A gas turbine compressor blade row

Abstract

The present invention discloses a gas turbine compressor blade row, including blades and mounting parts for fixing the blades. The flow path surface of the mounting part close to the blade side extends circumferentially to form an end wall surface. The end wall surfaces between adjacent blades form a flow path unit. The flow path unit includes multiple flow path areas. Adjacent flow path areas have a height difference at the circumferential intersection to reduce secondary flow loss and corner separation loss near the end wall surface.

Description

Technical Field

[0001] The present invention relates to the field of gas turbines, and in particular to a gas turbine compressor blade row. Background Art

[0002] As gas turbine compressors develop towards higher loads, the three-dimensional flow effects within the compressor intensify. The secondary flow intensity at the end of a high-load compressor is high, and flow separation is prone to occur under strong adverse pressure gradients. Near the endwall, the interaction between the secondary flow and the suction surface boundary layer can easily induce corner separation, resulting in significant flow losses and adversely affecting the compressor's aerodynamic performance. For the rear stages of a multi-stage axial-flow compressor, the impact of the end-stage flow on the compressor's aerodynamic performance becomes more significant as blade height decreases.

[0003] The asymmetric endwall structure is a design method that can effectively suppress secondary flow and corner separation on the endwall and improve compressor efficiency. The asymmetric endwall structure uses the convex and concave changes of the endwall to adjust the pressure distribution by shaping the endwall into a three-dimensional curved surface, thereby reducing the secondary flow and corner separation on the endwall. Existing research shows that a local convex endwall near the pressure side and a local concave endwall near the suction side is a better blade row shape. The local convex endwall near the pressure side can reduce the static pressure near the pressure side, while the local concave endwall near the suction side can increase the pressure near the suction side, thereby reducing the lateral pressure gradient from the pressure side to the suction side near the endwall and reducing the secondary flow.

[0004] Patent CN112446107A discloses a method for establishing a flow control structure in the end area of ​​a compressor. A concave-convex structure is formed on the end wall at the inlet of the compressor stator blades and controlled by a sine function. The incoming gas is used to form an array of flow vortex structures between the concave-convex structures arranged on the end wall.

[0005] Patent CN112560195A discloses a method for blade row shaping of an axial flow impeller. For end wall profiles with different concave and convex shapes, the configuration area is first divided. By adopting the circumferential third-order Fourier series curve, various complex end wall structures are flexibly constructed based on the use of fewer variables. Then, the third-order Fourier series curve along the circumference of the blade is read, and the axial direction is smoothly connected with a spline curve to form the blade row shape.

[0006] As mentioned above, existing asymmetric endwall structural solutions all consider the endwall surface as a whole and ensure the continuity of the curvature of the entire endwall surface. The shape of the endwall surface is generally controlled by multiple axial and circumferential control curves or discrete control points. The optimization process requires adjusting numerous design parameters, making the design process more difficult and time-consuming. Furthermore, existing blade row designs are significantly more difficult to manufacture than axisymmetric endwalls.

[0007] In view of the above technical problems, the present invention is specially introduced. Summary of the Invention

[0008] The main purpose of the present invention is to provide a gas turbine compressor blade row to solve the problems that the existing blade row design method requires many design parameters to be adjusted and is difficult to manufacture.

[0009] In order to achieve the above-mentioned objectives, the present invention proposes a gas turbine compressor blade row, including blades and mounting parts for fixing the blades, wherein the flow path surface of the mounting part close to the blade side extends circumferentially to form an end wall surface, and is characterized in that the end wall surfaces between adjacent blades form a flow path unit, and the flow path unit includes multiple flow path areas, and adjacent flow path areas have a height difference at the circumferential junction to reduce secondary flow loss and corner separation loss near the end wall surface.

[0010] Furthermore, the contours of the multiple flow channel areas are respectively defined by different flow channel profile lines, and the multiple flow channel areas are combined to form an asymmetric end wall structure.

[0011] Furthermore, each flow channel area includes at least one sub-area, each sub-area is convex or concave relative to the reference plane defined by the blade, and the sub-area adjacent to the sub-area is concave or convex relative to the reference plane defined by the blade, and the sub-areas adjacent to each other form a concave-convex change, wherein the reference plane extends from the leading edge to the trailing edge of the blade.

[0012] Furthermore, the contours of the plurality of flow channel regions are formed by revolving different flow channel profiles around the compressor axis.

[0013] Furthermore, the plurality of flow channel regions include a first flow channel region and a second flow channel region, the first flow channel region is the region where the root of the blade is located, and the second flow channel region is sandwiched between two adjacent first flow channel regions.

[0014] Furthermore, the first flow channel region includes a first sub-region and a second sub-region arranged axially along the end wall surface, and the contours of adjacent first and second sub-regions vary in concave and convex manner to adjust the pressure distribution at the blade root.

[0015] Furthermore, the second flow channel region includes a third sub-region and a fourth sub-region arranged axially along the end wall surface, and the contours of adjacent third sub-regions and fourth sub-regions vary in concave and convexity to adjust the pressure distribution at the root of the blade.

[0016] Furthermore, the first subregion corresponds to a first recessed portion relative to the reference plane, the third subregion corresponds to a first raised portion relative to the reference plane, the second subregion corresponds to a second raised portion relative to the reference plane, and the fourth subregion corresponds to a second recessed portion relative to the reference plane.

[0017] Furthermore, the first sub-region, the second sub-region, the third sub-region, and the fourth sub-region respectively define their respective flow channel profiles through the following function curves:

[0018] T=az 5 +bz 4 +cz 3 +dz 2 +ez 1 +f

[0019] Wherein, T is the distance from a point on the flow channel profile to the reference plane, z is the axial position coordinate along the end wall, a, b, c, d, e, and f are polynomial coefficients, and the flow channel profiles of the first sub-region, the second sub-region, the third sub-region, and the fourth sub-region have different polynomial coefficients.

[0020] Furthermore, the first sub-region extends from the first endpoint to the second endpoint along the first flow channel profile in the axial direction of the end wall surface, and the polynomial coefficients a1, b1, c1, d1, e1, and f1 of the function curve of the first flow channel profile are determined by one or more factors including the axial coordinates of the first endpoint and the second endpoint, the distances from the first endpoint and the second endpoint to the reference plane, the tangent slopes at the first endpoint and the second endpoint, and the maximum distance value of the first recessed portion 1 to the reference plane, the axial coordinates at the maximum distance, and the tangent slope at the maximum distance.

[0021] Furthermore, the third sub-region extends from the third endpoint along the third flow channel profile to the fourth endpoint in the axial direction of the end wall surface, and the polynomial coefficients a3, b3, c3, d3, e3, and f3 of the function curve of the third flow channel profile are determined by one or more factors including the axial coordinates of the third endpoint and the fourth endpoint, the distances from the third endpoint and the fourth endpoint to the reference plane, the tangent slopes at the third endpoint and the fourth endpoint, and the maximum distance value from the first protrusion 2 to the reference plane, the axial coordinates at the maximum distance, and the tangent slope at the maximum distance.

[0022] Furthermore, the second sub-region extends from the second endpoint along the second flow channel profile to the fifth endpoint in the axial direction of the end wall surface, and the polynomial coefficients a2, b2, c2, d2, e2, and f2 of the function curve of the second flow channel profile are determined by one or more factors including the axial coordinates of the second endpoint and the fifth endpoint, the distances from the second endpoint and the fifth endpoint to the reference plane, the tangent slopes at the second endpoint and the fifth endpoint, and the maximum distance value from the second protrusion 1 to the reference plane, the axial coordinates at the maximum distance, and the tangent slope at the maximum distance.

[0023] Furthermore, the fourth sub-region extends axially from the fourth endpoint along the fourth flow channel profile to the sixth endpoint on the end wall surface, and the polynomial coefficients a4, b4, c4, d4, e4, and f4 of the function curve of the fourth flow channel profile are determined by one or more factors including the axial coordinates of the fourth endpoint and the sixth endpoint, the distances from the fourth endpoint and the sixth endpoint to the reference plane, the tangent slopes at the fourth endpoint and the sixth end, the maximum distance value from the second recessed portion to the reference plane, the axial coordinates at the maximum distance, and the tangent slope at the maximum distance.

[0024] Furthermore, the first endpoint and the third endpoint are close to the leading edge of the blade.

[0025] Furthermore, the second endpoint and the fourth endpoint are close to the middle of the blade.

[0026] Furthermore, the fifth endpoint and the sixth endpoint are close to the trailing edge of the blade.

[0027] Furthermore, the position where the first recessed portion has the largest distance from the reference plane is located at 10% to 40% of the axial chord length of the blade, and the maximum distance from the first recessed portion to the reference plane is less than 1% of the blade height.

[0028] Furthermore, the position where the distance between the first protrusion and the reference plane is the largest is located at 10% to 40% of the axial chord length of the blade, and the maximum distance between the first protrusion and the reference plane is less than 1% of the blade height.

[0029] Furthermore, the coordinate at which the distance between the second raised portion 1 and the reference plane is the largest is located at 60% to 90% of the axial chord length of the blade, and the maximum distance between the second raised portion 1 and the reference plane is less than 1% of the blade height.

[0030] Furthermore, the position where the second recessed portion is at the maximum distance from the reference plane is located at 60% to 90% of the axial chord length of the blade, and the maximum distance from the second recessed portion to the reference plane is less than 1% of the blade height.

[0031] Furthermore, the junction between the first flow channel area and the second flow channel area has a smooth transition to reduce flow loss.

[0032] Furthermore, a third flow channel area is axially provided on the end wall surface, and the third flow channel area extends from the front end of the blade to the leading edge of the blade. The flow channel profile of the third flow channel area along the axial direction of the end wall surface of the mounting part is a straight line.

[0033] Furthermore, a fourth flow channel region is axially provided on the end wall surface. The fourth flow channel region extends from the trailing edge of the blade to the rear end of the blade. The flow channel profile of the fourth flow channel region along the axial direction of the end wall surface is a straight line.

[0034] Furthermore, the end wall surface includes a plurality of flow channel units, and the height difference between the first flow channel area and the second flow channel area in the plurality of flow channel units at the circumferential junction of the end wall surface varies periodically.

[0035] Furthermore, the first flow channel region and the second flow channel region in adjacent flow channel units have different height differences at the circumferential intersection of the end wall surfaces.

[0036] Furthermore, the height difference between the first flow channel area and the second flow channel area in the spaced-apart flow channel units at the circumferential intersection of the end wall surfaces is the same.

[0037] The application of the technical solution of the present invention achieves at least the following beneficial effects:

[0038] 1. By dividing the end wall surface of the mounting part between adjacent blades into regions and using different flow channel profiles to control the circumferential outer wall pressure distribution, a height difference is formed between adjacent flow channel areas, thereby suppressing the end wall secondary flow and corner zone separation, improving compressor efficiency; and increasing the degree of freedom in the design of the end wall surface of the compressor mounting part.

[0039] 2. Concave and convex changes are formed between adjacent sub-areas, forming an asymmetric end wall structure, thereby adjusting the pressure distribution near the blade root.

[0040] 3. In response to uneven air intake conditions, the compressor is adapted to the uneven airflow along the circumferential direction near the blade root, further improving the aerodynamic performance of the compressor.

[0041] 4. The number of control curves in each flow channel area of ​​the compressor is relatively small, which facilitates the optimization and adjustment of parameters and reduces the difficulty of design. In addition, each flow channel area is a curved surface of revolution, which reduces the difficulty of processing and manufacturing. BRIEF DESCRIPTION OF THE DRAWINGS

[0042] The accompanying drawings, which constitute part of the present invention, are intended to provide a further understanding of the present invention. The exemplary embodiments of the present invention and their descriptions are intended to explain the present invention and do not constitute an undue limitation of the present invention. In the accompanying drawings:

[0043] Figure 1 Schematic diagram of adjacent flow channel areas according to Example 1 of the present invention is shown;

[0044] Figure 2 Schematic diagram of adjacent flow channel areas according to Example 1 of the present invention is shown;

[0045] Figure 3 Schematic diagram of flow channel profiles of each sub-region of Example 1 of the present invention is shown;

[0046] Figure 4 A cross-sectional view at a position of 20% axial chord length of embodiment 1 of the present invention is shown;

[0047] Figure 5 A cross-sectional view at a position of 80% of the axial chord length of embodiment 1 of the present invention is shown;

[0048] Figure 6The compressor circumferential flow channel profile T at 20% axial chord length is shown. tf Change graph.

[0049] The above drawings include the following reference numerals:

[0050] 10. Blade; 20. Mounting part; 200. End wall; 210. First flow channel region; 211. First sub-region; 2111. First recessed portion; 212. Second sub-region; 2121. Second raised portion; 220. Second flow channel region; 221. Third sub-region; 2211. First raised portion; 222. Fourth sub-region; 2221. Second recessed portion; 230. Third flow channel region; 240. Fourth flow channel region. DETAILED DESCRIPTION

[0051] It should be noted that, in the absence of conflict, the embodiments and features of the embodiments of the present invention can be combined with each other. The present invention will be described in detail below with reference to the accompanying drawings and in combination with the embodiments.

[0052] The present invention is described in further detail below with reference to specific embodiments. These embodiments are not to be construed as limiting the scope of protection claimed by the present invention. The term "including" when used indicates the presence of a feature, but does not exclude the presence or addition of one or more other features; the terms "lateral", "upper", "lower", "front", "back", "left", "right", "top", "bottom", "inside", "outside" and the like indicate directions or positional relationships based on the directions or positional relationships shown in the accompanying drawings, and are only for ease of description, and do not indicate or imply that the device or element referred to must have a specific direction, be constructed and operated in a specific direction, and therefore cannot be construed as limiting the present invention; in addition, the terms "first" and "second" are only used for descriptive purposes, and cannot be construed as indicating or implying relative importance.

[0053] In this description, it should be noted that, unless otherwise specified or limited, the terms "installed," "connected," and "connected" should be understood broadly. For example, they can refer to fixed connections, detachable connections, or integral connections; they can refer to direct connections, indirect connections through an intermediate medium, or internal connections between two components. Those skilled in the art will understand the specific meanings of these terms in the present invention. Furthermore, in the description of the present invention, unless otherwise specified, "plurality" means two or more.

[0054] Example 1:

[0055] The existing compressor end wall design method requires adjustment of many design parameters and is difficult to process. This application proposes a structure for a gas turbine compressor blade row, which solves the above problems by dividing the end wall between adjacent blades into areas and using different flow channel profiles to control the end wall pressure distribution.

[0056] The gas turbine compressor blade row structure proposed in this application is as follows Figure 1 As shown, it includes a blade 10 and a mounting member 20 for fixing the blade 10. The flow path surface of the mounting member close to the blade side extends circumferentially to form an end wall surface. A flow path unit is formed between the end wall surfaces 200 of adjacent blades 10. The flow path unit includes multiple flow path areas. Adjacent flow path areas have a height difference at the circumferential junction to reduce secondary flow loss and corner separation loss near the end wall surface.

[0057] In the present application, the blades may be stationary blades or moving blades. When they are stationary blades, the mounting parts are outer rings or spacer blocks. When they are moving blades, the mounting parts are wheels or spacer blocks, half blocks, or locking blocks.

[0058] Specifically, the multiple flow channel regions are divided into a first flow channel region 210 and a second flow channel region 220. The first flow channel region 210 is the root region of the blade 10, and the second flow channel region 220 is sandwiched between two adjacent first flow channel regions 210. By dividing the end wall surface 200 between adjacent blades into regions and using different flow channel profiles to control the end wall pressure distribution, a height difference is formed between the flow channel regions, thereby suppressing secondary flow and corner separation on the end wall, thereby improving compressor efficiency.

[0059] In the present application, for axially mounted moving blades with tenons, the second flow channel area 220 is the flow channel surface of the compressor wheel; for circumferentially mounted moving blades with tenons, the second flow channel area 220 is the flow channel surface of the spacer block, half block or locking block; for axially mounted stationary blades with tenons, the second flow channel area 220 is the outer annular flow channel surface of the stationary blade; for circumferentially mounted stationary blades with tenons, the second flow channel area 220 is the flow channel surface of the spacer block.

[0060] Combine Figure 1 and Figure 2 As shown, the contours of multiple flow channel areas are respectively defined by different flow channel profiles, and the multiple flow channel areas are combined to form an asymmetric end wall structure. The contours of each flow channel area are formed by rotating different flow channel profiles around the compressor axis.

[0061] Furthermore, the present application further divides each flow channel region into at least one sub-region. Each sub-region is either convex or concave relative to a reference plane defined by the blade. At the same time, adjacent sub-regions are concave or convex relative to the reference plane defined by the blade, creating a concave-convex variation between adjacent sub-regions. The "reference plane" here refers to the surface formed by the linear rotation extending from the leading edge to the trailing edge of the blade. This concave-convex variation between adjacent sub-regions regulates the pressure distribution near the blade root.

[0062] Specifically, if Figure 1 As shown, the first flow channel region 210 includes a first sub-region 211 and a second sub-region 212 arranged along the axial direction of the end wall surface 200. The contours of the adjacent first sub-regions 211 and second sub-regions 212 vary in concave and convex manner to adjust the pressure distribution at the root of the blade 10. Figure 2 As shown, the second flow channel region 220 includes a third sub-region 221 and a fourth sub-region 222 arranged axially along the end wall surface 200 , and the contours of adjacent third sub-regions 221 and fourth sub-regions 222 vary to adjust the pressure distribution at the root of the blade 10 .

[0063] Preferably, combined Figure 1-3 As shown, the first sub-region 211 corresponds to a first recessed portion 2111 relative to the reference plane, the third sub-region 221 corresponds to a first raised portion 2211 relative to the reference plane, the second sub-region 212 corresponds to a second raised portion 2121 relative to the reference plane, and the fourth sub-region 222 corresponds to a second recessed portion 2221 relative to the reference plane. By designing the flow channel profile, the first flow channel region is concave at the front and convex at the rear, while the second flow channel region is convex at the front and concave at the rear. This reduces the blade flow pressure gradient and the lateral pressure gradient from the pressure side of the blade to the suction side, suppresses secondary flow on the end wall and corner separation, and improves compressor efficiency.

[0064] The present application uses a quintic polynomial function to define the flow channel profiles of each group of the first sub-region 211 , the second sub-region 212 , the third sub-region 221 and the fourth sub-region 222 , thereby reducing the design difficulty.

[0065] Specifically, the quintic polynomial function is:

[0066] T=az 5 +bz 4 +cz 3 +dz 2 +ez 1 +f

[0067] Where T is the distance from a point on the flow channel profile to the reference plane. A positive value indicates convexity relative to the reference plane, while a negative value indicates concaveness relative to the reference plane. z is the axial position coordinate along the end wall 200. a, b, c, d, e, and f are polynomial coefficients. The flow channel profiles of the first subregion 211, the second subregion 212, the third subregion 221, and the fourth subregion 222 have different polynomial coefficients.

[0068] Specifically, the first sub-region 211 extends from the first endpoint along the first flow channel line to the second endpoint in the axial direction of the end wall surface 200. The second sub-region 212 extends from the second endpoint along the second flow channel line to the fifth endpoint in the axial direction of the end wall surface 200. The third sub-region 221 extends from the third endpoint along the third flow channel line to the fourth endpoint in the axial direction of the end wall surface 200. The fourth sub-region 222 extends from the fourth endpoint along the fourth flow channel line to the sixth endpoint in the axial direction of the end wall surface 200.

[0069] like Figure 3 As shown, the first endpoint and the third endpoint are close to the leading edge of the blade 10 , the second endpoint and the fourth endpoint are close to the middle of the blade 10 , and the fifth endpoint and the sixth endpoint are close to the trailing edge of the blade 10 .

[0070] The following is a method for determining the polynomial coefficients of the function curves defining the flow channel profiles of the first sub-region 211 , the second sub-region 212 , the third sub-region 221 , and the fourth sub-region 222 .

[0071] The polynomial coefficients a1, b1, c1, d1, e1, and f1 of the function curve of the first runner profile are determined by one or more factors including the axial coordinates of the first endpoint and the second endpoint, the distances from the first endpoint and the second endpoint to the reference plane, the tangent slopes at the first endpoint and the second endpoint, and the maximum distance value from the first recessed portion 2111 to the reference plane, the axial coordinates at the maximum distance, and the tangent slope at the maximum distance.

[0072] The polynomial coefficients a3, b3, c3, d3, e3, and f3 of the function curve of the third runner profile are determined by one or more factors including the axial coordinates of the third endpoint and the fourth endpoint, the distances from the third endpoint and the fourth endpoint to the reference plane, the tangent slopes at the third endpoint and the fourth endpoint, and the maximum distance value from the first protrusion 2211 to the reference plane, the axial coordinates at the maximum distance, and the tangent slope at the maximum distance.

[0073] Specifically, the derivative of the polynomial function, i.e. the slope of the tangent line, is:

[0074] T'=5az 4 +4bz 3 +3cz 2 +2dz+e

[0075] The function curve of the first runner profile and its derivative satisfy the following equations:

[0076]

[0077] Among them, the first and second equations represent that the first endpoint, i.e., the point with the axial coordinate z1, is located on the reference plane, and the flow channel profile is tangent to the reference plane; the fifth and sixth equations represent that the second endpoint, i.e., the point with the axial coordinate z2, is located on the flow channel profile. The distance from the point to the reference line is T2, and the corresponding tangent slope is T2'; in the third and fourth equations, z tf is the axial coordinate of the maximum convex or concave position of the runner profile, and the corresponding maximum convex or concave distance is T tf , and the slope of the tangent at this point is 0, meaning the tangent is parallel to the reference line. Solving the six linear equations above yields the six polynomial coefficients a1, b1, c1, d1, e1, and f1. Similarly, the polynomial coefficients a3, b3, c3, d3, e3, and f3 for the function curve of the third runner profile can be determined.

[0078] The polynomial coefficients a2, b2, c2, d2, e2, and f2 of the function curve of the second runner profile are determined by one or more factors including the axial coordinates of the second endpoint and the fifth endpoint, the distances from the second endpoint and the fifth endpoint to the reference plane, the tangent slopes at the second endpoint and the fifth endpoint, and the maximum distance value from the second protrusion 2121 to the reference plane, the axial coordinates at the maximum distance, and the tangent slope at the maximum distance.

[0079] The polynomial coefficients a4, b4, c4, d4, e4, and f4 of the function curve of the fourth flow channel profile are determined by one or more factors including the axial coordinates of the fourth endpoint and the sixth endpoint, the distances from the fourth endpoint and the sixth endpoint to the reference plane, the tangent slopes at the fourth endpoint and the sixth end, and the maximum distance value from the second recessed portion 2221 to the reference plane, the axial coordinates at the maximum distance, and the tangent slope at the maximum distance.

[0080] Specifically, the function curve of the second runner profile and its derivative satisfy the following equations:

[0081]

[0082] Among them, the first and second equations represent the second endpoint, that is, the point with the axial coordinate z2. The distance from the point on the flow channel profile to the reference straight line is T2, and the corresponding tangent slope is T2', which is the same as the previous curve. That is, the second flow channel profile coincides with the first flow channel profile at the axial position z2, and the tangent slopes are equal; the fifth and sixth equations represent that the point with the axial coordinate z5 is located on the reference plane, and the flow channel profile is tangent to the reference plane; in the third and fourth equations, z tsis the axial coordinate of the maximum convex or concave position of the runner profile, and the corresponding maximum convex or concave distance is T ts , and the slope of the tangent at this point is 0, that is, the tangent is parallel to the reference plane. By solving the above linear equation system consisting of 6 equations, the 6 polynomial coefficients a2, b2, c2, d2, e2, and f2 can be obtained. Similarly, the polynomial coefficients a4, b4, c4, d4, e4, and f4 of the function curve of the fourth runner profile can be obtained.

[0083] In addition, the values ​​must also meet the following restrictions: the position where the first recessed portion 2111 has the largest distance from the reference plane is located between 10% and 40% of the axial chord length of the blade 10, and the maximum distance from the first recessed portion 2111 to the reference plane is less than 1% of the height of the blade 10. The position where the first raised portion 2211 has the largest distance from the reference plane is located between 10% and 40% of the axial chord length of the blade 10, and the maximum distance from the first raised portion 2211 to the reference plane is less than 1% of the height of the blade 10.

[0084] The position where the second raised portion 2121 has the greatest distance from the reference plane is located between 70% and 90% of the axial chord length of the blade 10, and the maximum distance from the second raised portion 2121 to the reference plane is less than 1% of the height of the blade 10. The position where the second recessed portion 2221 has the greatest distance from the reference plane is located between 70% and 90% of the axial chord length of the blade 10, and the maximum distance from the second recessed portion 2221 to the reference plane is less than 1% of the height of the blade 10.

[0085] In addition, the end wall surface 200 is axially provided with a third flow channel region 230, which extends from the front end of the blade 10 to the leading edge of the blade 10, and the flow channel profile of the third flow channel region 230 along the end wall surface 200 is linear. The end wall surface 200 is also axially provided with a fourth flow channel region 240, which extends from the trailing edge of the blade 10 to the rear end of the blade 10, and the flow channel profile of the fourth flow channel region 240 along the end wall surface 200 is linear.

[0086] In addition, according to Figure 4 and Figure 5 As shown, the junction between the first flow channel area 210 and the second flow channel area 220 is smoothly transitioned to reduce flow loss caused by the step height difference.

[0087] In this embodiment, the first and second flow channel regions 210, 220 at different circumferential angles of the compressor can each utilize the same flow channel profile. In this case, only two types of flow channel profiles are used for compressor end wall shaping. The fewer control curves for each compressor flow channel region facilitates parameter optimization and reduces design complexity. Furthermore, each flow channel region is a curved surface of revolution, reducing manufacturing complexity.

[0088] In summary, from the above description, it can be seen that the above-mentioned embodiment 1 of the present invention achieves the following technical effects: 1. By dividing the end wall surface between adjacent blades into areas and using different flow channel profiles to control the circumferential end wall pressure distribution, a height difference is formed between the flow channel areas, thereby suppressing the end wall secondary flow and corner area separation, and improving the compressor efficiency; and increasing the freedom of the compressor end wall curved surface design; 2. Concave and convex changes are formed between adjacent sub-areas to form an asymmetric end wall structure, thereby adjusting the pressure distribution near the blade root; 3. The number of control curves of each flow channel area of ​​the compressor is relatively small, which facilitates the optimization and adjustment of parameters and reduces the design difficulty, and each flow channel area is a curved rotation surface, which reduces the difficulty of processing and manufacturing.

[0089] Example 2:

[0090] Under uniform air intake conditions, the first flow channel regions 210 and the second flow channel regions 220 located at different angular positions in the circumferential direction of the compressor may each adopt the same flow channel profile, as described in the first embodiment.

[0091] Under uneven air intake conditions, the entire circumferential end wall of the gas turbine compressor can be divided into multiple flow channel units. The height difference between the first flow channel region 210 and the second flow channel region 220 at the circumferential intersection of the end wall 200 in the multiple flow channel units varies periodically. The height difference between the first flow channel region 210 and the second flow channel region 220 at the circumferential intersection of the end wall 200 in adjacent flow channel units is different. The height difference between the first flow channel region 210 and the second flow channel region 220 at the circumferential intersection of the end wall 200 in spaced-apart flow channel units is the same.

[0092] like Figure 6 As shown, the gas turbine compressor stator blade row is divided into multiple angle intervals along the circumferential direction. In each angle interval, the first flow channel area 210 and the second flow channel area 220 can be adjusted by taking different T tf or T ts values, forming different flow channel profiles to adapt to the uneven airflow along the circumferential direction near the blade root and improve the aerodynamic performance of the compressor.

[0093] Preferably, the compressor is divided into six angular intervals along the circumferential direction. The angular intervals of 0-60°, 120-180°, and 240-300° correspond to lower total intake pressure areas, where the first flow channel area 210 and the second flow channel area 220 are more convex or concave, effectively reducing flow losses. The angular intervals of 60-120°, 180-240°, and 300-360° correspond to higher total intake pressure areas, where the first flow channel area 210 and the second flow channel area 220 are less convex or concave.

[0094] In summary, from the above description, it can be seen that the above-mentioned embodiment 2 of the present invention achieves the following technical effects: in response to uneven air intake conditions, the compressor stator blade row is divided into multiple angular intervals along the circumferential direction, and within each angular interval, different flow channel profiles are designed for the first flow channel area and the second flow channel area to adapt to the uneven airflow along the circumferential direction near the blade root, thereby further improving the aerodynamic performance of the compressor.

[0095] The foregoing description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. Those skilled in the art will readily appreciate that various modifications and variations of the present invention are possible. Any modifications, equivalent substitutions, or improvements made within the spirit and principles of the present invention are intended to be within the scope of protection of the present invention.

Claims

1. A gas turbine compressor blade row, comprising a blade (10) and a mounting member (20) for fixing the blade (10), wherein a flow path surface of the mounting member (20) on a side close to the blade (10) extends circumferentially to form an end wall surface (200), characterized in that: The end wall surface (200) between adjacent blades (10) forms a flow channel unit, and the flow channel unit includes a plurality of flow channel areas, and adjacent flow channel areas have a height difference at the circumferential intersection to reduce the secondary flow loss and corner separation loss near the end wall surface (200); the contours of the plurality of flow channel areas are respectively defined by different flow channel lines, and the plurality of flow channel areas are combined to form an asymmetric end wall structure; each of the flow channel areas includes at least one sub-area, and each of the sub-areas is convex or concave relative to the reference surface defined by the blade (10), and is aligned with the reference surface defined by the blade (10). The adjacent sub-regions are concave or convex relative to the reference plane defined by the blade (10), and the adjacent sub-regions form a concave-convex change, wherein the reference plane extends from the leading edge to the trailing edge of the blade (10); the contours of the multiple flow channel regions are formed by rotating different flow channel lines around the compressor axis; the multiple flow channel regions are a first flow channel region (210) and a second flow channel region (220), the first flow channel region (210) is the region where the root of the blade (10) is located, and the second flow channel region (220) is sandwiched between the respective flow channel regions. Between two adjacent first flow channel areas (210); the first flow channel area (210) includes a first sub-area (211) and a second sub-area (212) arranged axially along the end wall surface (200), and the concave-convex changes of the contours of the adjacent first sub-area (211) and the second sub-area (212) are used to adjust the pressure distribution at the root of the blade (10); the second flow channel area (220) includes a third sub-area (221) and a fourth sub-area (222) arranged axially along the end wall surface (210), and the adjacent third sub-area (221) and the fourth sub-area (222) are used to adjust the pressure distribution at the root of the blade (10). The contours of the region (221) and the fourth sub-region (222) vary in concave and convex to adjust the pressure distribution at the root of the blade (10); the first sub-region (211) corresponds to a first recessed portion (2111) relative to the reference plane, the third sub-region (221) corresponds to a first raised portion (2211) relative to the reference plane, the second sub-region (212) corresponds to a second raised portion (2121) relative to the reference plane, and the fourth sub-region (222) corresponds to a second recessed portion (2221) relative to the reference plane.

2. The gas turbine compressor blade row according to claim 1, characterized in that: The first sub-region (211), the second sub-region (212), the third sub-region (221), and the fourth sub-region (222) respectively define their respective flow channel profiles through the following function curves: T=az 5 +bz 4 +cz 3 +dz 2 +ez 1 +f Wherein, T is the distance from a point on the flow channel profile to the reference plane, z is the axial position coordinate along the end wall surface (200), a, b, c, d, e, and f are polynomial coefficients, and the flow channel profiles of the first sub-region (211), the second sub-region (212), the third sub-region (221), and the fourth sub-region (222) have different polynomial coefficients.

3. The gas turbine compressor blade row according to claim 2, characterized in that: The first sub-region (211) extends axially from the first endpoint along the first flow channel profile to the second endpoint on the end wall surface (200), and the polynomial coefficients a1, b1, c1, d1, e1, and f1 of the function curve of the first flow channel profile are determined by one or more factors including the axial coordinates of the first endpoint and the second endpoint, the distances from the first endpoint and the second endpoint to the reference plane, the tangent slopes at the first endpoint and the second endpoint, and the maximum distance value from the first recessed portion (2111) to the reference plane, the axial coordinates at the maximum distance, and the tangent slope at the maximum distance.

4. The gas turbine compressor blade row according to claim 3, characterized in that: The third sub-region (221) extends axially from the third endpoint along the third flow channel profile to the fourth endpoint on the end wall surface (200), and the polynomial coefficients a3, b3, c3, d3, e3, and f3 of the function curve of the third flow channel profile are determined by one or more factors including the axial coordinates of the third endpoint and the fourth endpoint, the distances from the third endpoint and the fourth endpoint to the reference plane, the tangent slopes at the third endpoint and the fourth endpoint, and the maximum distance value from the first protrusion (2211) to the reference plane, the axial coordinates at the maximum distance, and the tangent slope at the maximum distance.

5. The gas turbine compressor blade row according to claim 4, characterized in that: The second sub-region (212) extends axially from the second endpoint along the second flow channel profile to the fifth endpoint on the end wall surface (200), and the polynomial coefficients a2, b2, c2, d2, e2, and f2 of the function curve of the second flow channel profile are determined by one or more factors including the axial coordinates of the second endpoint and the fifth endpoint, the distances from the second endpoint and the fifth endpoint to the reference plane, the tangent slopes at the second endpoint and the fifth endpoint, and the maximum distance value from the second protrusion (2121) to the reference plane, the axial coordinates at the maximum distance, and the tangent slope at the maximum distance.

6. The gas turbine compressor blade row according to claim 5, characterized in that: The fourth sub-region (222) extends axially from the fourth endpoint along the fourth flow channel profile to the sixth endpoint on the end wall surface (200), and the polynomial coefficients a4, b4, c4, d4, e4, and f4 of the function curve of the fourth flow channel profile are determined by one or more factors including the axial coordinates of the fourth endpoint and the sixth endpoint, the distances from the fourth endpoint and the sixth endpoint to the reference plane, the tangent slopes at the fourth endpoint and the sixth end, and the maximum distance value from the second recessed portion (2221) to the reference plane, the axial coordinates at the maximum distance, and the tangent slope at the maximum distance.

7. The gas turbine compressor blade row according to claim 4, characterized in that: The first end point and the third end point are close to the leading edge of the blade (10).

8. The gas turbine compressor blade row according to claim 4, characterized in that: The second end point and the fourth end point are close to the middle of the blade (10).

9. The gas turbine compressor blade row according to claim 6, characterized in that: The fifth end point and the sixth end point are close to the trailing edge of the blade (10).

10. The gas turbine compressor blade row according to any one of claims 1 to 9, characterized in that: The position where the distance between the first recessed portion (2111) and the reference plane is the largest is located at 10% to 40% of the axial chord length of the blade (10), and the maximum distance between the first recessed portion (2111) and the reference plane is less than 1% of the height of the blade (10).

11. The gas turbine compressor blade row according to any one of claims 1 to 9, characterized in that: The position where the distance between the first protrusion (2211) and the reference plane is the largest is located at 10% to 40% of the axial chord length of the blade (10), and the maximum distance between the first protrusion (2211) and the reference plane is less than 1% of the height of the blade (10).

12. The gas turbine compressor blade row according to any one of claims 1 to 9, characterized in that: The coordinate at which the second protrusion (2121) has the largest distance from the reference plane is located at 60% to 90% of the axial chord length of the blade (10), and the maximum distance from the second protrusion (2121) to the reference plane is less than 1% of the height of the blade (10).

13. The gas turbine compressor blade row according to any one of claims 1 to 9, characterized in that: The position where the second recessed portion (2221) has the largest distance from the reference plane is located at 60% to 90% of the axial chord length of the blade (10), and the maximum distance from the second recessed portion (2221) to the reference plane is less than 1% of the height of the blade (10).

14. The gas turbine compressor blade row according to any one of claims 1 to 9, characterized in that: The junction between the first flow channel area (210) and the second flow channel area (220) is smoothly transitioned to reduce flow loss.

15. The gas turbine compressor blade row according to claim 1, characterized in that: The end wall surface (200) is axially provided with a third flow channel area (230), the third flow channel area (230) extending from the front end of the blade (10) to the leading edge of the blade (10), and the flow channel profile of the third flow channel area (230) along the axial direction of the end wall surface of the mounting member (20) is a straight line.

16. The gas turbine compressor blade row according to claim 1, characterized in that: The end wall surface (200) is axially provided with a fourth flow channel region (240), the fourth flow channel region (240) extending from the trailing edge of the blade (10) to the rear end of the blade (10), and the flow channel profile of the fourth flow channel region (240) along the axial direction of the end wall surface (200) is a straight line.

17. The gas turbine compressor blade row according to claim 1, characterized in that: The end wall surface (200) includes a plurality of flow channel units, and the height difference between the first flow channel area (210) and the second flow channel area (220) in the plurality of flow channel units at the circumferential intersection of the end wall surface (200) changes periodically.

18. The gas turbine compressor blade row according to claim 17, characterized in that: The first flow channel area (210) and the second flow channel area (220) in adjacent flow channel units have different height differences at the circumferential intersection of the end wall surface (200).

19. The gas turbine compressor blade row according to claim 18, characterized in that: The first flow channel area (210) and the second flow channel area (220) in the flow channel units arranged at intervals have the same height difference at the circumferential intersection of the end wall surface (200).

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