CN113719474A - 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
CN113719474A
CN113719474A CN202111162131.6A CN202111162131A CN113719474A CN 113719474 A CN113719474 A CN 113719474A CN 202111162131 A CN202111162131 A CN 202111162131A CN 113719474 A CN113719474 A CN 113719474A
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China
Prior art keywords
blade
following table
stage
geometry
range
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Pending
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CN202111162131.6A
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Chinese (zh)
Inventor
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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Priority to CN202111162131.6A priority Critical patent/CN113719474A/en
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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
    • F04D29/26—Rotors specially for elastic fluids
    • F04D29/32—Rotors specially for elastic fluids for axial flow pumps
    • F04D29/38—Blades
    • F04D29/384—Blades characterised by form
    • F04D29/386—Skewed blades
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/666—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by means of rotor construction or layout, e.g. unequal distribution of blades or vanes
    • 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
    • F04D29/66—Combating cavitation, whirls, noise, vibration or the like; Balancing
    • F04D29/661—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps
    • F04D29/667—Combating cavitation, whirls, noise, vibration or the like; Balancing especially adapted for elastic fluid pumps by influencing the flow pattern, e.g. suppression of turbulence

Abstract

The invention relates to the field of turbomachinery, in particular to a mixed-flow compressor blade profile structure for an air separation device, and aims to solve the problems that the existing mixed-flow compressor for the air separation device with the grade of 10-20 ten thousand cubic meters has the defects of discontinuous curvature due to the adoption of an arc leading edge blade profile and an oval leading edge blade profile, so that the leading edge has larger pressure sharp points, the aerodynamic loss is increased, the tangential velocity is lower, the work capability is poorer, and the process requirements can be met only by eight-level to ten-level axial flows. 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 invention relates to the field of turbomachinery, in particular to a mixed-flow compressor blade profile structure for an air separation device.
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.
Disclosure of Invention
The invention aims to solve the problems that the prior mixed-flow compressor for the air separation device of 10-20 ten thousand cubic meters grade adopts an arc leading edge blade profile and an oval leading edge blade profile which have the defects of discontinuous curvature, so that the leading edge has larger pressure sharp, the pneumatic loss is increased, the tangential speed is lower, the working capacity is poorer, and the process requirements can be met by generally adopting eight-to ten-grade axial flow, and provides a mixed-flow compressor blade profile structure for the air separation device.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
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 BDA0003290625380000021
the first stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003290625380000022
the second stage bucket geometry ranges are shown in the following table:
Figure BDA0003290625380000023
Figure BDA0003290625380000031
the second stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003290625380000032
the third stage bucket geometry ranges are shown in the following table:
Figure BDA0003290625380000033
the third stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003290625380000034
the range of the geometric parameters of the fourth stage bucket is shown in the following table:
Figure BDA0003290625380000035
Figure BDA0003290625380000041
the fourth stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003290625380000042
the range of the geometric parameters of the fifth stage bucket is shown in the following table:
Figure BDA0003290625380000043
the fifth stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003290625380000044
Figure BDA0003290625380000051
the range of the geometric parameters of the sixth stage bucket is shown in the following table:
Figure BDA0003290625380000052
the sixth stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003290625380000053
further, the first stage bucket geometry is as shown in the following table:
Figure BDA0003290625380000054
Figure BDA0003290625380000061
the first stage vane geometry is as follows:
Figure BDA0003290625380000062
the second stage bucket geometry is shown in the following table:
Figure BDA0003290625380000063
the second stage vane geometry parameters are shown in the following table:
Figure BDA0003290625380000064
the third stage bucket geometry is shown in the following table:
Figure BDA0003290625380000065
Figure BDA0003290625380000071
the third stage vane geometry is as follows:
Figure BDA0003290625380000072
the fourth stage bucket geometry is shown in the following table:
Figure BDA0003290625380000073
the fourth stage vane geometry is shown in the following table:
Figure BDA0003290625380000074
the fifth stage bucket geometry is shown in the following table:
Figure BDA0003290625380000075
Figure BDA0003290625380000081
the fifth stage vane geometry is shown in the following table:
Figure BDA0003290625380000082
the sixth stage bucket geometry is shown in the following table:
Figure BDA0003290625380000083
the sixth stage vane geometry is shown in the following table:
Figure BDA0003290625380000084
furthermore, the movable blades and the static blades are made of a stainless steel material X3CrNiMo 13-4.
Compared with the prior art, the invention has the beneficial effects that:
the mixed-flow type compressor blade structure for the air separation device is based on an autonomously developed high-pressure-ratio axial flow compressor pneumatic design and analysis system, is provided with a novel blade with high-pressure ratio, high efficiency and high reliability, can realize the ten-stage pressure ratio level of the traditional axial flow compressor by only adopting four-stage to seven-stage (preferably six-stage), is high in tangential velocity and strong in working capacity, can effectively improve the operation cost of the air separation device, and reduces the manufacturing cost.
The mixed flow compressor adopting the vane-type structure has the peripheral speed of 190-244m/s at the inner diameter hub, the flow coefficient of 0.5-0.55, the load coefficient of 0.35 and the single-stage pressure ratio of 1.2.
Drawings
FIG. 1 is a schematic diagram of a comparison of the inventive airfoil configuration with a prior art airfoil configuration;
FIG. 2 is a schematic comparison of a prior art airfoil leading edge with a prior art airfoil leading edge, wherein a is a prior art-circular leading edge schematic, b is a prior art-elliptical leading edge schematic, and c is a present invention-curvature continuous leading edge schematic;
FIG. 3 is a pressure coefficient distribution plot for a prior art airfoil leading edge and a airfoil leading edge of the present invention, wherein the dashed line represents a circular leading edge, the solid line represents an elliptical leading edge, and the dashed-two dotted line represents a curvature-continuous leading edge;
FIG. 4 is a graph of the surface Mach number distribution of the airfoil of the present invention and existing airfoils;
FIG. 5 is a loss-inlet flow angle distribution plot for the airfoil of the present invention and for the prior art airfoil;
FIG. 6 is a schematic outer view of a stator blade according to the present invention;
FIG. 7 is a third order Bessel product overlay of a vane blade of the present invention;
FIG. 8 is a schematic view of the flow channels and blade profiles of a mixed flow compressor stage 6 axial flow section for a 10-20 million cubic meter class air separation plant using the inventive lobed configuration;
FIG. 9 is a relative Mach number cloud plot of 10% span of axial flow section of mixed flow compressor stage 6 for a 10-20 million cubic meter class air separation plant using the lobed configuration of the present invention;
FIG. 10 is a relative Mach number cloud plot of 50% span of the axial flow section of a mixed flow compressor stage 6 for a 10-20 million cubic meter class air separation plant using the lobed configuration of the present invention;
FIG. 11 is a relative Mach number cloud plot of 90% span of the axial flow section of mixed flow compressor stage 6 for a 10-20 million cubic meter class air separation plant using the lobed configuration of the present invention.
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 BDA0003290625380000101
the first stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003290625380000102
the second stage bucket geometry ranges are shown in the following table:
Figure BDA0003290625380000103
Figure BDA0003290625380000111
the second stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003290625380000112
the third stage bucket geometry ranges are shown in the following table:
Figure BDA0003290625380000113
the third stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003290625380000114
Figure BDA0003290625380000121
the range of the geometric parameters of the fourth stage bucket is shown in the following table:
Figure BDA0003290625380000122
the fourth stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003290625380000123
the range of the geometric parameters of the fifth stage bucket is shown in the following table:
Figure BDA0003290625380000124
Figure BDA0003290625380000131
the fifth stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003290625380000132
the range of the geometric parameters of the sixth stage bucket is shown in the following table:
Figure BDA0003290625380000133
the sixth stage vane geometry parameter ranges are shown in the following table:
Figure BDA0003290625380000134
preferably, the first stage bucket geometry is as shown in the following table:
Figure BDA0003290625380000141
the first stage vane geometry is as follows:
Figure BDA0003290625380000142
the second stage bucket geometry is shown in the following table:
Figure BDA0003290625380000143
the second stage vane geometry parameters are shown in the following table:
Figure BDA0003290625380000144
the third stage bucket geometry is shown in the following table:
Figure BDA0003290625380000151
the third stage vane geometry is as follows:
Figure BDA0003290625380000152
the fourth stage bucket geometry is shown in the following table:
Figure BDA0003290625380000153
the fourth stage vane geometry is shown in the following table:
Figure BDA0003290625380000154
Figure BDA0003290625380000161
the fifth stage bucket geometry is shown in the following table:
Figure BDA0003290625380000162
the fifth stage vane geometry is shown in the following table:
Figure BDA0003290625380000163
the sixth stage bucket geometry is shown in the following table:
Figure BDA0003290625380000164
the sixth stage vane geometry is shown in the following table:
Figure BDA0003290625380000165
Figure BDA0003290625380000171
as shown in FIG. 1, the blade profile structure of the invention adopts a forward transition blade profile with a wide chord length and a continuous front edge with curvature, the two-dimensional blade profile sections of each stage of the movable blade and the stationary blade are custom-designed according to local flow characteristics, and each section parameter of the movable blade profile and the stationary blade profile is changed along with the blade profile height. As shown in fig. 2 and 3, the arc leading edge blade profile and the elliptical leading edge blade profile adopted by the existing industrial axial flow compressor both have the defect of discontinuous curvature, so that the leading edge has a larger pressure sharp and the aerodynamic loss is increased. 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, in order to adapt to a large-scale space division high-reynolds number flow environment, the peak value position of the mach number is closer to the front edge of the blade and coincides with the transition point position, the low-loss attack angle range of the blade is enlarged, and the loss coefficient is also reduced. In FIG. 4, β 1 is the flow angle and Ma1 is the inlet Mach number.
The profile of the stator blade is shown in fig. 6, the third-order bessel stacking line is shown in fig. 7, the included angle between the tangent of the upper-stage stacking line and the radial direction is B2, the included angle between the tangent of the lower-stage stacking line and the circumferential direction is B1, the dividing point between the upper stage of the blade and the middle straight-line section is P1, and the dividing point between the lower stage of the blade and the middle straight-line section is P2.
The flow channel and blade profile 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 profile structure of the invention are shown in figure 8, wherein the black line is the profile of a moving impeller, and the gray line is the profile of a static impeller.
Fig. 9, 10 and 11 are relative mach number clouds of 10%, 50% and 90% blade span 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 type structure of the invention, respectively, and it can be seen that the structure of the discharge field of each stage of blade is good, and the boundary layer separation area causing high loss is not generated.
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 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.
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 FDA0003290625370000011
the first stage vane geometry parameter ranges are shown in the following table:
Figure FDA0003290625370000021
the second stage bucket geometry ranges are shown in the following table:
Figure FDA0003290625370000022
the second stage vane geometry parameter ranges are shown in the following table:
Figure FDA0003290625370000023
the third stage bucket geometry ranges are shown in the following table:
Figure FDA0003290625370000024
Figure FDA0003290625370000031
the third stage vane geometry parameter ranges are shown in the following table:
Figure FDA0003290625370000032
the range of the geometric parameters of the fourth stage bucket is shown in the following table:
Figure FDA0003290625370000033
the fourth stage vane geometry parameter ranges are shown in the following table:
Figure FDA0003290625370000034
Figure FDA0003290625370000041
the range of the geometric parameters of the fifth stage bucket is shown in the following table:
Figure FDA0003290625370000042
the fifth stage vane geometry parameter ranges are shown in the following table:
Figure FDA0003290625370000043
the range of the geometric parameters of the sixth stage bucket is shown in the following table:
Figure FDA0003290625370000044
Figure FDA0003290625370000051
the sixth stage vane geometry parameter ranges are shown in the following table:
Figure FDA0003290625370000052
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 FDA0003290625370000053
the first stage vane geometry is as follows:
Figure FDA0003290625370000054
the second stage bucket geometry is shown in the following table:
Figure FDA0003290625370000055
Figure FDA0003290625370000061
the second stage vane geometry parameters are shown in the following table:
Figure FDA0003290625370000062
the third stage bucket geometry is shown in the following table:
Figure FDA0003290625370000063
the third stage vane geometry is as follows:
Figure FDA0003290625370000064
the fourth stage bucket geometry is shown in the following table:
Figure FDA0003290625370000071
the fourth stage vane geometry is shown in the following table:
Figure FDA0003290625370000072
the fifth stage bucket geometry is shown in the following table:
Figure FDA0003290625370000073
the fifth stage vane geometry is shown in the following table:
Figure FDA0003290625370000074
the sixth stage bucket geometry is shown in the following table:
Figure FDA0003290625370000081
the sixth stage vane geometry is shown in the following table:
Figure FDA0003290625370000082
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.
CN202111162131.6A 2021-09-30 2021-09-30 Mixed-flow compressor blade structure for air separation device Pending CN113719474A (en)

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Application Number Priority Date Filing Date Title
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