area of the diffuser passage can be obtained by changing the front edge precompression angle of the primitive blades and the expansion half angle of the diffuser, so that the inlet-outlet area ratio of the diffuser can be adjusted.
Another object of the present invention is to provide a diffuser obtained by the above shaping method.
The invention also aims at providing a centrifugal compressor, which is characterized by comprising the diffuser.
Compared with the traditional vane diffuser, the vane diffuser with integrated tubular characteristics and radial/axial direction has the advantages that the fan-shaped front edge structure of the inlet of the vane diffuser has good adaptability to high Mach number airflow, and the efficiency and the stable working margin of the centrifugal compressor can be effectively improved in a compact space; compared with the tubular diffuser, the vane diffuser provided by the invention not only inherits the advantages of the tubular diffuser, but also can adopt the traditional vane diffuser processing technology, and effectively solves the problems of high processing difficulty, high cost, difficult guarantee of processing precision and the like of the tubular diffuser. In addition, the integrated diffuser modeling is adopted, so that the flow direction of fluid at a large corner can be effectively controlled, and the flow loss is effectively reduced, and therefore, the performance of the diffuser is higher than that of a traditional vane type diffuser and a pipe type diffuser.
Drawings
FIG. 1 is a schematic illustration of a fabricated diffuser with dovetail leading edge and radial and axial blade integration in accordance with the present invention.
FIG. 2 is a schematic illustration of an integrated disk configuration formed by integrated diffuser blades and diffuser shrouds.
FIG. 3 is a schematic diagram of the leading edge modeling parameters of the primitive blade profile.
FIG. 4 is a three-dimensional schematic view of a diffuser blade having a dovetail leading edge and integrated radial and axial blade segments.
Fig. 5 is a schematic view of the diffuser of the present invention applied to a high pressure ratio centrifugal compressor.
Reference numerals illustrate:
1-a diffuser wheel; 2-diffuser shroud; 3-fan-shaped leading edge; 4-integrated diffuser blades; 5-an integrated vane passage; 6-diffuser coupling bolts; 7-centrifugal compressor impeller; 8-R 3 Inlet radius for diffuser vanes; θ 1 Pre-pressing the contraction angle for the suction surface; θ 2 Is the angle of expansion of the runner; beta is the included angle between the center line of the runner and the coordinate x-axis.
Detailed Description
In order to make the objects, technical solutions and advantages of the present invention become more apparent, the technical solutions in the embodiments of the present invention will be described in more detail below with reference to the accompanying drawings in the embodiments of the present invention. In the drawings, the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The described embodiments are intended to be illustrative of the invention and should not be construed as limiting the invention in any way. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to be within the scope of the invention.
As shown in fig. 1 and 2, the diffuser with dovetail leading edge and integrated radial and axial blades of the present invention comprises a diffuser disk 1, a diffuser shroud 2, and a plurality of integrated diffuser blades 4. The diffuser wheel cover 1 and the diffuser wheel disc 2 comprise radial parts and axial parts, the axial parts are arranged on the outer circumferential parts of the radial parts, and the two parts are in smooth transition connection; the diffuser coupling bolts 6 secure the integrated diffuser blades 4 between the diffuser disk 1 and the diffuser shroud 2, which embodiment is suitable for use in high pressure ratio centrifugal compressors. The diffuser wheel cover 2 and the integrated diffuser blades 4 form an integral disc, the integrated diffuser blades are milled on the integral disc by a machine tool, and the radial-axial blade parts of the integrated diffuser need smooth transition in the milling process to form 17-29 integrated blades; a fan-shaped structure is milled at the front edge part of the diffuser, gradually becomes thicker along the channel and smoothly transits with the channel blades, and finally, the diffuser wheel disc 1, the diffuser wheel cover 2 and the integral disc formed by the integral diffuser blades are connected together by using the diffuser connecting bolts 6 to form an integral blade channel. In addition, during diffuser machining, it is necessary to ensure the diffuser inlet radius R 3 And the centrifugal impeller outlet radius R 2 The ratio is 1.03-1.1. The expansion half angle of the vane diffuser is not more than 6 DEG, the ratio of the diffuser throat length L to the diffuser throat width is 1/3-1, and the number of the diffuser vanes 4 is 17-29.
FIG. 3 shows the introduction of throat length L and precompression angle θ on the basis of conventional primitive blades 1 Equal design features, R 3 For radial diffuser blade inlet radius, θ 2 Is the angle of expansion of the runner; beta isAnd an included angle between the center line of the runner and the coordinate x-axis. When three-dimensional modeling is performed after the throat length characteristic is introduced, the cutting depth of the front edge fan shape cannot be longer than the throat length, so that the flow change range of the compressor before and after modification is basically unchanged. The cross-sectional area of the diffuser passage may be varied by varying the leading edge precompression angle θ of the primitive blades 1 And diffuser divergence angle θ 2 And the inlet/outlet area ratio of the diffuser is adjusted.
FIG. 4 illustrates a single integrated diffuser blade that is formed by introducing the throat length and precompression angle of a conventional primitive blade diffuser (FIG. 3) followed by a three-dimensional modeling and creative introduction of the leading edge scallop and integrated design modeling.
Fig. 5 shows an example of the application of the diffuser of the present invention to a high pressure ratio centrifugal compressor. The diffuser is at the outlet portion of the centrifugal compressor. During operation, the centrifugal impeller 7 rotates around the compressor shaft 8 to pressurize the air flow; the air flow then undergoes a deceleration boost through a diffuser passage comprised of a diffuser disk 1, a diffuser shroud 2 and integral diffuser vanes 4 before entering the combustion chamber. The centrifugal compressor has high rotating speed and high pressure ratio, and the distance between the inlet of the diffuser and the outlet of the impeller is very small, so that the Mach number Ma at the inlet of the diffuser is high, and meanwhile, due to the interaction between the leakage flow of the centrifugal impeller and the boundary layer near the wheel cover and the jet flow effect at the low-blade high position of the centrifugal impeller, the structure adopting the fan-shaped front edge can be well suitable for the incoming flow condition, and the efficiency and the stable working margin of the compressor can be effectively improved.
In summary, the radial/axial integrated vane diffuser can be directly used in centrifugal compressors and micro gas turbines of medium and small aviation gas turbine engines, and can improve the performance of the diffuser on the basis of not changing the prototype size and the processing and manufacturing cost, thereby improving the efficiency and the stable working margin of the compressors.
The object of the present invention is fully effectively achieved by the above-described embodiments. Those skilled in the art will appreciate that the present invention includes, but is not limited to, those illustrated in the drawings and described in the foregoing detailed description. While the invention has been described in connection with what is presently considered to be the most practical and preferred embodiment, it is to be understood that the invention is not limited to the disclosed embodiment, but on the contrary, is intended to cover various modifications and equivalent arrangements included within the scope of the appended claims.
Claims (12)
1. A diffuser design method with dovetail leading edge and radial and axial blade integration, the diffuser includes a diffuser wheel disc, a diffuser shroud and a plurality of integrated diffuser blades arranged between the diffuser wheel disc and the diffuser shroud and uniformly distributed along the circumferential direction, the diffuser wheel disc and the diffuser shroud each include a radial segment and an axial segment, each integrated diffuser blade includes a radial blade segment and an axial blade segment, each radial blade segment is distributed between the radial segments of the diffuser wheel disc and the diffuser shroud, each axial blade segment is distributed between the axial segments of the diffuser wheel disc and the diffuser shroud, and a diffusion flow channel is formed between two adjacent integrated diffuser blades, the integrated modeling method of the integrated diffuser blades is characterized in that:
the method comprises the following steps of SS1, using a diffuser wheel disc or a diffuser wheel cover as a base disc, machining a plurality of basic diffuser blades uniformly distributed along the circumferential direction on the base disc in a machining mode, wherein each basic diffuser blade is shaped by taking a blade of an existing vane type diffuser as a primitive blade, a radial blade segment of each basic diffuser blade is turned to an axial blade segment in a smooth transition mode, the front end of the radial blade segment is formed into the front edge of the basic diffuser blade, and the rear end of the axial blade segment is formed into the rear edge of the basic diffuser blade;
and SS2, processing a fan-shaped curved surface structure on the front edge part of each basic diffuser blade, wherein the fan-shaped curved surface is tangent to a suction surface molded line of the throat part of the blade channel on the suction surface side of the basic diffuser blade, the fan-shaped curved surface is bent from the suction surface side of the blade towards the pressure surface side so as to adapt to the high-speed incoming flow Mach number of an impeller outlet, and the cutting depth of the fan-shaped curved surface from the suction surface side of the blade towards the pressure surface side is not greater than the length of the throat part of the blade channel so as to ensure that the area of the throat part of the blade channel is kept basically unchanged before and after cutting.
2. The diffuser design method according to claim 1, wherein in step SS2, the fan-shaped curved surface structure is formed by adopting a smooth Bezier curve on the basis of the front edge portion of the base diffuser blade, and the curve is tangential to the suction surface line where the throat of the blade channel is located, and the curve is curved toward the pressure side to adapt to the high-speed incoming flow mach number of the impeller outlet.
3. The diffuser design method according to claim 1, wherein in step SS2, in order to ensure that the throat area of the diffuser is not changed while the base diffuser blade is introduced into the leading edge fan-shaped structure, the parameters of the throat length are introduced while the primitive blade is shaped, and the throat length having the proper length is determined according to the condition of the incoming flow.
4. The diffuser design method of claim 3, wherein each primitive diffuser blade leading edge is controlled by a multi-point Bezier curve, the size of the fan-shaped structure being determined based on the incoming flow conditions to ensure that the diffuser throat area is substantially constant before and after sectioning, the sectioning depth being no longer than the throat length.
5. The diffuser design method according to claim 1, wherein in step SS1, the radial blade segment and the axial blade segment are smoothly connected by Bezier curve, and the suction surface and the pressure surface of the basic diffuser blade are offset at a certain angle along the circumferential direction, and the channel center line is taken as an axisymmetric shape, so that the overall flow channel is ensured to be in a horn shape.
6. The diffuser design method according to claim 5, wherein the centerline of the passage is controlled by a curvature to provide better diffusing and guiding capabilities and less losses to the suction and pressure side profiles.
7. The method of claim 1, wherein the shroud and the disk of the diffuser each comprise a radial portion and an axial portion, the axial portions are disposed on an outer circumferential portion of the radial portion and are in smooth transition with each other, and the shroud, disk and blades together comprise an integrated blade diffuser.
8. The method of designing a diffuser according to claim 1, wherein the diffuser is disposed at an air outlet portion of the centrifugal compressor and has an inlet radius R 3 The ratio of the centrifugal impeller to the centrifugal impeller outlet radius R2 is 1.03-1.1.
9. The diffuser design method according to claim 1, wherein in step SS1, the expansion half angle of the basic diffuser blades for shaping is not more than 6 °, the ratio of the throat length L to the throat width of the blade channels is 1/3 to 1, and the number of diffuser blades is 17 to 29.
10. The diffuser design method of claim 9, wherein the size of the diffuser leading edge fan is obtained by adjusting a leading edge Bezier control line; the cross-sectional area of the diffuser passage is obtained by changing the leading edge precompression angle and the diffuser expansion half angle of the primitive blades, so that the inlet-outlet area ratio of the diffuser is adjusted.
11. A diffuser obtainable by the method of any one of claims 1 to 10.
12. A centrifugal compressor comprising the diffuser of claim 11.
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106089808A (en) * | 2016-07-28 | 2016-11-09 | 中南大学 | A kind of blade diffuser with trailing edge structures before swallow-tail form and formative method thereof |
| CN108386389A (en) * | 2018-02-08 | 2018-08-10 | 中国科学院工程热物理研究所 | A kind of centrifugal compressor diffuser structure that blade is blended with casing and wheel hub |
| CN108644152A (en) * | 2018-04-04 | 2018-10-12 | 中国航发湖南动力机械研究所 | Diffuser twisted blade and design method, diffuser and centrifugation/inclined flow air compressor |
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Patent Citations (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN106089808A (en) * | 2016-07-28 | 2016-11-09 | 中南大学 | A kind of blade diffuser with trailing edge structures before swallow-tail form and formative method thereof |
| CN108386389A (en) * | 2018-02-08 | 2018-08-10 | 中国科学院工程热物理研究所 | A kind of centrifugal compressor diffuser structure that blade is blended with casing and wheel hub |
| CN108644152A (en) * | 2018-04-04 | 2018-10-12 | 中国航发湖南动力机械研究所 | Diffuser twisted blade and design method, diffuser and centrifugation/inclined flow air compressor |
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