CN216430054U - Mixed-flow compressor blade structure for air separation device - Google Patents

Mixed-flow compressor blade structure for air separation device Download PDF

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Publication number
CN216430054U
CN216430054U CN202122393327.8U CN202122393327U CN216430054U CN 216430054 U CN216430054 U CN 216430054U CN 202122393327 U CN202122393327 U CN 202122393327U CN 216430054 U CN216430054 U CN 216430054U
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blade
following table
stage
geometry
range
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王雷
陈党民
张利民
陈江辉
田满洲
张暖
王晓红
谭小平
杨岐平
王仪田
王林英
刘妮
王冬
王小坤
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Xian Shaangu Power Co Ltd
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Xian Shaangu Power Co Ltd
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Abstract

The utility model relates to a turbomachinery field, concretely relates to mixed-flow compressor blade profile structure for air separation plant to solve current 10-20 ten thousand cubic meters mixed-flow compressor for air separation plant and adopt circular arc leading edge blade profile, oval leading edge blade profile all to have the discontinuous defect of camber, make the leading edge have great pressure to suddenly sharp, increased aerodynamic loss, lead to tangential velocity lower, the acting capacity is relatively poor, generally need eight to ten grades of axial flows just can satisfy the problem of technology demand. The mixed-flow compressor blade profile structure comprises movable blades and static blades with 4-7 stages; the movable blade type is a front transition blade type with transition position in the range of 8% -12% of axial chord length, and the front edge of the movable blade type is a curvature continuous front edge; the stationary blade profile is a front transition blade profile with a transition position in the range of 8% -12% of axial chord length, and the front edge of the stationary blade profile is a curvature continuous front edge; the static blade is an arched blade, and the stacking line of the static blade is in a three-order Bezier curve shape.

Description

Mixed-flow compressor blade structure for air separation device
Technical Field
The utility model relates to a turbomachinery field, concretely relates to mixed-flow compressor blade profile structure for air separation plant.
Background
At present, the mixed-flow compressor for the air separation device of 10-20 ten thousand cubic meters grade on the market generally uses the existing industrial axial flow compressor technology, and the adopted arc leading edge blade profile and the adopted oval leading edge blade profile have the defect of discontinuous curvature, so that the leading edge has larger pressure sharp, the pneumatic loss is increased, the tangential velocity is lower, the working capacity is poorer, and the process requirement can be met by generally adopting eight-to ten-grade axial flow. For example, the axial flow section of the existing ten thousand air separation mixed flow compressor adopts a ten-stage axial flow compressor scheme and adopts the existing NACA65 low-speed blade profile technology, the circumferential speed at the inner diameter hub is within the range of 170-175m/s, the flow coefficient is 0.7, the load coefficient is 0.3-0.35, the single-stage pressure ratio is 1.13, and the defects of multiple stages, complex structure, low efficiency, high production cost and the like exist.
SUMMERY OF THE UTILITY MODEL
The utility model aims at solving current 10-20 ten thousand cubic meters for air separation plant mixed flow compressor adopt circular arc leading edge blade profile, oval leading edge blade profile all to have the discontinuous defect of camber for there is great pressure sharp in the leading edge, has increased aerodynamic loss, results in tangential velocity lower, and the acting capacity is relatively poor, generally needs eight to ten grades of axial flows just can satisfy the problem of technology demand, and provides a mixed flow compressor blade profile structure for air separation plant.
In order to achieve the above purpose, the utility model adopts the technical scheme that:
a mixed-flow compressor blade structure for an air separation device is characterized in that:
the device comprises movable blades and static blades with 4-7 stages;
the movable blade type is a front transition blade type with a transition position in the range of 8% -12% of axial chord length, and the front edge of the movable blade type is a curvature continuous front edge;
the stator blade type is a front transition blade type with a transition position in the range of 8% -12% of axial chord length, and the front edge of the stator blade type is a curvature continuous front edge; the static blade is an arched blade, and the stacking line of the static blade is in a three-order Bezier curve shape.
Further, the chord length range of the movable vane profile is 75-268mm, and the aspect ratio range of the movable vane profile is 1.39-1.53; the maximum relative thickness of the blade root section of each stage of movable blade is within the range of 12-15%;
the chord length range of the stationary blade profile is 40-189mm, and the aspect ratio range of the stationary blade profile is 2.05-2.2; the stator blade stacking line has the following characteristics: the dividing point of the upper section of the blade and the middle straight line section is between 62 and 70 percent, and the dividing point of the lower section and the middle straight line section is between 29 and 37 percent; the included angle between the tangent line of the upper section of the stacking line and the radial direction is 0-5 degrees, and the included angle between the tangent line of the lower section of the stacking line and the circumferential direction is 0-5 degrees.
Further, the thickness of the front edge of the movable blade profile ranges from 0.4 mm to 2.7 mm.
Further, the number of stages is 6 stages.
Further, the first stage bucket geometry ranges are shown in the following table:
Figure BDA0003289672300000021
the first stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003289672300000022
the second stage bucket geometry ranges are shown in the following table:
Figure BDA0003289672300000023
Figure BDA0003289672300000031
the second stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003289672300000032
the third stage bucket geometry ranges are shown in the following table:
Figure BDA0003289672300000033
the third stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003289672300000034
the range of the geometric parameters of the fourth stage bucket is shown in the following table:
Figure BDA0003289672300000035
Figure BDA0003289672300000041
the fourth stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003289672300000042
the range of the geometric parameters of the fifth stage bucket is shown in the following table:
Figure BDA0003289672300000043
the fifth stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003289672300000044
Figure BDA0003289672300000051
the range of the geometric parameters of the sixth stage bucket is shown in the following table:
Figure BDA0003289672300000052
the sixth stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003289672300000053
further, the first stage bucket geometry is as shown in the following table:
Figure BDA0003289672300000054
Figure BDA0003289672300000061
the first stage vane geometry is as follows:
Figure BDA0003289672300000062
the second stage bucket geometry is shown in the following table:
Figure BDA0003289672300000063
the second stage vane geometry parameters are shown in the following table:
Figure BDA0003289672300000064
the third stage bucket geometry is shown in the following table:
Figure BDA0003289672300000065
Figure BDA0003289672300000071
the third stage vane geometry is as follows:
Figure BDA0003289672300000072
the fourth stage bucket geometry is shown in the following table:
Figure BDA0003289672300000073
the fourth stage vane geometry is shown in the following table:
Figure BDA0003289672300000074
the fifth stage bucket geometry is shown in the following table:
Figure BDA0003289672300000075
Figure BDA0003289672300000081
the fifth stage vane geometry is shown in the following table:
Figure BDA0003289672300000082
the sixth stage bucket geometry is shown in the following table:
Figure BDA0003289672300000083
the sixth stage vane geometry is shown in the following table:
Figure BDA0003289672300000084
furthermore, the movable blades and the static blades are made of a stainless steel material X3CrNiMo 13-4.
The utility model discloses compare prior art's beneficial effect is:
the utility model provides a mixed flow compressor blade profile structure for air separation plant, the high-grade pressure based on independently developing compares the pneumatic design of axial compressor and analysis system, and the design has the high-grade pressure to compare, high efficiency and high reliability's novel blade, only adopts four to seven grades (preferred six grades) can realize the ten grades of pressure ratio levels of traditional axial compressor, and tangential velocity is high, and the ability of doing work is strong, can effectively improve air separation plant's running cost, reduces manufacturing cost.
The mixed flow compressor adopting the vane structure of the utility model has the peripheral speed of the hub at the inner diameter of the compressor being 190-244m/s, the flow coefficient being 0.5-0.55, the load coefficient being 0.35 and the single-stage pressure ratio being 1.2.
Drawings
FIG. 1 is a schematic diagram of the blade structure of the present invention compared with the existing blade structure;
fig. 2 is a schematic diagram comparing the leading edge of the blade profile of the present invention with the leading edge of the blade profile of the prior art, wherein a is a schematic diagram of the prior art-circular leading edge, b is a schematic diagram of the prior art-elliptical leading edge, and c is a schematic diagram of the present invention-curvature continuous leading edge;
FIG. 3 is a pressure coefficient profile of a prior art airfoil leading edge and airfoil leading edge of the present invention wherein the dashed line represents a circular arc leading edge, the solid line represents an elliptical leading edge, and the dashed double-dotted line represents a curvature continuous leading edge;
FIG. 4 is a graph showing the distribution of the surface Mach number of the airfoil of the present invention and the existing airfoil;
FIG. 5 is a graph of the loss-inlet draft angle distribution for the airfoil of the present invention and the existing airfoil;
FIG. 6 is a schematic view of a stator blade according to the present invention;
FIG. 7 is a third order Bessel product overlay of a middle stator blade according to the present invention;
FIG. 8 is a schematic view of the flow channels and blade profiles of the mixed-flow compressor 6-stage axial flow section for a 10-20 million cubic meter class air separation plant using the inventive vane structure;
FIG. 9 is a relative mach number cloud plot of 10% span of the mixed flow compressor 6 stage axial flow section for a 10-20 million cubic meter class air separation plant using the inventive lobed configuration;
FIG. 10 is a relative mach number cloud plot of 50% span of the mixed flow compressor 6 stage axial flow section for a 10-20 million cubic meter class air separation plant using the inventive lobed structure;
FIG. 11 is a relative Mach number cloud plot of 90% span of the mixed flow compressor 6 stage axial flow section for a 10-20 million cubic meter class air separation plant using the inventive lobed structure.
Detailed Description
The mixed-flow compressor blade structure for an air separation device provided by the present embodiment includes a movable blade and a stationary blade having 6 stages.
The movable blade type is a front transition blade type with transition position in the range of 8% -12% of axial chord length, the front edge of the movable blade type is a curvature continuous front edge, and the thickness range of the front edge is 0.4-2.7 mm; the chord length range of the movable blade profile is 75-268mm, the chord length is increased by 40-50% compared with the chord length of the traditional blade, and the aspect ratio range is 1.39-1.53; the thickness of the tail edge is increased by 230 percent to reach 3.2mm, so that the crack expansion caused by erosion can be avoided; the maximum relative thickness of the blade root section of each stage of movable blade is within the range of 12% -15%, and is increased by 20% compared with the traditional blade.
The stationary blade profile is a front transition blade profile with a transition position in the range of 8% -12% of axial chord length, and the front edge of the stationary blade profile is a curvature continuous front edge; the chord length range of the stationary blade profile is 40-189mm, and the aspect ratio range of the stationary blade profile is 2.05-2.2; the stator blade is an arched blade, and the stacking line of the stator blade has the modeling characteristics of a three-order Bezier curve: the dividing point of the upper section of the blade and the middle straight line section is between 62 and 70 percent, and the dividing point of the lower section and the middle straight line section is between 29 and 37 percent; the included angle between the tangent line of the upper section of the stacking line and the radial direction is 0-5 degrees, and the included angle between the tangent line of the lower section of the stacking line and the circumferential direction is 0-5 degrees.
The ranges of the geometric parameters of each stage of the movable blade and the static blade are as follows:
the first stage bucket geometry ranges are shown in the following table:
Figure BDA0003289672300000101
the first stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003289672300000102
the second stage bucket geometry ranges are shown in the following table:
Figure BDA0003289672300000103
Figure BDA0003289672300000111
the second stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003289672300000112
the third stage bucket geometry ranges are shown in the following table:
Figure BDA0003289672300000113
the third stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003289672300000114
Figure BDA0003289672300000121
the range of the geometric parameters of the fourth stage bucket is shown in the following table:
Figure BDA0003289672300000122
the fourth stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003289672300000123
the range of the geometric parameters of the fifth stage bucket is shown in the following table:
Figure BDA0003289672300000124
Figure BDA0003289672300000131
the fifth stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003289672300000132
the sixth stage bucket geometry ranges are shown in the following table:
Figure BDA0003289672300000133
the sixth stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003289672300000134
preferably, the first stage bucket geometry is as shown in the following table:
Figure BDA0003289672300000141
the first stage vane geometry is as follows:
Figure BDA0003289672300000142
the second stage bucket geometry is shown in the following table:
Figure BDA0003289672300000143
the second stage vane geometry parameters are shown in the following table:
Figure BDA0003289672300000144
Figure BDA0003289672300000151
the third stage bucket geometry is shown in the following table:
Figure BDA0003289672300000152
the third stage vane geometry is as follows:
Figure BDA0003289672300000153
the fourth stage bucket geometry is shown in the following table:
Figure BDA0003289672300000154
the fourth stage vane geometry is as shown in the following table:
Figure BDA0003289672300000155
Figure BDA0003289672300000161
the fifth stage bucket geometry is shown in the following table:
Figure BDA0003289672300000162
the fifth stage vane geometry is shown in the following table:
Figure BDA0003289672300000163
the sixth stage bucket geometry is shown in the following table:
Figure BDA0003289672300000164
the sixth stage vane geometry is shown in the following table:
Figure BDA0003289672300000165
Figure BDA0003289672300000171
as shown in FIG. 1, the blade profile structure of the present invention employs a forward transition blade profile with a wide chord length and a continuous front edge of curvature, the two-dimensional blade profile cross section of each stage of the movable blade and the stationary blade is designed according to the local flow characteristics, and each section parameter of the movable blade profile and the stationary blade profile changes with the height of the blade profile. As shown in FIG. 2 and FIG. 3, the arc leading edge blade profile and the elliptical leading edge blade profile adopted by the existing industrial axial flow compressor all have the defect of discontinuous curvature, which causes the leading edge to have a large pressure sharp point, increases the pneumatic loss, and the blade profile structure of the utility model adopts the curvature continuous leading edge, can eliminate the pressure sharp point and reduce the performance loss. In fig. 3, the dotted line represents an arc front edge, the solid line represents an ellipse front edge, the two-dot chain line represents a curvature continuous front edge, the pressure coefficient sharp of the arc front edge is the largest, the loss is the highest, the ellipse arc is the second, the pressure sharp and the loss of the curvature continuous front edge are the smallest, it can be seen that the curvature continuous front edge can weaken the front edge suction surface mach number sharp, avoid the air flow from separating in a large range on the blade type suction surface in the high subsonic mach number environment, and have a wider range of attack angle of incoming flow, thereby reducing the flow loss, increasing the working range and breaking through the upper limit of the efficiency of the existing industrial axial flow compressor under the high supercharging ratio and the working capacity.
In order to improve the surge resistance of the blades, the front transition blade profile which is customized and developed aiming at the high Reynolds number flow environment in the large-scale air separation compressor is adopted in the design of the movable blades, and compared with the NACA65 blade profile used in the traditional compressor, the front transition blade profile is wider and thicker and has better pneumatic performance, and the polytropic efficiency is improved by 1-1.5% at each working condition point. As shown in fig. 4 and 5, the utility model discloses the blade profile structure is for adapting to the large-scale empty high reynolds number environment of flowing, and mach number peak position is close to the blade leading edge more, and with transition point position coincidence, has increased the low-loss angle of attack scope of blade profile, and the loss coefficient also reduces to some extent. In FIG. 4, β 1 is the flow angle and Ma1 is the inlet Mach number.
The shape of the stator blade is shown in fig. 6, the three-step bessel stacking line of the stator blade is shown in fig. 7, the included angle between the tangent of the upper-section stacking line and the radial direction is B2, the included angle between the tangent of the lower-section stacking line and the circumferential direction is B1, the dividing point between the upper section of the blade and the middle straight section is P1, and the dividing point between the lower section of the blade and the middle straight section is P2.
The flow channel and the blade outline of the mixed-flow compressor 6-stage axial flow section for the 10-20-kilometric grade air separation device with the blade structure of the utility model are shown in figure 8, wherein the black line is the outline of a movable impeller, and the gray line is the outline of a static impeller.
Fig. 9, fig. 10, fig. 11 are respectively the relative mach number cloud charts of 10%, 50% and 90% of the mixed-flow compressor 6-stage axial flow section for the 10-20 ten thousand cubic meter grade air separation device using the blade structure of the present invention, and it can be seen that the structure of the discharge field of each stage of blade is good, and there is no boundary layer separation zone causing high loss.
The centrifugal force and the static stress are increased due to the fact that the peripheral speed of the hub is increased, the material 2Cr13 used by the movable blades and the static blades in the existing axial-flow compressor is not applicable due to low yield limit, and the high-strength stainless steel material X3CrNiMo13-4 is used, so that the yield limit reaches 800 MPa.

Claims (7)

1. The utility model provides a mixed-flow compressor blade profile structure for air separation plant which characterized in that:
the device comprises movable blades and fixed blades with 4-7 stages;
the movable blade type is a front transition blade type with a transition position in the range of 8% -12% of axial chord length, and the front edge of the movable blade type is a curvature continuous front edge;
the stator blade type is a front transition blade type with a transition position in the range of 8% -12% of axial chord length, and the front edge of the stator blade type is a curvature continuous front edge; the static blade is an arched blade, and the stacking line of the static blade is in a three-order Bezier curve shape.
2. The mixed-flow compressor blade-type structure for an air separation plant according to claim 1, characterized in that:
the range of the chord length of the movable vane profile is 75-268mm, and the range of the aspect ratio of the movable vane profile is 1.39-1.53; the maximum relative thickness of the blade root section of each stage of movable blade is within the range of 12-15%;
the chord length range of the stationary blade profile is 40-189mm, and the aspect ratio range of the stationary blade profile is 2.05-2.2; the stator blade stacking line has the following characteristics: the dividing point of the upper section of the blade and the middle straight line section is between 62 and 70 percent, and the dividing point of the lower section and the middle straight line section is between 29 and 37 percent; the included angle between the tangent line of the upper section of the stacking line and the radial direction is 0-5 degrees, and the included angle between the tangent line of the lower section of the stacking line and the circumferential direction is 0-5 degrees.
3. The mixed-flow compressor blade-type structure for an air separation plant according to claim 2, characterized in that:
the thickness range of the front edge of the movable blade profile is 0.4-2.7 mm.
4. The mixed-flow compressor blade-type structure for an air separation plant according to any one of claims 1 to 3, characterized in that:
the number of stages is 6 stages.
5. The mixed-flow compressor blade-type structure for an air separation plant according to claim 4, characterized in that:
the first stage bucket geometry ranges are shown in the following table:
Figure FDA0003289672290000011
the first stage vane geometry ranges are shown in the following table:
Figure FDA0003289672290000021
the second stage bucket geometry ranges are shown in the following table:
Figure FDA0003289672290000022
the second stage vane geometry parameter ranges are shown in the following table:
Figure FDA0003289672290000023
the third stage bucket geometry ranges are shown in the following table:
Figure FDA0003289672290000024
Figure FDA0003289672290000031
the third stage vane geometry parameter ranges are shown in the following table:
Figure FDA0003289672290000032
the range of the geometric parameters of the fourth stage bucket is shown in the following table:
Figure FDA0003289672290000033
the fourth stage vane geometry parameter ranges are shown in the following table:
Figure FDA0003289672290000034
Figure FDA0003289672290000041
the range of the geometric parameters of the fifth stage bucket is shown in the following table:
Figure FDA0003289672290000042
the fifth stage vane geometry parameter ranges are shown in the following table:
Figure FDA0003289672290000043
the range of the geometric parameters of the sixth stage bucket is shown in the following table:
Figure FDA0003289672290000044
Figure FDA0003289672290000051
the sixth stage vane geometry parameter ranges are shown in the following table:
Figure FDA0003289672290000052
6. the mixed-flow compressor blade-type structure for an air separation plant according to claim 5, characterized in that:
the first stage bucket geometry is shown in the following table:
Figure FDA0003289672290000053
the first stage vane geometry is as follows:
Figure FDA0003289672290000054
the second stage bucket geometry is shown in the following table:
Figure FDA0003289672290000055
Figure FDA0003289672290000061
the second stage vane geometry parameters are shown in the following table:
Figure FDA0003289672290000062
the third stage bucket geometry is shown in the following table:
Figure FDA0003289672290000063
the third stage vane geometry is as follows:
Figure FDA0003289672290000064
the fourth stage bucket geometry is shown in the following table:
Figure FDA0003289672290000071
the fourth stage vane geometry is shown in the following table:
Figure FDA0003289672290000072
the fifth stage bucket geometry is shown in the following table:
Figure FDA0003289672290000073
the fifth stage vane geometry is shown in the following table:
Figure FDA0003289672290000074
the sixth stage bucket geometry is shown in the following table:
Figure FDA0003289672290000081
the sixth stage vane geometry is shown in the following table:
Figure FDA0003289672290000082
7. a mixed-flow compressor vane type structure for an air separation plant according to any one of claims 1 to 3, characterized in that:
the movable blades and the static blades are made of a stainless steel material X3CrNiMo 13-4.
CN202122393327.8U 2021-09-30 2021-09-30 Mixed-flow compressor blade structure for air separation device Active CN216430054U (en)

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