CN220101610U - Blade structure of axial flow compressor for medium-sized blast furnace - Google Patents
Blade structure of axial flow compressor for medium-sized blast furnace Download PDFInfo
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Abstract
The utility model relates to a blade profile structure of an axial flow compressor for a medium-sized blast furnace, which mainly solves the technical problems that the existing axial flow compressor for the medium-sized blast furnace adopts an N-series blade profile structure, has lower tangential velocity and poorer working capacity, and generally needs sixteen to seventeen stages of blades to meet the pressure requirement of a compression process. The device comprises a movable blade and a stationary blade with nine stages; the movable blades and the stationary blades are controllable diffusion blade shapes with the surface isentropic Mach number peak positions within the axial chord length range of 8% -15%, and the front edges are curvature continuous front edges; the blade of the stationary blade is a composite curved blade with a curved shape, and the stacking line is a three-order Bezier curve shape.
Description
Technical Field
The utility model relates to an axial flow compressor blade profile structure, in particular to an axial flow compressor blade profile structure for a medium-sized blast furnace.
Background
Currently, the furnace volume on the market is 1800m 3 -2700m 3 The axial flow compressor for the medium-sized blast furnace adopts an N-series blade-shaped structure, has lower tangential velocity and poorer acting capability, and generally needs sixteen to seventeen stages of blades to meet the pressure requirement of the compression process. For example, 1800m is available 3 The axial flow compressor for the medium-sized blast furnace adopts sixteen-stage axial flow compressor technical proposal, adopts the prior N-series blade profile technology, has the circumferential speed at the inner diameter hub of 170-175m/s, has the flow coefficient of 0.7, the load coefficient of 0.3-0.35, has the single-stage average pressure ratio of 1.13, and has the defects of multiple stages, complex structure, low efficiency and the like.
Disclosure of Invention
The utility model aims to solve the technical problems that the existing axial flow compressor for the medium-sized blast furnace adopts an N-series blade profile structure, has lower tangential velocity and poorer acting capability, and generally needs sixteen to seventeen stages of blades to meet the pressure requirement of a compression process, and provides the blade profile structure of the axial flow compressor for the medium-sized blast furnace.
In order to achieve the above purpose, the technical scheme adopted by the utility model is as follows:
the blade structure of the axial flow compressor for the medium-sized blast furnace is characterized in that: the device comprises a movable blade and a stationary blade with nine stages;
the movable blades and the stationary blades are controllable diffusion blade shapes with the surface isentropic Mach number peak positions within the axial chord length range of 8% -15%, and the front edges are curvature continuous front edges;
the blade of the stationary blade is a composite curved blade with a curved shape, and the stacking line is a three-order Bezier curve shape. Further, the chord length of the blade profile of the movable blade ranges from 75mm to 268mm, and the aspect ratio of the blade profile ranges from 1.39 to 1.53; the maximum relative thickness of the blade root sections of the movable blades at each stage is within the range of 10% -15%;
the vane profile chord length of the stator vane ranges from 40mm to 189mm, and the aspect ratio ranges from 1.8 to 2.2; the blade stacking line of the stator blade has the following characteristics: the demarcation point of the upper section and the middle arc section of the blade is between 62% and 70%, and the demarcation point of the lower section and the middle arc section is between 29% and 37%; the included angle between the tangent line of the upper segment stacking line of the blade and the radial direction is 0-15 degrees, and the included angle between the tangent line of the lower segment stacking line and the circumferential direction is 0-15 degrees.
Further, the geometric parameters of the first stage bucket are shown in the following table:
the geometry parameters of the first stage vane are shown in the following table:
the geometric parameters of the second stage bucket are shown in the following table:
the geometry of the second stage vane is shown in the following table:
the geometry of the third stage bucket is shown in the following table:
the geometry parameters of the third stage vane are shown in the following table:
the geometry parameters of the fourth stage bucket are shown in the following table:
the geometry parameters of the fourth stage vane are shown in the following table:
the geometric parameters of the fifth stage bucket are shown in the following table:
the geometric parameters of the fifth stage vane are shown in the following table:
the geometric parameters of the sixth stage bucket are shown in the following table:
the geometry parameters of the sixth stage vane are shown in the following table:
the geometry parameters of the seventh stage bucket are shown in the following table:
the geometry parameters of the seventh stage vane are shown in the following table:
the geometry parameters of the eighth stage bucket are shown in the following table:
the geometry parameters of the eighth stage vane are shown in the following table:
the geometry parameters of the ninth stage bucket are shown in the following table:
the geometry parameters of the ninth stage vane are shown in the following table:
further, the material of the movable blades and the stationary blades is high-strength alloy steel material X3CrNiMo13-4.
The utility model combines the characteristics of wide operation range of the axial flow compressor for blast furnace blast and high single-stage average pressure-equalizing ratio of the axial flow compressor of the aeroengine in the prior art, and the proposed blade profile structure of the axial flow compressor for medium-sized blast furnace is called as a mixed concept blade profile structure so as to pursue the optimal combination of the axial flow compressor technology for blast furnace blast and the blade profile structure of the axial flow compressor of the aeroengine. The axial flow compressor for blast furnace blast has higher requirement on the equivalent pressure ratio flow range and efficiency of non-design points, so that the aerodynamic load coefficient cannot be higher than 0.35, and therefore, compared with the axial flow compressor in the prior art, the aerodynamic load level of the novel mixed configuration blade is kept unchanged, and a higher single-stage average pressure ratio is obtained by a method of improving the tangential speed by 30% -40%, so that the novel axial flow compressor with more compactness and fewer stages is obtained. Each stage in the aerodynamic through-flow configuration is still maintained in a high subsonic flow state, and shock wave loss and shock wave induced boundary layer loss in the axial flow compressor of the aeroengine are not generated.
Compared with the prior art, the utility model has the beneficial effects that:
1. compared with sixteen or seventeen stages of axial flow compressor blade profile technology in the prior art, the mixed concept blade profile structure provided by the utility model has the advantages that the rotating speed is improved by 37%, the stage number is reduced by 44%, the efficiency is improved by 2% at most, and the power consumption is reduced by 3% at most. The nine-stage axial flow compressor for the medium-sized blast furnace adopting the blade-shaped structure has the circumferential speed of 190-244m/s at the inner diameter hub and the nine-stage average stage pressure ratio of 1.21. Taking the axial flow compressor for medium-sized blast furnace with rated power of 31000kw as an example, the energy-saving effect can save more than 702 ten thousand degrees of electricity per station per year on the basis of the axial flow compressor in the prior art, and further reduce the carbon emission amount of 190944 kg per station.
2. The novel nine-stage axial flow compressor for the medium-sized blast furnace is based on a novel independent development of an air-driven design and analysis system of the novel axial flow compressor, and is designed into the three-dimensional blade with the mixed configuration with high single-stage average pressure ratio, high efficiency and high reliability, and the sixteen-stage pressure ratio level of the axial flow compressor in the prior art can be realized by only adopting nine stages, so that the structural complexity, the size weight and the occupied area of the axial flow compressor for the medium-sized blast furnace are greatly reduced.
Drawings
FIG. 1 is a schematic diagram of a comparison of a profile of an embodiment of the present utility model with a conventional profile;
FIG. 2 is a schematic view of the outline of the moving blades and stationary blades in an embodiment of a blade profile structure of an axial flow compressor for a medium-sized blast furnace according to the present utility model;
FIG. 3 is a schematic view of a profile and prior art N-series profile surface Mach number distribution in accordance with an embodiment of the present utility model;
FIG. 4 is a graph of vane pattern loss versus inlet air flow angle for an embodiment of the present utility model for an N series of vane patterns of the prior art;
FIG. 5 is a graph of pressure coefficient profiles for a profiled leading edge in accordance with an embodiment of the present utility model and a profiled leading edge of the prior art, wherein the dashed line represents a circular arc leading edge, the solid line represents an elliptical leading edge, and the two-dot chain line represents a curvature continuous leading edge;
FIG. 6 is a three-dimensional outline schematic of a bucket according to an embodiment of the present utility model;
FIG. 7 is a three-dimensional profile schematic of a vane blade in an embodiment of the utility model;
FIG. 8 is a schematic view of a third order Bessel stacking line for a vane blade in an embodiment of the utility model;
figure 9 is a graph of relative mach number clouds for 10%, 50% and 90% of the leaf spreads in an embodiment of the present utility model.
In the figure: 1-movable blade and 2-stationary blade.
Detailed Description
In order to make the objects, advantages and features of the present utility model more apparent, the following describes in further detail a blade profile structure of an axial flow compressor for medium-sized blast furnaces in accordance with the accompanying drawings and specific examples. The advantages and features of the present utility model will become more apparent from the following detailed description. It should be noted that: the drawings are in a very simplified form and are all to a non-precise scale, merely for convenience and clarity in aiding in the description of embodiments of the utility model; second, the structures shown in the drawings are often part of the actual structure.
As shown in fig. 1-9, the blade type structure of the axial flow compressor for the medium-sized blast furnace provided by the utility model comprises a movable blade 1 and a stationary blade 2 with nine stages as shown in fig. 2.
As shown in FIG. 6, the movable blade 1 adopts a mixed blade profile structure of a controllable diffusion blade profile and a wide chord blade, the chord length of the blade profile of the movable blade 1 ranges from 75mm to 268mm, and the aspect ratio of the blade profile is 1.39 to 1.53; the maximum relative thickness of the blade root sections of the movable blades 1 at each stage is within the range of 10% -15%; compared with the prior art, the axial flow compressor has the advantages that N series of blade profiles are wider and thicker, the aerodynamic performance is better, the polytropic efficiency is improved by 1-2% at each working condition point in the application range of the medium-sized blast furnace, and the anti-surge capacity of the blades is greatly improved.
The static blade 2 adopts a mixed blade profile structure of a controllable diffusion blade profile and a composite curved blade, and the stacking line is in a three-order Bezier curve shape; each stage of stationary blade 2 adopts a full three-dimensional modeling concept, the parameters of each section of the blade profile change along with the height of the blade profile, the chord length range of the blade profile of the stationary blade 2 is 40mm-189mm, and the aspect ratio range is 1.8-2.2; as shown in fig. 7, a schematic view of a third-order bessel stacking line of the stator blade 2 is shown in fig. 8, an included angle between a tangent line of an upper stacking line and a radial direction is B2, an included angle between a tangent line of a lower stacking line and a circumferential direction is B1, a boundary point between an upper blade section and a middle arc section is P1, and a boundary point between a lower blade section and the middle arc section is P2. The boundary point P1 of the upper section and the middle arc section of the blade is between 62% and 70%, and the boundary point P2 of the lower section and the middle arc section is between 29% and 37%; the included angle between the tangent line of the upper segment stacking line and the radial direction is 0-15 degrees, and the included angle between the tangent line of the lower segment stacking line and the circumferential direction is 0-15 degrees.
The range of geometrical parameters of each stage of movable blades 1 and static blades 2 is as follows, and the geometrical parameters of the first stage of movable blades are shown in the following table:
the geometry parameters of the first stage vane are shown in the following table:
the geometric parameters of the second stage bucket are shown in the following table:
the geometry of the second stage vane is shown in the following table:
the geometry of the third stage bucket is shown in the following table:
the geometry parameters of the third stage vane are shown in the following table:
the geometry parameters of the fourth stage bucket are shown in the following table:
the geometry parameters of the fourth stage vane are shown in the following table:
the geometric parameters of the fifth stage bucket are shown in the following table:
the geometric parameters of the fifth stage vane are shown in the following table:
the geometric parameters of the sixth stage bucket are shown in the following table:
the geometry parameters of the sixth stage vane are shown in the following table:
the geometry parameters of the seventh stage bucket are shown in the following table:
the geometry parameters of the seventh stage vane are shown in the following table:
the geometry parameters of the eighth stage bucket are shown in the following table:
the geometry parameters of the eighth stage vane are shown in the following table:
the geometry parameters of the ninth stage bucket are shown in the following table:
the geometry parameters of the ninth stage vane are shown in the following table:
as shown in FIG. 3, the blade profiles of the movable blades 1 and the stationary blades 2 in the utility model are controllable diffusion blade profiles with the surface isentropic Mach number peak positions within the axial chord length range of 8% -15%, the surface isentropic Mach number peak positions are closer to the front edge than the N series blade profiles used in the axial flow compressor in the prior art, the low loss attack angle range of the blade profiles is enlarged, the loss coefficient is also reduced, i is attack angle in FIG. 4, and ω is blade profile loss.
In the prior art, the axial flow compressor generally adopts an arc leading edge blade profile and an elliptic leading edge blade profile, which have the pneumatic defect that the curvature at the leading edge is discontinuous, so that a larger pressure protruding point exists at the leading edge, and the pneumatic loss is increased. The vane type structure of the movable vane 1 and the stationary vane 2 adopts the curvature continuous front edge, so that the pressure sharp at the front edge can be eliminated, the performance loss is reduced, the flow loss is reduced, the working range is enlarged while the high single-stage supercharging ratio and the working capacity are realized, and the upper efficiency limit of the axial flow compressor in the prior art is broken through, as shown in figure 5.
Fig. 9 is a graph of relative mach number clouds of 10%, 50% and 90% of the leaf spreads of nine-stage axial flow compressors for medium-sized blast furnaces, each stage She Pailiu field is well organized, without boundary layer separation zones leading to high losses.
The centrifugal force and static stress are increased due to the increase of the tangential speed of the hub, the material 2Cr13 used by the movable blades and the static blades in the axial flow compressor in the prior art is not applicable any more due to the lower yield limit, and the movable blades and the static blades of the nine-stage axial flow compressor are made of high-strength stainless steel materials X3CrNiMo13-4, and the yield limit reaches 800MPa.
Claims (4)
1. The utility model provides a medium-sized axial compressor blade form structure for blast furnace which characterized in that:
comprises a movable blade (1) and a stationary blade (2) with nine stages;
the movable blades (1) and the stationary blades (2) are controllable diffusion blade shapes with the surface isentropic Mach number peak positions in the axial chord length range of 8% -15%, and the front edges are curvature continuous front edges;
the movable blade (1) is a wide chord blade;
the blade of the stator blade (2) is a composite curved blade, and the stacking line is a three-order Bezier curve.
2. The axial flow compressor blade form structure for medium size blast furnace according to claim 1, wherein: the chord length of the blade profile of the movable blade (1) ranges from 75mm to 268mm, and the aspect ratio of the blade profile ranges from 1.15 to 1.75; the maximum relative thickness of the blade root sections of the movable blades (1) at each stage is within the range of 10% -15%;
the vane profile chord length of the stator blade (2) ranges from 40mm to 189mm, and the aspect ratio ranges from 1.8 to 2.2; the stacking line on the stator blade (2) has the following characteristics: the demarcation point of the upper section and the middle arc section of the blade is between 62% and 70%, and the demarcation point of the lower section and the middle arc section is between 29% and 37%; the included angle between the tangent line of the upper segment stacking line of the blade and the radial direction is 0-15 degrees, and the included angle between the tangent line of the lower segment stacking line and the circumferential direction is 0-15 degrees.
3. The axial flow compressor blade form structure for medium size blast furnace according to claim 2, wherein:
the geometry of the first stage bucket is shown in the following table:
the geometry parameters of the first stage vane are shown in the following table:
the geometric parameters of the second stage bucket are shown in the following table:
the geometry of the second stage vane is shown in the following table:
the geometry of the third stage bucket is shown in the following table:
the geometry parameters of the third stage vane are shown in the following table:
the geometry parameters of the fourth stage bucket are shown in the following table:
the geometry parameters of the fourth stage vane are shown in the following table:
the geometric parameters of the fifth stage bucket are shown in the following table:
the geometric parameters of the fifth stage vane are shown in the following table:
the geometric parameters of the sixth stage bucket are shown in the following table:
the geometry parameters of the sixth stage vane are shown in the following table:
the geometry parameters of the seventh stage bucket are shown in the following table:
the geometry parameters of the seventh stage vane are shown in the following table:
the geometry parameters of the eighth stage bucket are shown in the following table:
the geometry parameters of the eighth stage vane are shown in the following table:
the geometry parameters of the ninth stage bucket are shown in the following table:
the geometry parameters of the ninth stage vane are shown in the following table:
4. the axial flow compressor blade form structure for medium sized blast furnace according to claim 3, wherein: the material of the movable blades (1) and the stationary blades (2) is high-strength alloy steel material X3CrNiMo13-4.
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| Application Number | Priority Date | Filing Date | Title |
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| CN202320851667.7U CN220101610U (en) | 2023-04-17 | 2023-04-17 | Blade structure of axial flow compressor for medium-sized blast furnace |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202320851667.7U CN220101610U (en) | 2023-04-17 | 2023-04-17 | Blade structure of axial flow compressor for medium-sized blast furnace |
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| CN220101610U true CN220101610U (en) | 2023-11-28 |
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