Last-stage moving blade for compressed carbon dioxide energy storage turbine

Abstract

The invention discloses a last-stage moving blade for a compressed carbon dioxide energy storage turbine. A blade body structure of the last-stage moving blade is formed by stacking and twisting a plurality of characteristic sections according to a rule; the overlapping rule of each characteristic section is continuous and smooth transition from the root end to the top end along the height direction of the blade body; the relative value of the height H of the blade body is monotonically increased to 1.0 from 0.0; the relative value of the relative blade height h / H is linearly increased to 1.0 from 0.0; the absolute value of the mounting angle C is monotonically decreased from 52.89 degrees to 13.33 degrees; the characteristic parameter of each characteristic section takes the root section as a reference; the relative value of the pitch T is linearly increased from 1.0 to 1.6 from the root section to the top section; the relative value of the axial width Xa is linearly reduced from 1.0 to 0.87 from the root section to the top section; the relative value of the chord length B is linearly increased from 1.0 to 1.36 from the root section to the top section; the relative value W of the maximum thickness is linearly reduced from 1.0 to 0.36 from the root section to the top section.

Description

Technical Field

[0001] The invention belongs to the technical field of high-power compressed gas energy storage turbines, and in particular relates to a last-stage moving blade for a compressed carbon dioxide energy storage turbine. Background Art

[0002] The new energy power system has the characteristics of clean and low carbon, flexible and efficient, safe and controllable. However, the grid connection of new energy power generation has problems such as intermittent and volatile, which aggravates the peak-shaving task of the power grid.

[0003] Energy storage technology is the link between new energy and the power grid, and is the supporting technology for large-scale grid connection of new energy. Compressed carbon dioxide energy storage is a rapidly developing new energy storage technology due to its advantages such as high safety, zero pollution, large scale, long working time, and flexible site selection. The compressed carbon dioxide energy storage system uses a multi-stage turbine expander in the energy release stage. As one of the key components of the energy storage system, its performance directly affects the efficiency of the energy storage system.

[0004] As the scale of power generation becomes larger and larger, the development of the last stage blades of energy storage turbines for deep peak regulation of large power units is very necessary. The long blades of the last stage of large power turbines have the characteristics of high load and large diameter-to-height ratio, and the energy storage units may operate at low load and change load rapidly. Therefore, it is necessary to develop the last stage moving blades for compressed carbon dioxide energy storage turbines that are suitable for high load, large flow coefficient and excellent load change performance, so as to improve the flexibility, economy and safety of traditional power systems. Summary of the invention

[0005] The purpose of the present invention is to provide a last stage moving blade for compressing carbon dioxide energy storage turbine with high stage load, large flow coefficient and excellent variable load performance in view of the shortcomings of the prior art.

[0006] The technical purpose of the present invention is achieved by the following technical solutions:

[0007] A final stage moving blade for a compressed carbon dioxide energy storage turbine, wherein the blade body structure of the final stage moving blade is formed by stacking and twisting a plurality of characteristic cross sections in a regular manner; the characteristic parameters of the moving blade include: a blade body height H;

[0008] The contour line of each characteristic section is a closed curve composed of a leading edge, a pressure surface, a trailing edge, and a suction surface; the characteristic parameters of the characteristic section include: installation angle C, pitch T, axial width Xa, chord length B, maximum thickness W, section height h, relative blade height h / H; the superposition rule of each characteristic section is a continuous and smooth transition from the root end to the tip end along the blade height direction;

[0009] The relative value of the blade height H increases monotonically from 0.0 to 1.0;

[0010] The relative value of the relative leaf height h / H increases linearly from 0.0 to 1.0;

[0011] The absolute value of the installation angle C decreases monotonically from 52.89° to 13.33°;

[0012] The characteristic parameters of each characteristic section are based on the root section;

[0013] The relative value of the pitch T increases linearly from 1.0 to 1.6 from the root section to the top section;

[0014] The relative value of the axial width Xa decreases linearly from 1.0 to 0.87 from the root section to the top section;

[0015] The relative value of the chord length B increases linearly from 1.0 to 1.36 from the root section to the top section;

[0016] The relative value W of the maximum thickness decreases linearly from 1.0 to 0.36 from the root section to the top section.

[0017] Furthermore, the blade structure is formed by five characteristic cross-sections with different contour shapes that transition continuously and smoothly from the root end to the tip end along the height direction of the blade.

[0018] Furthermore, the characteristic cross-section includes three key cross-sections, including the AA cross-section located at 0.0% of the blade height H, the CC cross-section located at 50% of the blade height H, and the EE cross-section located at 100% of the blade height H; the theoretical contour line of each cross-section is described by the coordinates (X, Y) of a number of discrete points, and the discrete points are smoothly connected to obtain the theoretical contour line of the corresponding key cross-section.

[0019] Furthermore, the theoretical contour lines of each of the key cross sections are described by coordinates (X, Y) of 24 discrete points.

[0020] Furthermore, the theoretical contour line of the AA section is described by the coordinates (X, Y) of the following discrete points:

[0021]

[0022]

[0023] Furthermore, the theoretical contour line of the CC section is described by the coordinates (X, Y) of the following discrete points:

[0024] No. 1 2 3 4 5 6 7 8 X -68.7 -69.6 -63.7 -54.4 -44.7 -34.3 -23.1 -10.4 Y -99.8 -99.8 -86.8 -67.8 -48.9 -30.1 -11.6 6.4 No. 9 10 11 12 13 14 15 16 X 5.0 25 50.3 59.4 60.9 60.7 55.0 33.6 Y 23.2 37.1 44.2 43.2 42.0 40.2 34.9 22.3 No. 17 18 19 20 21 22 23 24 X 16.4 -0.9 -14.2 -25.7 -37.4 -49.7 -61.6 -67.6 Y 9.5 -4.7 -18.5 -33.1 -50.0 -69.1 -88.3 -97.9 .

[0025] Furthermore, the theoretical contour line of the EE section is described by the coordinates (X, Y) of the following discrete points:

[0026] No. 1 2 3 4 5 6 7 8 X -71.7 -72.4 -64.8 -53.4 -41.9 -30.4 -18.6 -6.0 Y -113.2 -113.0 -98.3 -76.7 -55.0 -33.4 -12.0 9.0 No. 9 10 11 12 13 14 15 16 X -8.2 24.7 45.0 55.1 57.3 57.0 51.0 34.0 Y 28.9 46.9 60.0 60.9 59.3 57.1 51.0 34.0 No. 17 18 19 20 21 22 23 24 X 18.4 3.7 -10.2 -25.7 -23.7 -50.0 -63.1 -70.3 Y 16.4 -2.2 -21.4 -33.1 -40.8 -80.2 -100.0 -111.0 .

[0027] Furthermore, the contour line of each characteristic section may have a tolerance zone, and the range of the tolerance zone is within the contour shape range formed by a circle with a discrete point of the theoretical contour line of each characteristic section as the center and a radius of 0.2mm to 0.7mm as the envelope.

[0028] Furthermore, the blade height H is 373 mm; the root diameter Dr is 1185 mm.

[0029] Compared with the prior art, the present invention has the following beneficial effects:

[0030] 1. The present invention is a 373mm last stage moving blade for compressing carbon dioxide energy storage turbine, which is compatible with carbon dioxide energy storage turbines of 100MW and above power levels. The present invention is suitable for high load levels and has the advantages of large flow coefficient and excellent variable load performance. The present invention can provide excellent last stage moving blades for existing large-capacity carbon dioxide turbine units, effectively improve unit efficiency and variable operating performance, meet the needs of market economy and power grid peak regulation, and effectively increase market competitiveness.

[0031] 2. The blade of the present invention has excellent aerodynamic performance, excellent subsonic flow characteristics at the root, transonic flow characteristics in the middle, and supersonic flow characteristics at the top, weak shock waves and simple wave system structure, controllable vortex system, continuous and smooth twist stacking of each section along the blade height, large strength margin, and high reliability.

[0032] 3. The present invention optimizes the parameters of the contour lines of each characteristic cross section, so that the last-stage moving blade of the present invention has better adaptability to the angle of attack and excellent variable operating condition performance. BRIEF DESCRIPTION OF THE DRAWINGS

[0033] Figure 1 It is a schematic diagram of the structure of the present invention;

[0034] Figure 2 yes Figure 1 Top view of the blade structure;

[0035] Figure 3 It is a schematic diagram of the superposition of all characteristic sections;

[0036] Figure 4 It is a schematic diagram of characteristic cross-section in the blade structure;

[0037] Reference numerals: 1—blade root; 2—blade body; 3—shroud;

[0038] H—blade height; B—chord length; C—installation angle; W—maximum thickness; Xa—axial width; T—pitch. DETAILED DESCRIPTION

[0039] In order to make the purpose, technical solutions and advantages of the embodiments of the present invention clearer, the technical solutions in the embodiments of the present invention will be clearly and completely described below in conjunction with the drawings in the embodiments of the present invention. Obviously, the described embodiments are part of the embodiments of the present invention, not all of the embodiments. Generally, the components of the embodiments of the present invention described and shown in the drawings here can be arranged and designed in various different configurations.

[0040] Therefore, the following detailed description of the embodiments of the present invention provided in the accompanying drawings is not intended to limit the scope of the invention claimed for protection, but merely represents selected embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by ordinary technicians in this field without creative work are within the scope of protection of the present invention.

[0041] It should be noted that similar reference numerals and letters represent similar items in the following drawings, so once an item is defined in one drawing, it does not need to be further defined and explained in the subsequent drawings. In addition, the terms "first", "second", etc. are only used to distinguish the description and cannot be understood as indicating or implying relative importance.

[0042] like Figure 1 — Figure 4As shown, a last-stage moving blade for compressing a carbon dioxide energy storage turbine, the last-stage moving blade includes a blade root 1, a blade body 2 and a shroud 3, the blade body 2 structure of the last-stage moving blade is formed by stacking and twisting multiple characteristic sections according to a rule; the characteristic parameters of the moving blade include: blade body height H; the contour line of each characteristic section is a closed curve composed of a leading edge, a pressure surface, a trailing edge, and a suction surface; the characteristic parameters of the characteristic section include: installation angle C, pitch T, axial width Xa, chord length B, maximum thickness W, section height h, relative blade height h / H; the superposition rule of each characteristic section is a continuous and smooth transition from the root end to the top end along the height direction of the blade body 2; the blade height The relative value of the degree H increases monotonically from 0.0 to 1.0; the relative value of the relative blade height h / H increases linearly from 0.0 to 1.0; the absolute value of the installation angle C decreases monotonically from 52.89° to 13.33°; the characteristic parameters of each characteristic section are based on the root section; the relative value of the pitch T increases linearly from 1.0 to 1.6 from the root section to the top section; the relative value of the axial width Xa decreases linearly from 1.0 to 0.87 from the root section to the top section; the relative value of the chord length B increases linearly from 1.0 to 1.36 from the root section to the top section; the relative value of the maximum thickness W decreases linearly from 1.0 to 0.36 from the root section to the top section. The last stage moving blade is suitable for high stage loads and has the advantages of large flow coefficient and excellent variable load performance. The last stage moving blade provides an excellent last stage moving blade for the existing large-capacity carbon dioxide turbine unit, which can effectively improve the unit efficiency and improve the variable operating performance. It can meet the needs of market economy and grid peak regulation, and effectively increase market competitiveness.

[0043] Specifically, Figure 1 As shown, the last stage moving blade includes a blade root 1, a blade body 2 and a shroud 3. Among them, the last stage moving blade is a 373mm last stage moving blade, which is compatible with the boundary conditions of the carbon dioxide turbine engineering of 100MW level and above. The characteristic parameters of the blade structure are determined as follows: the blade body height H is 373mm, that is, the distance between the root section of the blade body 2 and the top section of the blade body 2 is 373mm; the subsonic, transonic and supersonic flow characteristics are excellent. Match the first few stages of the low-pressure module to determine the basic characteristic parameters of the blade body 2 structure. In actual use, the root diameter Dr (not shown in the figure) is 1185mm.

[0044] The contour lines of multiple characteristic sections of the blade body 2 structure are obtained using 3D modeling software, and the area distribution law of each section along the distribution is adjusted according to the requirements of strength design to obtain a cross-sectional area distribution that meets the strength requirements. Then, the full 3D computational fluid dynamics simulation software is used to perform aerodynamic analysis on the blade stage, and the local blade profile contour line is adjusted according to the flow characteristics of the stage, thereby obtaining a characteristic cross-sectional profile line that conforms to the root subsonic, middle transonic, and top supersonic flow characteristics. The blade body 2 structure uses high-order Bezier curves and third-order C-spline curves to optimize, smooth, and locally fine-tune each characteristic section.

[0045] Specifically, the blade body 2 of the last stage moving blade is formed by stacking and twisting a plurality of characteristic cross sections according to a certain rule. Among them, the characteristic parameters of the moving blade include: the blade body height H.

[0046] The contour line of each characteristic section is a closed curve composed of the leading edge, pressure surface, trailing edge and suction surface.

[0047] The characteristic section has the following characteristic parameters: installation angle C, pitch T, axial width Xa, chord length B, maximum thickness W, section height h, relative blade height h / H and other characteristic parameters.

[0048] Specifically, the relative value of the blade height H increases monotonically from 0.0 to 1.0; the relative value of the relative blade height h / H increases linearly from 0.0 to 1.0; the absolute value of the installation angle C decreases monotonically from 52.89° to 13.33°; each characteristic section takes the root section, that is, the characteristic parameter of the section with relative blade height h / H=0 equal to 1 as the benchmark; the relative values ​​of the characteristic parameters of the characteristic section and the root section have the following characteristics:

[0049] 1) The relative value of pitch T increases linearly from 1.0 to 1.6 from the root section to the top section;

[0050] 2) The relative value of the axial width Xa decreases linearly from 1.0 to 0.87 from the root section to the top section;

[0051] 3) The relative value of the chord length B increases linearly from 1.0 to 1.36 from the root section to the top section;

[0052] 4) The relative value of the maximum thickness W decreases linearly from 1.0 to 0.36 from the root section to the top section.

[0053] The blade body 2 structure is formed by a plurality of characteristic cross sections with different contour shapes that continuously and smoothly transition from the root end to the tip end along the height direction of the blade body 2. In this embodiment, the blade body 2 structure has a total of 5 characteristic cross sections.

[0054] Specifically, the key cross section is determined in the following way: Figure 4 As shown, the blade body 2 structure is formed by 5 characteristic cross sections with different contour shapes that continuously and smoothly transition from the root end to the top end along the blade body height H direction, and the arrangement order of each characteristic cross section from the root to the top is 1 to 5.

[0055] As shown in Table 1, the characteristic section includes three key sections, specifically, the key sections include the AA section at 0.0% of the blade height H, the CC section at 50% of the blade height H, and the EE section at 100% of the blade height H; the theoretical contour line of each section is described by the coordinates (X, Y) of several discrete points, and each discrete point is smoothly connected to obtain the theoretical contour line of the corresponding key section. The theoretical contour line of each key section is described by the coordinates (X, Y) of 24 discrete points respectively. By optimizing the parameters of the contour line of each characteristic section, the last stage moving blade has better adaptability to the angle of attack and excellent performance under variable working conditions.

[0056] Table 1 Relative heights of three key sections at the blade height H

[0057] Section Name Relative leaf height AA 0.0％ CC 50％ EE 100％ .

[0058] The theoretical contour lines of the AA section, CC section and EE section are described by the coordinates (X, Y) of the following discrete points respectively.

[0059] Specifically, the theoretical contour line of the AA section is described by the coordinates (X, Y) of the following discrete points:

[0060] Table 2 Coordinate data of discrete points of section A-A

[0061]

[0062]

[0063] Specifically, the theoretical contour of the CC section is described by the coordinates (X, Y) of the following discrete points:

[0064] Table 3 Coordinate data of discrete points of C-C section

[0065] No. 1 2 3 4 5 6 7 8 X -68.7 -69.6 -63.7 -54.4 -44.7 -34.3 -23.1 -10.4 Y -99.8 -99.8 -86.8 -67.8 -48.9 -30.1 -11.6 6.4 No. 9 10 11 12 13 14 15 16 X 5.0 25 50.3 59.4 60.9 60.7 55.0 33.6 Y 23.2 37.1 44.2 43.2 42.0 40.2 34.9 22.3 No. 17 18 19 20 21 22 23 24 X 16.4 -0.9 -14.2 -25.7 -37.4 -49.7 -61.6 -67.6 Y 9.5 -4.7 -18.5 -33.1 -50.0 -69.1 -88.3 -97.9 .

[0066] Specifically, the theoretical contour of the EE section is described by the coordinates (X, Y) of the following discrete points:

[0067] Table 4 Coordinate data of discrete points of section E-E

[0068] No. 1 2 3 4 5 6 7 8 X -71.7 -72.4 -64.8 -53.4 -41.9 -30.4 -18.6 -6.0 Y -113.2 -113.0 -98.3 -76.7 -55.0 -33.4 -12.0 9.0 No. 9 10 11 12 13 14 15 16 X -8.2 24.7 45.0 55.1 57.3 57.0 51.0 34.0 Y 28.9 46.9 60.0 60.9 59.3 57.1 51.0 34.0 No. 17 18 19 20 21 22 23 24 X 18.4 3.7 -10.2 -25.7 -23.7 -50.0 -63.1 -70.3 Y 16.4 -2.2 -21.4 -33.1 -40.8 -80.2 -100.0 -111.0 .

[0069] The contour line of each characteristic section may have a tolerance zone, and the range of the tolerance zone is within the contour shape range formed by a circle with a discrete point of the theoretical contour line of each characteristic section as the center and a radius of 0.2mm to 0.7mm as the envelope.

[0070] The technical solutions provided by the embodiments of the present invention are introduced in detail above. Specific examples are used herein to illustrate the principles and implementation methods of the embodiments of the present invention. The description of the above embodiments is only applicable to help understand the principles of the embodiments of the present invention. At the same time, for those skilled in the art, according to the embodiments of the present invention, there will be changes in the specific implementation methods and application scopes. In summary, the content of this specification should not be understood as limiting the present invention.

Claims

1. A final stage moving blade for a carbon dioxide compression energy storage turbine, characterized in that: The blade structure of the last stage moving blade is formed by stacking and twisting a plurality of characteristic cross sections in a regular manner; The characteristic parameters of the moving blades include: blade height H; The contour line of each characteristic section is a closed curve composed of a leading edge, a pressure surface, a trailing edge, and a suction surface; the characteristic parameters of the characteristic section include: installation angle C, pitch T, axial width Xa, chord length B, maximum thickness W, section height h, relative blade height h / H; the superposition rule of each characteristic section is a continuous and smooth transition from the root end to the tip end along the blade height direction; The relative value of the blade height H increases monotonically from 0.0 to 1.0; The relative value of the relative leaf height h / H increases linearly from 0.0 to 1.0; The absolute value of the installation angle C decreases monotonically from 52.89° to 13.33°; The characteristic parameters of each characteristic section are based on the root section; The relative value of the pitch T increases linearly from 1.0 to 1.6 from the root section to the top section; The relative value of the axial width Xa decreases linearly from 1.0 to 0.87 from the root section to the top section; The relative value of the chord length B increases linearly from 1.0 to 1.36 from the root section to the top section; The relative value W of the maximum thickness decreases linearly from 1.0 to 0.36 from the root section to the top section.

2. The last stage moving blade for compressing carbon dioxide energy storage turbine according to claim 1, characterized in that: The blade structure is formed by five characteristic cross sections with different contour shapes, which transition continuously and smoothly from the root end to the tip end along the height direction of the blade.

3. The last stage moving blade for compressing carbon dioxide energy storage turbine according to claim 1, characterized in that: The characteristic cross-section includes three key cross-sections, including the AA cross-section located at 0.0% of the blade height H, the CC cross-section located at 50% of the blade height H, and the EE cross-section located at 100% of the blade height H; the theoretical contour line of each cross-section is described by the coordinates (X, Y) of a number of discrete points, and the discrete points are smoothly connected to obtain the theoretical contour line of the corresponding key cross-section.

4. The last stage moving blade for compressing carbon dioxide energy storage turbine according to claim 3, characterized in that: The theoretical contour lines of each of the key cross sections are described by coordinates (X, Y) of 24 discrete points.

5. The last stage moving blade for compressing carbon dioxide energy storage turbine according to claim 3, characterized in that: The theoretical contour of the AA section is described by the coordinates (X, Y) of the following discrete points: 。 6. The last stage moving blade for compressing carbon dioxide energy storage turbine according to claim 3, characterized in that: The theoretical contour of the CC section is described by the coordinates (X, Y) of the following discrete points: 。 7. The last stage moving blade for compressing carbon dioxide energy storage turbine according to claim 3, characterized in that: The theoretical contour of the EE section is described by the coordinates (X, Y) of the following discrete points: 。 8. The last stage moving blade for compressing carbon dioxide energy storage turbine according to claim 3, characterized in that: The contour line of each characteristic section may have a tolerance zone, and the range of the tolerance zone is within the contour shape range formed by a circle with a discrete point of the theoretical contour line of each characteristic section as the center and a radius of 0.2mm~0.7mm as the envelope.

9. The last stage moving blade for compressing carbon dioxide energy storage turbine according to claim 1, characterized in that: The blade height H is 373 mm; the root diameter Dr is 1185 mm.

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