Turbine compressor blade path based on S3 surface and its construction method

Abstract

The present invention discloses a turbine compressor blade channel based on S3 surfaces and a construction method thereof. In the method, a three-dimensional geometric model of the turbine compressor is established based on the turbine compressor geometric data, the internal flow field is calculated based on the three-dimensional geometric model, and the near-wall streamlines of the turbine compressor are extracted; the geometric data of multiple S3 surfaces along the flow direction are extracted based on the turbine compressor geometric data, and the multiple S3 surfaces and the leading edge surface and the trailing edge surface jointly define the blade channel; the multiple S3 surfaces and the leading edge surface and the trailing edge surface are geometrically parameterized, and the parameterized curve is lofted along the near-wall streamline direction to generate the three-dimensional geometry of the blade channel, and the three-dimensional geometry of the blade channel is optimized based on computational fluid dynamics to determine the optimal structure of the blade channel.

Description

Technical Field

[0001] The present invention belongs to the field of turbine machinery pneumatic technology, in particular to a turbine compressor blade passage based on an S3 surface and a construction method thereof. Background Art

[0002] The turbine compressor is one of the core components of aircraft engines, gas turbines and industrial compression systems, and its aerodynamic performance has a significant impact on the overall performance of the machine. Higher loads, higher efficiency and a wider range of stable operating conditions have always been the goals pursued by compressor designers. However, breaking through the load limit will make the internal flow field of the compressor more complex, posing a huge challenge to the design of compressor stabilization and efficiency improvement. Taking the axial flow compressor as an example, its end wall flow loss is closely related to the interaction between the blades and the boundary layer in the end area, which can account for about 30% of the total flow loss and is one of the key constraints on improving the aerodynamic performance of the compressor. Therefore, the refined organization and control of the end area flow is an important starting point for achieving compressor stabilization and efficiency improvement.

[0003] Conventional compressor aerodynamic design methods generate three-dimensional blade geometry based on the concepts of "elementary blade profile" and "radial stacking", and have been widely used in turbine compressor aerodynamic design. However, this method has the inherent disadvantage of forcibly separating the blade and the end region, making it difficult to achieve high-order smooth fusion of the blade and end region geometry, which brings inconvenience to the refined organization and regulation of the end region flow. Although many works have carried out local modification of the geometry of the intersection of the blade and the end region (corner area), since it does not involve the coordinated adjustment of the blade and end wall geometry, it is impossible to fundamentally improve the radial creep of the blade boundary layer and the lateral creep of the end wall boundary layer, which is also not conducive to reducing the end wall flow loss.

[0004] Existing methods for analyzing and evaluating third-type flow surfaces in turbomachinery secondary flows and their design suffer from the following shortcomings: They fail to address the geometric parametric modeling of S3 surfaces, lack flexible control over them, and are unable to achieve high-order smooth fusion of the blade and tip regions and control the flow field in the tip regions. Second, they rely solely on a two-dimensional description of the S3 surface and fail to address the modeling of three-dimensional blade passages, thus failing to guide the generation of complete three-dimensional blade passages, severely hindering their practical engineering applications. While the design method for integrating impeller blades and endwalls mentions localized geometry modification of S3 surface angles along the flow direction, it fails to propose a comprehensive control scheme for the compressor flow passage and a comprehensive design and generation method for the flow passage.

[0005] The above information disclosed in this Background section is only for enhancement of understanding of the background of the invention and therefore it may contain information that does not form the prior art that is already known in this country to a person of ordinary skill in the art. Summary of the Invention

[0006] In response to the problems existing in the prior art, the present invention proposes a turbine compressor blade path based on the S3 surface and a construction method thereof, which solves the problem that conventional compressor design methods are difficult to achieve high-order smooth fusion of the blade and end area and the flow organization in the end area is poor.

[0007] The object of the present invention is achieved through the following technical solutions: a method for constructing a turbine compressor blade path based on an S3 surface comprises:

[0008] Step 1: Establish a three-dimensional geometric model of the turbine compressor based on the turbine compressor geometric data. The three-dimensional geometric model includes a hub, a leading edge surface and a trailing edge surface located on the hub and arranged in a front-to-rear manner along the flow direction, and a pressure surface and a suction surface extending in the flow direction. The pressure surface and the suction surface have near-wall streamlines. The internal flow field is calculated based on the three-dimensional geometric model to extract the near-wall streamlines of the turbine compressor.

[0009] Step 2: The S1 flow surface is a flow surface formed by the streamlines of each fluid particle on the same arc centered on the rotation axis, which can be approximated as a surface of revolution. The S2 flow surface is a flow surface formed by the streamlines of each fluid particle on the same radial line, which can be approximated as a geometric center plane. The S3 surface is a third type of surface orthogonal to the S1 and S2 flow surfaces. Based on the turbine compressor geometric data, geometric data of multiple S3 surfaces along the flow direction are extracted. The multiple S3 surfaces, the leading edge surface, and the trailing edge surface jointly define the blade path.

[0010] Step 3, geometrically parameterizing the plurality of S3 surfaces and the leading edge surface and the trailing edge surface, which includes:

[0011] Step 3.1: geometrically parameterize the curves formed by the leading edge line of the leading edge surface, the trailing edge line of the trailing edge surface, and the wheel hub. The geometrically parameterized leading edge line extends forward, and the trailing edge line extends backward so that the leading edge line and the trailing edge line respectively transition smoothly with the wheel hub surface.

[0012] Step 3.2: Fit multiple S3 surface suction surface-hub-pressure surface curves to ensure a smooth transition between the suction surface, hub, and pressure surface of the blade path, and then geometrically parameterize the wheel cover side curve.

[0013] Step 4: Loft the parameterized curve along the direction of the near-wall streamline to generate the three-dimensional geometry of the blade path.

[0014] Step 5: Optimizing the three-dimensional geometry of the blade channel based on computational fluid dynamics to determine the optimal structure of the blade channel.

[0015] In the turbine compressor blade path construction method based on the S3 surface, in the step 3.1, after geometrically parameterizing the curve composed of the leading edge line of the leading edge surface, the trailing edge line of the trailing edge surface and the hub, the hub and wheel cover parts in the leading edge surface and the trailing edge surface are then geometrically parameterized.

[0016] In the turbine compressor blade path construction method based on the S3 surface, step 3.2 is to fit multiple S3 surface suction surface-hub-pressure surface curves and then geometrically parameterize the wheel cover side curve.

[0017] In the turbine compressor blade path construction method based on S3 surfaces, a fitting curve having high-order smooth characteristics and capable of generating a curve from a number of control points is used to geometrically parameterize the multiple S3 surfaces and the leading edge surface and the trailing edge surface.

[0018] In the turbine compressor blade path construction method based on the S3 surface, the fitting curve can be a NURBS curve, a B-spline or a Bezier curve.

[0019] In the turbine compressor blade path construction method based on the S3 surface, the parameterized curve includes at least two streamlines along the near-wall streamlines, one on the suction side and the other on the pressure side of the blade.

[0020] In the turbine compressor blade channel construction method based on the S3 surface, the optimal structure of the blade channel fully optimizes the blade-corner area-end area-wheel cover of the entire compressor blade channel. During the optimization process, the area of ​​the S3 surface remains unchanged to maintain consistent flow capacity.

[0021] A turbine compressor blade path is prepared according to the turbine compressor blade path construction method based on the S3 surface.

[0022] In the turbine compressor blade path based on the S3 surface, the turbine compressor blade path is an axial flow compressor blade path.

[0023] Compared with the existing technology, the present invention has the following advantages: the existing blade shaping and corner area control method is a traditional blade shaping design method based on the primitive blade profile + radial stacking. This corner area structural shaping method forcibly separates the three connected parts of the blade-corner area-end area. It is difficult to achieve high-order smooth fusion of the blade and the end wall by designing the corner area alone, which limits the upper limit of the development of corner area shaping technology. The present invention shapes the blade path along the near-wall streamline, the leading edge surface, several S3 surfaces and the trailing edge surface. The high-order continuity of the curves of several S3 surfaces ensures the high-order smoothness of the blade and the end wall. The high-order continuity of the leading and trailing edge surfaces and the hub curved surface ensures the high-order smoothness of the leading and trailing edges of the blade and the end wall. The control of the S3 surface area remains unchanged to ensure the consistency of the flow capacity of the new blade path. Compared with the traditional blade path design method, this method ensures a high-order smooth transition between the blade and the end wall, and realizes the refined control of the flow in the corner area of ​​the turbine compressor. The present invention can realize the overall geometric design of the compressor including blades-corner area-hub-wheel cover. After the blade path is redesigned, the blade shape is changed and has the geometric characteristics of blade height fusion, asymmetric end wall and asymmetric wheel cover, providing a new idea for improving the design method of turbine compressor. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Various other advantages and benefits of the present invention will become apparent to those skilled in the art upon reading the detailed description of the preferred embodiments below. The accompanying drawings are intended only to illustrate preferred embodiments and are not to be construed as limiting the present invention. It should be understood that the drawings described below are merely examples of the present invention, and that those skilled in the art will be able to derive other drawings from these drawings without inventive effort. Throughout the drawings, identical reference numerals are used to denote identical components.

[0025] In the attached figure:

[0026] Figure 1 is a schematic diagram of the original geometric model of Rotor 37 according to one embodiment of the present invention;

[0027] Figure 2 2. It is a schematic diagram showing the effect of a method for extracting leaf path S3 surface data according to an embodiment of the present invention;

[0028] Figure 3 is a schematic diagram of a parameterization method for a leading / edge surface according to an embodiment of the present invention;

[0029] Figure 4 is a schematic diagram of a parameterization method for an intermediate S3 surface according to an embodiment of the present invention;

[0030] Figure 5 is a schematic diagram of blade path geometry reconstruction according to one embodiment of the present invention;

[0031] FIG6(a) and FIG6(b) are schematic diagrams showing a geometric comparison between a prototype machine and an optimized machine according to one embodiment of the present invention, wherein FIG6(a) shows the original geometry of Rotor 37, and FIG6(b) shows the optimized geometry of Rotor 37;

[0032] FIG7(a) and FIG7(b) are schematic diagrams comparing the aerodynamic performance of a prototype and an optimized machine according to one embodiment of the present invention, wherein FIG7(a) is a pressure ratio versus flow characteristic curve, and FIG7(b) is an efficiency versus flow characteristic curve;

[0033] FIG8( a ) and FIG8( b ) are schematic diagrams comparing the flow fields of a prototype machine and an optimized machine according to an embodiment of the present invention, wherein FIG8( a ) is the original geometric static pressure distribution, and FIG8( b ) is the optimized modified geometric static pressure distribution.

[0034] The present invention will be further explained below with reference to the accompanying drawings and embodiments. DETAILED DESCRIPTION

[0035] The following will refer to the attached Figures 1 to 8(b)Specific embodiments of the present invention will now be described in greater detail. Although specific embodiments of the present invention are shown in the accompanying drawings, it should be understood that the present invention may be implemented in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided to facilitate a more thorough understanding of the present invention and to fully convey the scope of the present invention to those skilled in the art.

[0036] It should be noted that certain words are used in the specification and claims to refer to specific components. Those skilled in the art should understand that technicians may use different nouns to refer to the same component. This specification and claims do not use the difference in nouns as a way to distinguish components, but use the difference in the functions of the components as the criterion for distinction. As mentioned throughout the specification and claims, "including" or "comprising" is an open term, so it should be interpreted as "including but not limited to". The subsequent description of the specification is a preferred embodiment of the present invention, but the description is based on the general principles of the specification and is not intended to limit the scope of the invention. The scope of protection of the present invention shall be as defined in the attached claims.

[0037] To facilitate understanding of the embodiments of the present invention, further explanation will be given below using specific embodiments as examples in conjunction with the accompanying drawings, and the accompanying drawings do not constitute a limitation on the embodiments of the present invention.

[0038] For better understanding, Figures 1 to 8(b) As shown in FIG, the turbine compressor blade path construction method based on the S3 surface includes:

[0039] Step 1: Establish a three-dimensional geometric model of the turbine compressor based on the turbine compressor geometric data. The three-dimensional geometric model includes a hub, a leading edge surface and a trailing edge surface located on the hub and arranged in a front-to-rear manner along the flow direction, and a pressure surface and a suction surface extending in the flow direction. The pressure surface and the suction surface have near-wall streamlines. The internal flow field is calculated based on the three-dimensional geometric model to extract the near-wall streamlines of the turbine compressor.

[0040] Step 2: Surface S1 is a flow surface formed by streamlines of fluid particles on the same arc centered on the rotation axis; surface S2 is a flow surface formed by streamlines of fluid particles on the same radial line; surface S3 is a third type of surface orthogonal to surface S1 and surface S2. Geometric data of multiple S3 surfaces along the flow direction are extracted based on the turbine compressor geometric data. The multiple S3 surfaces, the leading edge surface, and the trailing edge surface jointly define the blade path;

[0041] Step 3, geometrically parameterizing the plurality of S3 surfaces and the leading edge surface and the trailing edge surface, which includes:

[0042] Step 3.1: geometrically parameterize the curves formed by the leading edge line of the leading edge surface, the trailing edge line of the trailing edge surface, and the wheel hub. The geometrically parameterized leading edge line extends forward, and the trailing edge line extends backward so that the leading edge line and the trailing edge line respectively transition smoothly with the wheel hub surface.

[0043] Step 3.2: Fit multiple S3 surface suction surface-hub-pressure surface curves to ensure a smooth transition between the suction surface, hub, and pressure surface of the blade path, and then geometrically parameterize the wheel cover side curve.

[0044] Step 4: Loft the parameterized curve along the direction of the near-wall streamline to generate the three-dimensional geometry of the blade path.

[0045] Step 5: Optimizing the three-dimensional geometry of the blade channel based on computational fluid dynamics to determine the optimal structure of the blade channel.

[0046] In a preferred embodiment of the turbine compressor blade path construction method based on S3 surfaces, geometric data of three S3 surfaces along the flow direction are extracted based on the turbine compressor geometric data, and the three S3 surfaces and the leading edge surface and the trailing edge surface jointly define the blade path.

[0047] In a preferred embodiment of the turbine compressor blade path construction method based on the S3 surface, in the step 3.1, after geometrically parameterizing the curve composed of the leading edge line of the leading edge surface, the trailing edge line of the trailing edge surface and the hub, the hub and wheel cover parts in the leading edge surface and the trailing edge surface are geometrically parameterized.

[0048] In a preferred embodiment of the turbine compressor blade path construction method based on the S3 surface, step 3.2 is to geometrically parameterize the wheel cover side curve after fitting multiple S3 surface suction surface-hub-pressure surface curves.

[0049] In a preferred embodiment of the turbine compressor blade path construction method based on S3 surfaces, a fitting curve having high-order smooth features and capable of generating curves from a number of control points is used to geometrically parameterize the multiple S3 surfaces and leading edge surfaces and trailing edge surfaces.

[0050] In a preferred embodiment of the turbine compressor blade path construction method based on the S3 surface, the fitting curve is a NURBS curve, a B-spline or a Bezier curve.

[0051] In a preferred embodiment of the turbine compressor blade path construction method based on the S3 surface, the parameterized curve includes at least two streamlines along the near-wall streamlines, one on the suction side and the other on the pressure side of the blade.

[0052] In the preferred embodiment of the turbine compressor blade channel construction method based on the S3 surface, the optimal structure of the blade channel fully optimizes the blade-corner area-end area-wheel cover of the entire compressor blade channel. During the optimization process, the area of ​​the S3 surface remains unchanged to maintain consistent flow capacity.

[0053] In one embodiment, the method includes using the leading / trailing edge surface and several S3 surfaces to jointly control the blade channel. In order to achieve a high-order smooth transition between the blade channel and the hub during parameterization, the leading / trailing edge surface uses a NURBS curve to fit the curve composed of the leading / trailing edge and the hub, and the geometry after fitting has the geometric characteristics of the leading / trailing edge strips; in the middle S3 surface, the NURBS curve directly fits the curve composed of the suction surface-hub-pressure surface side of the blade channel, and the geometry within the S3 surface after fitting has the geometric characteristics of the blade body fusion. The flow channel geometry is generated by lofting using the near-wall streamline as the guide line, and the modification optimization is completed after the blade channel is parameterized. During the optimization process, the position of the control point on the hub side of the S3 surface is adjusted to control the area of ​​the S3 surface unchanged, so as to ensure the consistency of the compressor flow capacity after the modification optimization. The parameterization and optimization modification of Rotor37 was completed, and the stable operating range of the designed new compressor was widened by 94%, and the efficiency at the highest efficiency point was increased by 0.3%.

[0054] In one embodiment, a method for constructing a turbine compressor blade path based on S3 surface lofting includes the following steps:

[0055] Step 1: Calculate the internal flow field of the original turbine compressor and extract the near-wall streamlines of the original compressor;

[0056] Step 2: Surface S1 is the surface of revolution, surface S2 is approximately the geometric center plane of the flow path, and surface S3 is orthogonal to surfaces S1 and S2. Based on the original blade path data of the turbine compressor, the geometric data of the leading / trailing edge surfaces and several blade paths on surface S3 are extracted;

[0057] Step 3: geometric parameterization of the blade path geometry at different axial positions extracted in step 2. The specific method is as follows:

[0058] In step 3.1, use NURBS curves to parameterize the leading / trailing edge surfaces. Parameterize the curves formed by the leading / trailing edge lines and the wheel hub. After parameterization, the leading edge lines extend forward, and the trailing edge lines extend backward, achieving a high-order smooth transition between the leading / trailing edge lines and the wheel hub surfaces. Next, use NURBS curves to complete the parameterization of the wheel hub and wheel cover geometry within the leading / trailing edge surfaces.

[0059] In step 3.2, a NURBS curve is used to directly fit several suction surface-hub-pressure surface curves within the S3 surface. Due to the high-order smoothness of the NURBS curve, the high-order smoothness of the curve within the S3 surface of the blade ensures a smooth transition between the suction surface, hub and pressure surface of the blade. The NURBS curve is used to parameterize the wheel cover side curve. The fitting curve is not limited to NURBS curves, but can also be a curve with high-order smooth characteristics such as B-spline and Bezier, which can be generated by several control points. The leading / trailing edge strips generated during the parameterization process are relatively small and will not significantly affect the flow field and compressor performance.

[0060] Step 4: Based on the parameterized curve obtained in Step 3, the parameterized curve is lofted along the near-wall streamlines to generate the 3D blade runner geometry. The near-wall streamlines include at least two streamlines on the suction and pressure sides of the blade, achieving a smooth transition between the leading and trailing edges of the blade runner. The blade runner surface and the hub surface are smoothly integrated at a high level, creating a geometric structure that integrates the blade strip and the blade body.

[0061] In step 5, the parametric research method of computational fluid dynamics tools is used to optimize the new flow channel obtained in step 4 and determine the optimal structure of the blade channel. During the blade channel optimization process, the side curves of the hub and the wheel cover can be changed, which can achieve full optimization of the entire compressor blade channel from blade to corner area to end area to wheel cover. During the optimization and modification process, the S3 surface area is controlled to remain unchanged to maintain consistent flow capacity.

[0062] In one embodiment, this example redesigned the NASA Rotor 37 axial compressor blade path according to the method described in the Summary of the Invention, and the effectiveness was verified using numerical simulation. The aerodynamic parameters of this example are as follows: inlet total pressure 101325 Pa, total temperature 288.15 K, and design parameters as shown in Table 1.

[0063] Table 1 NASA Rotor37 design parameters

[0064]

[0065] The specific construction process is:

[0066] In step 1, a three-dimensional geometric model of the compressor was established based on the original Rotor37 geometric data, the aerodynamic performance calculation of the original Rotor37 blade was completed, and the near-wall streamlines were extracted.

[0067] Step 2: Based on step 1, the S1 flow surface is the flow surface formed by the streamlines of each fluid particle on the same arc with the rotation axis as the center, which can be simplified as a rotation surface. The S2 flow surface is the flow surface formed by the streamlines of each fluid particle on the same radial line, which can be simplified as the geometric center plane of the flow channel. The S3 surface is a third type of surface orthogonal to the S1 and S2 flow surfaces. According to the definition of the S3 surface, the geometric data of the three S3 surfaces along the flow direction are extracted and defined as S3_1~S3_3. Figure 2 As shown, the three S3 surfaces, the leading edge surface and the trailing edge surface jointly define the blade path.

[0068] Step 3: Building on the work done in Step 2, the Rotor 37 blade geometry was parameterized. To achieve a smooth, high-order transition between the blade and the hub at the leading and trailing edges, the curves of the leading and trailing edges and the hub were parameterized together. This parameterization gave the blade the geometric characteristics of a leading and trailing strip, extending forward at the leading edge and backward at the trailing edge. NURBS curves were then used to parameterize the hub and shroud sections of the leading and trailing edge surfaces.

[0069] The parameterization method of S3_2 surface is as follows Figure 4 As shown in the figure, the parameterization method for surfaces S3_1 and S3_3 is the same as that for S3_2. A single NURBS curve is used to directly parameterize the pressure-hub-suction surface curve. Due to the high-order smoothness of NURBS curves, the control curve within surface S3_2 after parameterization has high-order smoothness between the suction, hub, and pressure surfaces. Subsequently, a separate NURBS curve is used to parameterize the wheel cover side curve.

[0070] Step 4: Based on step 3, the 3D geometric reconstruction of the blade path is completed. The 3D blade path reconstruction scheme is as follows: Figure 5 As shown in the figure, the parameterized rear curves of the leading / trailing edge surfaces and several S3 surfaces control the blade path along the axial direction. The near-wall streamline is used as the guide line to control the blade path, which ensures a smooth transition of the blade path at the leading / trailing edge and realizes a smooth transition of the blade path between several S3 surfaces. Finally, a blade path geometry with a seamless integration of the suction surface, hub, and pressure surface is generated, with a total of 59 control variables.

[0071] Step 5, based on step 4, the Rotor37 blade channel is modified and optimized. The advantage of this blade channel control method is that the generated compressor has a smooth transition between the suction surface, hub surface and pressure surface. Therefore, in this example, CFD numerical optimization is only completed for the Rotor 37 corner area structure, and the hub control point is controlled to ensure that the S3 surface area remains unchanged before and after the modification. The performance of the optimized compressor is compared with the original one as shown in Figure 6(a) and Figure 6(b). The numerical simulation results are shown in Figure 7(a) and Figure 7(b). The maximum efficiency of the modified and optimized compressor under this method is improved by 0.3%, and the stable operating range is widened by 94%. The comparative analysis of the flow under near-stall conditions is shown in Figure 8(a) and Figure 8(b). After optimization, the flow separation area of ​​the compressor is greatly reduced, and the overall flow performance is improved.

[0072] The blade channel control method of the present invention can also modify the wheel cover, suction surface and pressure surface structures to achieve full optimization of the three flow channels.

[0073] The embodiment of the present invention adopts NURBS fitting, and other B-spline, Bezier and the like having high-order smooth characteristics can also be adopted to fit a curve controlled by a number of control points.

[0074] A turbine compressor blade path is prepared according to the turbine compressor blade path construction method based on the S3 surface.

[0075] In a preferred embodiment of the turbine compressor blade passage, the turbine compressor blade passage is an axial flow compressor blade passage.

[0076] Although the embodiments of the present invention have been described above with reference to the accompanying drawings, the present invention is not limited to the above-mentioned specific embodiments and application fields. The above-mentioned specific embodiments are merely illustrative and instructive, and are not restrictive. A person skilled in the art, guided by this specification and without departing from the scope of protection of the claims of the present invention, may also devise various forms, all of which fall within the scope of protection of the present invention.

Claims

1. A method for constructing a turbine compressor blade path based on an S3 surface, characterized in that: It includes the following steps, Step 1: Establish a three-dimensional geometric model of the turbine compressor based on the turbine compressor geometric data. The three-dimensional geometric model includes a hub, a leading edge surface and a trailing edge surface located on the hub and arranged in a front-to-rear manner along the flow direction, and a pressure surface and a suction surface extending in the flow direction. The pressure surface and the suction surface have near-wall streamlines. The internal flow field is calculated based on the three-dimensional geometric model to extract the near-wall streamlines of the turbine compressor. Step 2: The S1 flow surface is a flow surface formed by the streamlines of each fluid particle on the same arc centered on the rotation axis. The S2 flow surface is a flow surface formed by the streamlines of each fluid particle on the same radial line. The S3 surface is a third type of surface orthogonal to the S1 and S2 flow surfaces. Based on the turbine compressor geometry data, the geometric data of multiple S3 surfaces along the flow direction are extracted. The multiple S3 surfaces, the leading edge surface, and the trailing edge surface jointly define the blade path. Step 3, geometrically parameterizing the multiple S3 surfaces and the leading edge surface and the trailing edge surface; Step 4: Loft the parameterized curve along the direction of the near-wall streamline to generate the three-dimensional geometry of the blade path; Step 5: Optimizing the three-dimensional geometry of the blade channel based on computational fluid dynamics to determine the optimal structure of the blade channel.

2. The turbine compressor blade path construction method based on the S3 surface according to claim 1, wherein: Preferably, in step 3, after geometrically parameterizing the curve formed by the leading edge line of the leading edge surface, the trailing edge line of the trailing edge surface and the wheel hub, the wheel hub and wheel cover parts in the leading edge surface and the trailing edge surface are geometrically parameterized.

3. The turbine compressor blade path construction method based on the S3 surface according to claim 1, wherein: In step 3, the wheel cover side curve is geometrically parameterized after fitting multiple S3 surface suction surface-hub-pressure surface curves.

4. The turbine compressor blade path construction method based on the S3 surface according to claim 1, wherein: The plurality of S3 surfaces and the leading edge surface and the trailing edge surface are geometrically parameterized using a fitting curve having a high-order smooth feature and capable of generating a curve from a number of control points.

5. The turbine compressor blade path construction method based on the S3 surface according to claim 4, wherein: The fitting curve is a NURBS curve, a B-spline, or a Bezier curve.

6. The turbine compressor blade path construction method based on the S3 surface according to claim 1, wherein: The parameterized curve includes at least two streamlines along the near-wall streamlines, one on the suction side and the other on the pressure side of the blade.

7. The turbine compressor blade path construction method based on the S3 surface according to claim 1, wherein: The optimal structure of the blade channel fully optimizes the blade-corner area-end area-wheel cover of the entire compressor blade channel. During the optimization process, the area of ​​S3 surface remains unchanged to maintain consistent flow capacity.

8. A turbine compressor blade path, characterized in that: It is prepared according to the turbine compressor blade path construction method based on the S3 surface according to any one of claims 1-7.

9. The turbine compressor blade passage based on the S3 surface according to claim 8, wherein: The turbine compressor blade path is an axial flow compressor blade path.

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