Mixed-flow compressor for hundred thousand-twenty thousand cubic meter grade air separation device
阅读说明：本技术 十万-二十万立方米等级空分装置用混流式压缩机 (Mixed-flow compressor for hundred thousand-twenty thousand cubic meter grade air separation device ) 是由 王雷 李宏安 陈余平 田满洲 陈江辉 朱安安 蔺满相 周根标 祁周会 江慧敏 申 于 2021-09-30 设计创作，主要内容包括：本发明涉及一种十万-二十万立方米等级空分装置用混流式压缩机,以解决现有的十万-二十万立方米等级空分装置用混流式压缩机轴流段使用现有工业轴流压缩机技术,导致切线速度较低,做功能力较差,存在级数多、结构复杂、效率偏低、生产成本较高的问题。该压缩机采用三层缸结构,包括机壳、调节缸和叶片承缸,其转子上设置有4-7级动叶,叶片承缸上设置有4-7级静叶；各级动叶轮毂处的圆周速度为190-244m/s；空分装置用混流式压缩机的等级为十万立方米至二十万立方米,动叶第一级叶片入口处外径相应为0.68726m至1.08712m,动叶末级叶片出口处外径相应为0.630054m至1.01134m；静叶第零级叶片入口处内径相应为0.366633m至0.588511m,静叶末级叶片出口处内径相应为0.4797m至0.777m。(The invention relates to a mixed-flow compressor for a hundred thousand-twenty-thousand cubic meter grade air separation device, which aims to solve the problems of lower tangential speed, poorer work-doing capability, more stages, complex structure, lower efficiency and higher production cost of the existing mixed-flow compressor for the hundred thousand-twenty-thousand cubic meter grade air separation device due to the fact that the existing industrial axial flow compressor technology is used in an axial flow section of the existing mixed-flow compressor. The compressor adopts a three-layer cylinder structure and comprises a shell, an adjusting cylinder and a blade bearing cylinder, wherein a rotor of the compressor is provided with 4-7 stages of movable blades, and a blade bearing cylinder is provided with 4-7 stages of static blades; the peripheral speed of each movable impeller hub is 190-244 m/s; the mixed-flow compressor for the air separation device is of a grade of ten-thousand cubic meter to twenty-thousand cubic meter, the outer diameter of the inlet of a first-stage blade of the movable blade is 0.68726m to 1.08712m correspondingly, and the outer diameter of the outlet of a last-stage blade of the movable blade is 0.630054m to 1.01134m correspondingly; the vane zeroth stage blade inlet inner diameter is 0.366633m to 0.588511m, and the vane last stage blade outlet inner diameter is 0.4797m to 0.777 m.)
1. The utility model provides a mixed flow compressor for air separation plant of hundred thousand-twenty thousand cubic meters class, adopts three-layer cylinder structure, three-layer cylinder includes casing (1), adjusting cylinder (2) and blade and holds jar (3), its characterized in that: a rotor (4) is provided with 4-7 stages of movable blades; 4-7 stages of static blades are arranged on the blade bearing cylinder (3);
the peripheral speed of each movable impeller hub is 190-244 m/s;
the mixed-flow compressor for the air separation device is of a grade of ten-thousand cubic meter to twenty-thousand cubic meter, the outer diameter of the inlet of a first-stage blade of the movable blade is 0.68726m to 1.08712m correspondingly, and the outer diameter of the outlet of a last-stage blade of the movable blade is 0.630054m to 1.01134m correspondingly; the vane zeroth stage blade inlet inner diameter is 0.366633m to 0.588511m, and the vane last stage blade outlet inner diameter is 0.4797m to 0.777 m.
2. The mixed flow compressor for a hundred thousand-twenty thousand cubic meter grade air separation plant of claim 1, wherein:
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.
3. The mixed flow compressor for a hundred thousand-twenty thousand cubic meter grade air separation plant of claim 2, wherein:
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.
4. The mixed flow compressor for a hundred thousand-twenty thousand cubic meter grade air separation plant of claim 3, wherein:
the thickness range of the front edge of the movable blade profile is 0.4-2.7 mm.
5. The mixed-flow compressor for a hundred thousand-twenty thousand cubic meter grade air separation plant according to any one of claims 1 to 4, characterized in that:
the rotor (4) is provided with 6 stages of movable blades, and the blade bearing cylinder (3) is provided with 6 stages of static blades.
6. The mixed flow compressor for a hundred thousand-twenty thousand cubic meter grade air separation plant of claim 5, wherein:
when the mixed-flow compressor for the air separation plant has a rating of ten-thousand cubic meters to twenty-ten-thousand cubic meters, the design rotation speed is 4376 rpm to 3708 rpm, respectively.
7. The mixed flow compressor for a hundred thousand-twenty thousand cubic meter grade air separation plant of claim 6, wherein:
the first stage bucket geometry ranges are shown in the following table:
the first stage vane geometry parameter ranges are shown in the following table:
the second stage bucket geometry ranges are shown in the following table:
the second stage vane geometry parameter ranges are shown in the following table:
the third stage bucket geometry ranges are shown in the following table:
the third stage vane geometry parameter ranges are shown in the following table:
the range of the geometric parameters of the fourth stage bucket is shown in the following table:
the fourth stage vane geometry parameter ranges are shown in the following table:
the range of the geometric parameters of the fifth stage bucket is shown in the following table:
the fifth stage vane geometry parameter ranges are shown in the following table:
the range of the geometric parameters of the sixth stage bucket is shown in the following table:
the sixth stage vane geometry parameter ranges are shown in the following table:
8. the mixed flow compressor for a hundred thousand-twenty thousand cubic meter grade air separation plant of claim 7, wherein:
the first stage bucket geometry is shown in the following table:
the first stage vane geometry is as follows:
the second stage bucket geometry is shown in the following table:
the second stage vane geometry parameters are shown in the following table:
the third stage bucket geometry is shown in the following table:
the third stage vane geometry is as follows:
the fourth stage bucket geometry is shown in the following table:
the fourth stage vane geometry is shown in the following table:
the fifth stage bucket geometry is shown in the following table:
the fifth stage vane geometry is shown in the following table:
the sixth stage bucket geometry is shown in the following table:
the sixth stage vane geometry is shown in the following table:
9. the mixed-flow compressor for a hundred thousand-twenty thousand cubic meter grade air separation plant according to any one of claims 1 to 4, characterized in that:
the movable blades and the static blades are made of a stainless steel material X3CrNiMo 13-4.
Technical Field
The invention relates to the field of turbomachinery, in particular to a mixed-flow compressor for a hundred thousand-twenty-thousand cubic meter grade air separation device.
Background
At present, mixed-flow compressors for hundred thousand-twenty-thousand cubic meter grade air separation devices in the market generally use the existing industrial axial flow compressor technology, the tangential speed is low, the working capacity is poor, and eight to ten grades of axial flows are generally needed to meet the process requirements. For example, the axial flow section of the existing ten-thousand space division mixed flow compressor adopts a ten-stage axial flow compressor scheme, and adopts a constant inner diameter flow channel and the existing NACA65 low speed blade profile technology, the circumferential speed at the inner diameter hub is in 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.
With the development of the design technology of turbomachinery with high performance and high tangential velocity, the advanced wide chord blade type obtained by customizing three-dimensional modeling technologies such as blade type, bending and sweeping is used in the mixed flow type compressor for the modern air separation device, and the high efficiency can be realized while the high pressure ratio is obtained. Therefore, the multi-stage axial flow compressor technology with high pressure ratio is used in specific product application, the performance requirement can be met under fewer stages, the structure of the existing compressor for the large air separation unit is greatly simplified, and the single set of unit adopted by the larger air separation unit is possible.
Disclosure of Invention
The invention aims to solve the problems that the mixed-flow compressor for the air separation device at the level of hundred thousand-twenty thousand cubic meters commonly uses the existing industrial axial flow compressor technology, has lower tangential speed and poorer work-doing capability, generally needs eight-to-ten-level axial flow to meet the process requirement, has multiple levels, complex structure, lower efficiency, higher production cost and the like, and provides the mixed-flow compressor for the air separation device at the level of hundred thousand-twenty thousand cubic meters.
In order to achieve the purpose, the technical scheme adopted by the invention is as follows:
a mixed-flow compressor for a hundred thousand-twenty thousand cubic meter grade air separation device adopts a three-layer cylinder structure, wherein the three-layer cylinder comprises a shell, an adjusting cylinder and a blade bearing cylinder, and is characterized in that: the rotor is provided with 4-7 stages of movable blades; 4-7 stages of static blades are arranged on the blade bearing cylinder;
the peripheral speed of each movable impeller hub is 190-244 m/s;
the mixed-flow compressor for the air separation device is of a grade of ten-thousand cubic meter to twenty-thousand cubic meter, the outer diameter of the inlet of a first-stage blade of the movable blade is 0.68726m to 1.08712m correspondingly, and the outer diameter of the outlet of a last-stage blade of the movable blade is 0.630054m to 1.01134m correspondingly; the vane zeroth stage blade inlet inner diameter is 0.366633m to 0.588511m, and the vane last stage blade outlet inner diameter is 0.4797m to 0.777 m.
Further, 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.
Furthermore, the rotor is provided with 6 stages of movable blades, and the blade bearing cylinder is provided with 6 stages of static blades.
Further, when the grade of the mixed flow compressor for the air separation device is changed from ten thousand cubic meters to twenty thousand cubic meters, the design rotating speed is gradually reduced from 4376 revolutions per minute to 3708 revolutions per minute.
Further, the first stage bucket geometry ranges are shown in the following table:
the first stage vane geometry parameter ranges are shown in the following table:
the second stage bucket geometry ranges are shown in the following table:
the second stage vane geometry parameter ranges are shown in the following table:
the third stage bucket geometry ranges are shown in the following table:
the third stage vane geometry parameter ranges are shown in the following table:
the range of the geometric parameters of the fourth stage bucket is shown in the following table:
the fourth stage vane geometry parameter ranges are shown in the following table:
the range of the geometric parameters of the fifth stage bucket is shown in the following table:
the fifth stage vane geometry parameter ranges are shown in the following table:
the range of the geometric parameters of the sixth stage bucket is shown in the following table:
the sixth stage vane geometry parameter ranges are shown in the following table:
further, the first stage bucket geometry is as shown in the following table:
the first stage vane geometry is as follows:
the second stage bucket geometry is shown in the following table:
the second stage vane geometry parameters are shown in the following table:
the third stage bucket geometry is shown in the following table:
the third stage vane geometry is as follows:
the fourth stage bucket geometry is shown in the following table:
the fourth stage vane geometry is shown in the following table:
the fifth stage bucket geometry is shown in the following table:
the fifth stage vane geometry is shown in the following table:
the sixth stage bucket geometry is shown in the following table:
the sixth stage vane geometry is shown in the following table:
furthermore, the movable blades and the static blades are made of a stainless steel material X3CrNiMo 13-4.
Typically, gas turbine compressors have a high pressure ratio and a small number of stages, resulting in a shorter compressor. However, the high single stage pressure ratio gas turbine compressor technology cannot be used directly in industrial applications because: 1. the front 2 stages of the gas turbine compressor are designed in a transonic mode, so that the operation range is narrow; 2. the design only considers the operation near the gas turbine common working line, when the blockage and the surging are approached, the flutter and high forced response phenomena can occur and the efficiency can be obviously reduced; 3. because the cavity of the combustion chamber of the gas turbine is smaller, the blade designed aiming at the small surge cavity is thinner and thinner, and the capability of resisting surge is poorer.
In contrast, the present invention combines the advantages of a wide operating range of an industrial compressor with a high power density and high stage pressure ratio of a gas turbine compressor, referred to as hybrid concept vanes, for the design of runners and vanes in pursuit of an optimal combination of gas turbine compressor technology and conventional industrial compressor technology. Industrial compressors have high requirements on operating range and non-design point efficiency, and the aerodynamic loads cannot be generally too high, so that the aerodynamic loads of the new blade design are almost unchanged compared with the traditional industrial compressor. Unlike conventional methods for increasing head coefficient to increase stage pressure ratio, a higher stage pressure ratio is achieved by increasing the peripheral speed by about 30% under nearly constant aerodynamic loading, resulting in a more compact, shorter axial length compressor, while reducing the vane flow coefficient to compensate for the increased mach number at higher speeds.
Compared with the prior art, the invention has the beneficial effects that:
(1) compared with the existing axial flow compressor for the large-scale air separation unit, the mixed flow compressor for the hundred thousand-twenty-thousand cubic meter grade air separation unit provided by the invention has the advantages that the number of stages is reduced by about 35-45%, the single-stage pressure ratio is averagely improved by 9%, the circumferential speed is improved by 30%, the rotor dynamics stability is improved, and the possibility of obtaining a higher overall pressure ratio is increased; the axial length of the axial flow section of the compressor is reduced by 25%, the width is reduced by 16%, the height is reduced by 7%, the total weight of the compressor is reduced by 24%, the weight of a maximum overhaul member is reduced by 35%, and the weight of a rotor is reduced by 33%, so that the axial flow section of the compressor has the characteristics of few stages, compact structure, light weight and low manufacturing cost.
(2) The mixed-flow compressor is based on an independently developed high-grade pressure ratio axial flow compressor pneumatic design and analysis system, a novel blade with high-grade pressure ratio, high efficiency and high reliability is designed, the pressure ratio level of ten grades of the traditional axial flow compressor can be realized only by adopting four to seven grades (preferably six grades), and the operation cost and the manufacturing cost of an air separation device are greatly reduced.
Drawings
FIG. 1 is a schematic diagram of a mixed flow compressor for a hundred thousand-twenty thousand cubic meter grade air separation plant of the present invention;
FIG. 2 is a schematic view of the flow channel and vane profile of the present invention;
FIG. 3 is a schematic diagram of a blade profile configuration of the present invention in comparison to a prior art blade profile configuration;
FIG. 4 is a schematic comparison of the leading edge of the airfoil of the present invention with the leading edge of the prior art airfoil, wherein a is a schematic prior art-circular leading edge, b is a schematic prior art-elliptical leading edge, and c is a schematic prior art-curvature continuous leading edge;
FIG. 5 is a pressure coefficient distribution plot for a prior art airfoil leading edge and airfoil leading edge of the present invention, wherein the dashed line represents a rounded leading edge, the solid line represents an elliptical leading edge, and the dashed-two dotted line represents a curvature-continuous leading edge;
FIG. 6 is a graph of the profile surface Mach number distribution for the airfoil of the present invention and for the prior art airfoil;
FIG. 7 is a profile of the airfoil loss versus inlet flow angle for the present invention and prior art airfoils;
FIG. 8 is a schematic outer view of a stator blade according to the present invention;
FIG. 9 is a third order Bessel product overlay of a vane blade of the present invention;
FIG. 10 is a relative Mach number cloud plot for 10% span for an embodiment of the present invention;
FIG. 11 is a relative Mach number cloud for a 50% span of a blade according to an embodiment of the present invention;
FIG. 12 is a relative Mach number cloud for 90% span for an embodiment of the present invention.
In the figure, 1-machine shell, 2-adjusting cylinder, 3-blade bearing cylinder, 4-rotor, 5-inner runner diameter, 6-outer runner diameter, 7-movable blade and 8-static blade.
Detailed Description
To further clarify the objects, advantages and features of the present invention, a mixed flow compressor for air separation plants of the hundred thousand to twenty thousand cubic meters class proposed by the present invention will be described in further detail with reference to the accompanying drawings and specific examples.
The mixed-flow compressor for an air separation unit of the hundred thousand-twenty-thousand cubic meter class provided by the embodiment comprises a casing 1, a three-layer cylinder structure of a regulating cylinder 2 and a blade bearing cylinder 3, and a rotor 4, as shown in fig. 1. The rotor 4 and the vane bearing cylinder 3 form the inner and outer diameters of the compressor flow passage. The rotor 4 is provided with 6 stages of movable blades, and the blade bearing cylinder 3 is provided with 6 stages of static blades.
The grade of the mixed-flow compressor for the air separation device is between ten and twenty thousand cubic meters, the outer diameter of the inlet of a first-stage blade of the movable blade is between 0.68726 and 1.08712m, and the outer diameter of the outlet of a last-stage blade of the movable blade is between 0.630054 and 1.01134 m; the vane zeroth stage blade inlet inner diameter is 0.366633m to 0.588511m, and the vane last stage blade outlet inner diameter is 0.4797m to 0.777 m. Therefore, the inner diameter variation trend of the mixed flow compressor for the ten-thousand cubic meter grade air separation device is 0.366633m to 0.5863m, and the outer diameter variation trend is 0.84055m to 0.62244 m; the inner diameter variation trend of the flow-mixing type compressor flow-through part for the air separation plant of twenty-ten thousand cubic meters grade is 0.48151m to 0.77m, and the outer diameter variation trend is 1.10393m to 0.81747 m.
The flow channel of the mixed-flow compressor for the fifteen-ten thousand and twenty-ten thousand cubic meter grade air separation device is generated by similar amplification of the flow channel of the mixed-flow compressor for the fifteen-ten thousand cubic meter grade air separation device.
Specifically, the radial dimensions of the flow channels of the mixed-flow compressor for a ten-thousand cubic meter class air separation plant are shown in the following table (unit: m):
the radial dimensions of the flow channels of a mixed-flow compressor for a fifteen-ten-thousand-cubic meter-class air separation plant are shown in the following table (unit: m):
the radial dimensions of the flow channels of a mixed-flow compressor for a twenty-million cubic meter grade air separation plant are shown in the following table (unit: m):
the flow channel and blade profile of the mixed flow compressor 6 stage axial flow section is shown in fig. 2, wherein the inner diameter 5 of the flow channel is gradually increased from the inlet to the outlet, the outer diameter 6 of the flow channel is gradually decreased from the inlet to the outlet, a black line between the inner diameter 5 of the flow channel and the outer diameter 6 of the flow channel is the profile of the movable blade 7, and a gray line is the profile of the static blade 8. The mixed-flow compressor has the following characteristics: the six-stage pressure ratio is 1.31, 1.29, 1.265, 1.23, 1.195 and 1.19 respectively, the six-stage average pressure ratio is 1.24, the total pressure ratio is 3.75, and the peak value polytropic efficiency from flange to flange is 92%. The design rotating speed is gradually reduced from 4376 rpm of one hundred thousand air separation to 3708 rpm of twenty thousand air separation according to the size of the air separation device, and the surge pressure margin of the design point is more than 20%. The tangential speed of the hub is in the range of 190-244 m/s.
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 type is a front transition blade type with transition position in the range of 8% -12% of axial chord length, the front edge is a curvature continuous front edge, the chord length range is 40-189mm, and the aspect ratio range 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:
the first stage vane geometry parameter ranges are shown in the following table:
the second stage bucket geometry ranges are shown in the following table:
the second stage vane geometry parameter ranges are shown in the following table:
the third stage bucket geometry ranges are shown in the following table:
the third stage vane geometry parameter ranges are shown in the following table:
the range of the geometric parameters of the fourth stage bucket is shown in the following table:
the fourth stage vane geometry parameter ranges are shown in the following table:
the range of the geometric parameters of the fifth stage bucket is shown in the following table:
the fifth stage vane geometry parameter ranges are shown in the following table:
the range of the geometric parameters of the sixth stage bucket is shown in the following table:
the sixth stage vane geometry parameter ranges are shown in the following table:
preferably, the first stage bucket geometry is as shown in the following table:
the first stage vane geometry is as follows:
the second stage bucket geometry is shown in the following table:
the second stage vane geometry parameters are shown in the following table:
the third stage bucket geometry is shown in the following table:
the third stage vane geometry is as follows:
the fourth stage bucket geometry is shown in the following table:
the fourth stage vane geometry is shown in the following table:
the fifth stage bucket geometry is shown in the following table:
the fifth stage vane geometry is shown in the following table:
the sixth stage bucket geometry is shown in the following table:
the sixth stage vane geometry is shown in the following table:
as shown in FIG. 3, the blade profile structure of the invention adopts a wide chord length, the two-dimensional blade profile sections of each stage of the movable blade and the static blade are designed according to local flow characteristics in a customized mode, and each section parameter of the movable blade profile and the static blade profile is changed along with the height of the blade profile. As shown in fig. 4 and 5, the arc leading edge blade profile and the elliptical leading edge blade profile adopted by the existing industrial 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. 5, the dotted line is an arc front edge, the solid line is an ellipse front edge, the two-dot chain line is a curvature continuous front edge, the pressure coefficient sharp point of the arc front edge is the largest, the loss is the highest, the ellipse arc is the second, the pressure sharp point and the loss of the curvature continuous front edge are the smallest, it can be seen that the adoption of the curvature continuous front edge can weaken the front edge suction surface mach number sharp point, avoid the air flow from separating in a large range on the blade type suction surface under the high subsonic mach number environment, and have a wider range of attack angle of incoming flow, thereby reducing the flow loss and increasing the working range under the high pressure boost ratio and the work capacity, and breaking through the upper limit of the efficiency of the existing industrial axial flow compressor.
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. 6 and 7, 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. 6, β 1 is the flow angle and Ma1 is the inlet Mach number.
The profile of the stator blade is shown in fig. 8, the third-order bessel stacking line is shown in fig. 9, 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.
Fig. 10, 11, 12 are relative mach number cloud charts of 10%, 50% and 90% blade span of the mixed-flow compressor 6 stage axial flow section for the 10-ten-thousand-cubic meter grade air separation device respectively, and it can be seen that the structure of the discharge field of each stage of the 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.