Turbine blade, aero-engine, design method and computer readable storage medium

Abstract

The invention discloses a turbine blade, an aero-engine, a design method and a computer readable storage medium, relates to the field of aero-engines, and aims to reduce the exciting force of an upstream guide vane to a downstream movable vane and prolong the service life of the aero-engine. The front edge circle center stacking line of the turbine blade comprises a first curve section, a straight line section and a second curve section which are adjacent in sequence; the first curve section is a root section, and the second curve section is a sharp section; wherein the included angle between a first position M2 which is 40% of the blade height away from the first curve section and the blade height direction is a first anti-bending angle, and the first anti-bending angle is 9-11 degrees. According to the technical scheme, the anti-bending design is adopted, the downward pressure gradient is formed, low-energy fluid is restrained from moving upwards, a shear layer formed by the radial speed difference of the pressure face and the suction face of the blade trailing edge is reduced, the strength and range of trailing edge falling vortexes are restrained from the source, and the exciting force to downstream moving blades is reduced; and meanwhile, the secondary flow influence range of the upstream guide vane is obviously reduced.

Description

Technical Field

[0001] The present invention relates to the field of aeroengines, and particularly to a turbine blade, an aeroengine, a design method, and a computer-readable storage medium. Background Art

[0002] Civil large bypass ratio turbofan engines pursue high thrust-to-weight ratio, low fuel consumption rate, and long service life, which pose higher requirements for the engine efficiency and service life. In order to reduce the component weight, shorten the axial dimension of the engine, reduce the number of parts, and lower the maintenance cost, etc., turbine blades usually adopt high-load design. However, the increase in the aerodynamic load of the blades leads to large profile losses and end region losses, bringing about complex flow problems such as the interaction between the end region secondary flow and the blade surface boundary layer.

[0003] The inventors found that there are at least the following problems in the prior art: The turbine rotor operates in a complex three-dimensional unsteady environment of the upstream guide vane, including the unsteady transport of the unsteady flow of the upstream guide vane wake, passage vortices, trailing edge shear shedding vortices and other streamwise vortex structures. The trailing edge concentrated shedding vortex is both an aggregation area of low-energy fluid and has the spiral characteristics of a vortex. When it acts as an aggregation area of low-energy fluid, it shows the characteristics of a wake, generating a periodic excitation force on the downstream moving blade; when it acts as a vortex, it periodically detaches from the upstream guide vane and acts on the downstream moving blade, bringing vibration problems and affecting the safety and service life of the engine. Summary of the Invention

[0004] The present invention provides a turbine blade, an aeroengine, a design method, and a computer-readable storage medium to reduce the excitation force of the upstream guide vane on the downstream moving blade and improve the service life of the aeroengine.

[0005] An embodiment of the present invention provides a turbine blade. The leading edge center stacking line of the turbine blade includes a first curve segment, a straight line segment, and a second curve segment that are sequentially adjacent; the first curve segment is the root section, and the second curve segment is the tip section;

[0006] Wherein, the included angle between the first position M2 at 40% of the blade height from the first curve segment and the blade height direction is the first reverse bend angle, and the first reverse bend angle is 9° - 11°.

[0007] In some embodiments, the first position M2 forms an obtuse angle with the pressure surface of the turbine blade.

[0008] In some embodiments, the included angle between the second position M5 at 40% of the blade height from the second curve segment and the blade height direction is the second reverse bend angle.

[0009] In some embodiments, the second reverse bend angle is 27° - 29°.

[0010] In some embodiments, the second position M5 forms an obtuse angle with the pressure surface of the turbine blade.

[0011] In some embodiments, at the third position M3 and the fourth position M4 which are at 50% of the blade height from the first curve segment or the second curve segment, the angles with the blade height direction are both 0°.

[0012] An embodiment of the present invention further provides an aeroengine, including the turbine blade provided by any technical solution of the present invention.

[0013] An embodiment of the present invention further provides a turbine blade design method, including the following steps:

[0014] Determine the leading edge center stacking line of the turbine blade; wherein, the leading edge center stacking line of the turbine blade includes a first curve segment, a straight line segment and a second curve segment that are adjacent in sequence; the first curve segment is the root section, and the second curve segment is the tip section;

[0015] Determine that the first reverse bend angle is 9° - 11°, wherein, at the first position M2 which is at 40% of the blade height from the first curve segment, the angle with the blade height direction is the first reverse bend angle.

[0016] In some embodiments, the turbine blade design method further includes the following steps:

[0017] Determine that the second reverse bend angle is 27° - 29°, wherein, at the second position M5 which is at 40% of the blade height from the second curve segment, the angle with the blade height direction is the second reverse bend angle.

[0018] In some embodiments, the turbine blade design method further includes the following steps: at the third position M3 and the fourth position M4 which are at 50% of the blade height from the first curve segment or the second curve segment, the angles with the blade height direction are both 0°.

[0019] An embodiment of the present invention further provides a turbine blade design device, including:

[0020] A memory; and

[0021] A processor coupled to the memory, the processor is configured to execute the turbine blade design method provided by any technical solution of the present invention based on the instructions stored in the memory.

[0022] An embodiment of the present invention further provides a computer-readable storage medium, on which a computer program is stored, and when the program is executed by a processor, it implements the turbine blade design method provided by any technical solution of the present invention.

[0023] The turbine blade provided by the above technical solution, according to the formation and development mechanism of the trailing-edge concentrated shedding vortex and the interference mechanism between the wake and the downstream blade, the trailing-edge concentrated shedding vortex is induced by the velocity gradients with opposite directions on the pressure surface and the suction surface of the blade trailing edge. The through-flow design technology integrating compound bending and torsion is adopted, and the reverse bending design is used to form a downward pressure gradient to inhibit the upward movement of low-energy fluid, reduce the shear layer formed by the radial velocity difference between the pressure surface and the suction surface of the blade trailing edge, suppress the intensity and range of the trailing-edge shedding vortex from the source, reduce the exciting force on the downstream moving blade, and at the same time significantly reduce the influence range of the secondary flow of the upstream guide vane and improve the inflow condition of the downstream moving blade; the wake is restricted by the shape of the blade trailing edge, the installation angle in the end region is reduced, the shape of the trailing edge of the front-row guide vane is adjusted effectively, and a "C"-shaped wake is constructed to form a phase difference with the leading edge of the downstream moving blade, reducing the exciting force of the upstream guide vane on the downstream moving blade and improving the service life of the aero-engine. Brief Description of the Drawings

[0024] The drawings described herein are used to provide a further understanding of the present invention, form a part of this application, and the schematic embodiments of the present invention and their descriptions are used to explain the present invention and do not constitute an improper limitation to the present invention. In the drawings:

[0025] Figure 1 It is a schematic diagram of the formation mechanism of the trailing-edge concentrated shedding vortex of the turbine blade.

[0026] Figure 2a It is a schematic diagram of the structure of a positively inclined designed turbine blade in the related art.

[0027] Figure 2b It is a schematic diagram of the structure of the turbine blade with reverse bending design provided by the embodiment of the present invention.

[0028] Figure 3 It is a dimensionless static pressure comparison diagram of the suction surface of the blade body between the positively inclined (dashed line) in the related art and the turbine blade (solid line) provided by the embodiment of the present invention.

[0029] Figure 4a It is a schematic diagram of the trailing-edge shear layer of a positively inclined turbine blade in the related art.

[0030] Figure 4b It is a schematic diagram of the trailing-edge shear layer of the turbine blade provided by the embodiment of the present invention.

[0031] Figure 5a It is a schematic diagram of the trailing-edge axial vorticity of a positively inclined turbine blade in the related art.

[0032] Figure 5b It is a schematic diagram of the trailing-edge axial vorticity of the turbine blade provided by the embodiment of the present invention.

[0033] Figure 6a It is a schematic diagram of the development of the wake shear layer of a positively inclined turbine blade in the related art.

[0034] Figure 6b Schematic diagram of the development of the wake shear layer of the turbine blade provided by the embodiment of the present invention.

[0035] Figure 7 Schematic diagram of the stacking line of the leading edge center of the guide vane of the turbine blade provided by the embodiment of the present invention.

[0036] Figure 8 Isentropic Mach number distribution on the surface of the turbine blade provided by the embodiment of the present invention.

[0037] Figure 9a Schematic diagram of the outlet trailing edge shape of the positively inclined turbine blade in the related art.

[0038] Figure 9b Schematic diagram of the outlet trailing edge shape of the turbine blade provided by the embodiment of the present invention.

[0039] Figure 10a Schematic diagram of the outlet wake shape of the positively inclined turbine blade in the related art and its positional relationship with the leading edge of the moving blade.

[0040] Figure 10b Schematic diagram of the outlet wake shape of the turbine blade provided by the embodiment of the present invention and its positional relationship with the leading edge of the moving blade.

[0041] Figure 10c Schematic diagram of the effective outlet angle of the turbine blade provided by the embodiment of the present invention.

[0042] Figure 10d Schematic diagram of the installation angle of the turbine blade provided by the embodiment of the present invention.

[0043] Figure 10e Schematic diagram of the throat width of the turbine blade provided by the embodiment of the present invention.

[0044] Figure 10f Schematic diagram of the throat area of the turbine blade provided by the embodiment of the present invention.

[0045] Figure 10g Schematic diagram of the throat width of the turbine blade provided by the embodiment of the present invention.

[0046] Figure 10h Schematic diagram of the installation angle of the turbine blade provided by the embodiment of the present invention.

[0047] Figure 11a Schematic diagram of the outlet wake shape of the guide vane of the positively inclined turbine blade at different times in the related art.

[0048] Figure 11b Schematic diagram of the outlet wake shape of the guide vane of the turbine blade at different times provided by the embodiment of the present invention.

[0049] Figure 12Schematic diagram of the unsteady blade force of the positive-tilted turbine blade on the downstream moving blade in the related art.

[0050] Figure 13 Comparison diagram of the total pressure loss of the positive-tilted turbine blade in the related art and the turbine blade provided by the embodiment of the present invention.

[0051] Figure 14a Schematic diagram of the action range of the secondary flow of the positive-tilted turbine blade in the related art.

[0052] Figure 14b Schematic diagram of the action range of the secondary flow of the turbine blade provided by the embodiment of the present invention. Detailed implementation manners

[0053] The following Figures 1 to 14b elaborates in more detail on the technical solutions provided by the present invention. The description of the exemplary embodiments is merely illustrative and in no way limits the present disclosure and its application or use. The present disclosure can be implemented in many different forms and is not limited to the embodiments described herein. These embodiments are provided to make the present disclosure thorough and complete and to fully convey the scope of the present disclosure to those skilled in the art. It should be noted that: unless otherwise specifically stated, the relative arrangements of components and steps, the compositions of materials, numerical expressions and values set forth in these embodiments should be construed as merely exemplary and not as limitations.

[0054] The "first", "second" and similar terms used in the present disclosure do not denote any order, quantity or importance, but are only used to distinguish different parts. Terms such as "comprising" or "including" mean that the elements before such terms cover the elements listed after such terms, and do not exclude the possibility of also covering other elements.

[0055] In the present disclosure, when it is described that a specific device is located between a first device and a second device, there may or may not be an intermediate device between the specific device and the first device or the second device. When it is described that a specific device is connected to other devices, the specific device may be directly connected to the other devices without an intermediate device, or may not be directly connected to the other devices but have an intermediate device.

[0056] All terms used in the present disclosure (including technical terms or scientific terms) have the same meaning as understood by those of ordinary skill in the art to which the present disclosure pertains, unless otherwise specifically defined. It should also be understood that terms defined in a general dictionary such as should be interpreted as having a meaning consistent with their meaning in the context of the related art and should not be interpreted in an idealized or overly formal sense, unless specifically defined as such herein.

[0057] Technologies, methods, and devices known to those of ordinary skill in the relevant art may not be discussed in detail, but where appropriate, such technologies, methods, and devices shall be regarded as part of the specification. The dimensions of the various parts shown in the drawings are not drawn to actual scale. The same reference numerals are attached to common structural elements or structural elements of the same type in the drawings, and repeated descriptions thereof are appropriately omitted.

[0058] Explanation of the nouns or terms used herein.

[0059] Turbo machinery: A rotary machine that converts kinetic energy into internal energy or internal energy into kinetic energy.

[0060] S2 flow path design: A blade design method that obtains a suitable distribution law of parameters along the spanwise direction by selecting different twisting laws.

[0061] Trailing edge concentrated shedding vortex: Induced by the velocity gradients in opposite directions on the pressure surface and suction surface of the trailing edge of the upstream blade.

[0062] The inventors found that: The turbine rotor blade operates in a complex three-dimensional unsteady environment of the upstream guide vane, including the unsteady transport of flow structures such as the unsteady flow of the upstream guide vane wake, passage vortex, and trailing edge shear shedding vortex. The trailing edge concentrated shedding vortex is both an aggregation area of low-energy fluid and has the spiral characteristics of a vortex. Its formation and development are affected by the radial velocity direction at the trailing edge position and the trailing edge shape. When it acts as an aggregation area of low-energy fluid, it exhibits the characteristics of a wake. According to the formation and development mechanism of the trailing edge concentrated shedding vortex and the interference mechanism between the wake and the downstream blade, the technical solution of the embodiment of the present invention creatively proposes a flow path design technology that combines compound bending and twisting, realizing the control of the upstream guide vane wake and vortex intensity from the source, reducing the excitation force on the downstream moving blade, and at the same time significantly reducing the influence range of the upstream guide vane secondary flow and improving the incoming flow condition of the downstream moving blade; improving performance while increasing the blade life.

[0063] The embodiment of the present invention provides a turbine blade. The leading edge center stacking line of the turbine blade includes a first curve segment S1, a straight line segment S2, and a second curve segment S3 that are sequentially adjacent; the first curve segment is the root section, and the second curve segment is the tip section. Among them, the angle between the first position M2 at 40% of the blade height from the first curve segment and the blade height direction H1 is the first reverse bend angle, and the first reverse bend angle is 9° to 11°. The first reverse bend angle can be, for example, 9°, 10°, or 11°. If the reverse bend angle is too large, it will result in a low reaction degree at the root, resulting in a light load and an increase in root loss. The turbine blade with the above range has better performance.

[0064] In some embodiments, the first position M2 forms an obtuse angle with the pressure surface of the turbine blade.

[0065] In some embodiments, the included angle between the second position M5, which is at 40% of the blade height from the second curve segment, and the blade height direction H2 is the second reverse bend angle.

[0066] In some embodiments, the second reverse bend angle is 27° to 29°. Specifically, the second reverse bend angle can be, for example, 27°, 28°, or 29°.

[0067] In some embodiments, the second position M5 forms an obtuse angle with the pressure surface of the turbine blade.

[0068] In some embodiments, the included angles between the third position M3 and the fourth position M4, which are at 50% of the blade height from the first curve segment or the second curve segment, and the blade height direction are both 0°.

[0069] See Figure 1 , the trailing edge concentrated shedding vortex of the turbine blade is induced by the velocities 2 in the radial directions of the pressure surface and the suction surface of the trailing edge 1 of the upstream blade. To control its intensity and reduce the excitation force on the downstream moving blade, the technical solution of the embodiment of the present invention adopts Figure 2b the reverse bend design shown, that is, the dihedral angle between the blade concave side and the end wall is an obtuse angle, forming a downward pressure gradient, and the radial velocity of the suction surface is inhibited. Compared with Figure 2a the positive inclination design adopted in the related technology in Figure 2b , the technical solution of the embodiment of the present invention adopting the reverse bend design shown has better performance.

[0070] From Figure 3 , it can be known that for the turbine blade adopting the reverse bend design of the embodiment of the present invention, its driving force is significantly smaller than that of the turbine blade adopting the positive inclination design in the conventional technology.

[0071] Comparing Figure 4a and Figure 4b , it can be known that for the turbine blade adopting the reverse bend design in the embodiment of the present invention, the strength and range C of its trailing edge shear layer are significantly smaller than those of the trailing edge shear layer of the turbine blade adopting the conventional positive inclination design, i.e., C'.

[0072] Comparing Figure 5a and Figure 5b , it can be known that compared with the blade adopting the conventional positive inclination design, the turbine blade provided by the embodiment of the present invention significantly weakens the trailing edge concentrated shedding vortex D, and the trailing edge concentrated shedding vortex D' of the blade adopting the conventional positive inclination design is significantly stronger than the technical solution of the embodiment of the present invention.

[0073] Comparing Figure 6a and Figure 6b , it can be known that for the turbine blade provided by the embodiment of the present invention, the shear layer E gradually decays along the downstream and basically disappears before entering the downstream moving blade. The wake of the turbine blade adopting the conventional positive inclination design still has a relatively strong shear layer E' before entering the downstream moving blade.

[0074] See Figure 8 , by using the turbine blade provided by the embodiment of the present invention, the uniform distribution of the radial load of the blade can be realized, and the isentropic Mach number distributions of each section coincide.

[0075] Compare Figure 9a and Figure 9b It can be known that by using the turbine blade provided by the embodiment of the present invention, the shape of the outlet trailing edge of the turbine blade is significantly different from that of the positive-inclined turbine blade in the related art.

[0076] See Figure 10a and Figure 10b , the counterbending design provided by the embodiment of the present invention will lead to an increase in the throat area of the tip section, an increase in the tip reaction degree, and an increase in the tip leakage loss. To reduce the tip leakage loss and weaken the excitation force of the guide vane wake on the downstream moving blade at the same time, the through-flow design technology of integrating compound bending and torsion is adopted. On the basis of the blade with counterbending design, the effective angle of the end region is reduced, the installation angle is constructed to form a "C"-type trailing edge 6, and "C"-type wakes G and H are formed, which form a phase difference with the leading edge of the downstream moving blade. In this embodiment, the distribution of the effective angle and the installation angle can be seen in Figure 10c , Figure 10d , and the "C"-type throat width distribution is obtained Figure 10e , and the optimized blade profile throat surface can be seen in Figure 10f . The schematic diagram of the throat width can be seen in Figure 10g as shown, and the installation angle can be seen in Figure 10h as shown. Figure 10g In Figure 10h , O indicates the throat width, and t is the grid pitch. The arcsine angle α determined by O and t is the outlet effective angle.

[0077] Compare Figure 11a and Figure 11b It can be known that the wakes of the turbine blade provided by the embodiment of the present invention stagger and hit the leading edge of the downstream moving blade at different times, reducing the excitation force of the downstream moving blade. The unsteady calculation results show that the amplitude of the excitation force of the upstream guide vane wake is reduced from 26.5 N to 21.2 N, a decrease of 20%.

[0078] From Figure 12 it can be seen that by using the turbine blade provided by the embodiment of the present invention, the upward movement of low-energy fluid can be inhibited, Figure 12In the embodiment of the present invention, the mid-span loss of the optimized turbine blade is significantly reduced, and the influence range of the secondary flow is significantly narrowed.

[0079] Comparison Figure 13 The solid line and the dashed line in Figure 14a and Figure 14b It can be seen that the solid line represents the turbine blade provided by the embodiment of the present invention, and the dashed line represents the blade of the related technology. The design of the turbine blade in the related technology causes the passage vortex to climb along the blade surface, and the influence range of the secondary flow accounts for 35% of the blade height, forming an obvious high-loss area; while the turbine blade provided by the embodiment of the present invention can inhibit the passage vortex from climbing along the blade surface, and the influence range of the secondary flow only accounts for 12% of the blade height, effectively improving the incoming flow condition of the downstream moving blade.

[0080] According to the formation and development mechanism of the trailing-edge concentrated shedding vortex and the interference mechanism between the wake and the downstream blade, the above technical solution proposes a new full three-dimensional flow-through design technology that combines compound bending and torsion. The anti-bending design is used to inhibit the trailing-edge concentrated shedding vortex, and the flow-through optimization constructs a "C" type wake to form a phase difference with the leading edge of the downstream moving blade, reducing the exciting force of the upstream guide vane on the downstream moving blade. The unsteady calculation results show that the amplitude of the unsteady exciting force felt by the downstream moving blade is reduced by 20%. After being verified by the core engine test, the influence range of the secondary flow of the second-stage guide vane itself is reduced from 35% of the blade height to only 12% of the blade height. While optimizing the aerodynamic performance, vibration reduction design is realized, and the blade life of the high-vortex rotor is improved.

[0081] The embodiment of the present invention also provides an aeroengine, including the turbine blade provided by any technical solution of the present invention.

[0082] The embodiment of the present invention also provides a turbine blade design method, including the following steps:

[0083] First, determine the leading-edge center stacking line of the turbine blade; wherein, the leading-edge center stacking line of the turbine blade includes a first curve segment, a straight line segment and a second curve segment that are sequentially adjacent; the first curve segment is the root section, and the second curve segment is the tip section;

[0084] Secondly, determine that the first anti-bending angle is 9° - 11°, specifically, for example, 9°, 10°, 11°. Among them, the included angle between the first position M2 at 40% of the blade height from the first curve segment and the blade height direction is the first anti-bending angle H1.

[0085] The turbine blade design method further includes the following steps: determine that the second anti-bending angle is 27° - 29°, specifically, for example, 27°, 28°, 29°. Among them, the included angle between the second position M5 at 40% of the blade height from the second curve segment and the blade height direction is the second anti-bending angle H2.

[0086] In some embodiments, the turbine blade design method further includes the following steps: at the third position M3 and the fourth position M4 which are 50% of the blade height away from the first curve segment or the second curve segment, the included angles with the blade height direction are both 0°.

[0087] An embodiment of the present invention also provides a turbine blade design device, including a memory and a processor coupled to the memory. The processor is configured to execute the turbine blade design method in any of the foregoing embodiments based on the instructions stored in the memory.

[0088] The memory may include, for example, a system memory, a fixed non-volatile storage medium, etc. The system memory stores, for example, an operating system, application programs, a boot loader, and other programs.

[0089] An embodiment of the present disclosure also provides a computer-readable storage medium, on which a computer program is stored. When the program is executed by a processor, it implements any of the foregoing turbine blade design methods.

[0090] The processor described herein may include a general-purpose processor, a digital signal processor (DSP), an application-specific integrated circuit (ASIC), a field-programmable gate array (FPGA), or other programmable logic devices, discrete gates or transistor logic, discrete hardware components, or any combination thereof designed to perform the functions described herein. The general-purpose processor may be a microprocessor, but in an alternative, the processor may be any conventional processor, controller, microcontroller, or state machine. The processor may also be implemented as a combination of computing devices, such as a combination of a DSP and a microprocessor, multiple microprocessors, one or more microprocessors cooperating with a DSP core, or any other such configuration.

[0091] A storage medium can be any available medium accessible by a computer. By way of example and not limitation, such computer-readable media can include RAM, ROM, EEPROM, CD-ROM or other optical disk storage, magnetic disk storage or other magnetic storage devices, or any other medium that can be used to carry or store desired program code in the form of instruction or data structures and be accessible by a computer. Any connection is also properly termed a computer-readable medium. For example, if software is transmitted from a web site, server, or other remote source using coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwave, then the coaxial cable, fiber optic cable, twisted pair, DSL, or wireless technologies such as infrared, radio, and microwave are included in the definition of the medium. As used herein, disk and disc include compact disc (CD), laser disc, optical disc, digital versatile disc (DVD), floppy disk and Blu-ray disc, where disk typically reproduces data magnetically, while disc reproduces data optically with a laser. Combinations of the above should also be included within the scope of computer-readable media.

[0092] Those skilled in the art should understand that the method embodiments of the present disclosure can be provided as a method, system, or computer program product. Therefore, the present disclosure can take the form of an entirely hardware embodiment, an entirely software embodiment, or an embodiment combining software and hardware aspects. Moreover, the present disclosure can take the form of a computer program product implemented on one or more computer-usable non-transitory storage media (including but not limited to disk memory, CD-ROM, optical memory, etc.) containing computer-usable program code.

[0093] The present disclosure is described with reference to the flowcharts and / or block diagrams of methods, apparatus (systems), and computer program products according to embodiments of the present invention. It should be understood that each flow and / or block in the flowcharts and / or block diagrams, and combinations of flows and / or blocks in the flowcharts and / or block diagrams, can be implemented by computer program instructions. These computer program instructions can be provided to the processor of a general-purpose computer, special-purpose computer, embedded processor, or other programmable data processing device to produce a machine, such that the instructions executed by the processor of the computer or other programmable data processing device produce means for implementing the functions specified in Figure 1 one or more of the flows or multiple flows and / or blocks Figure 1 one or more of the blocks or multiple blocks.

[0094] These computer program instructions can also be stored in a computer-readable memory that can direct a computer or other programmable data processing device to operate in a particular manner, such that the instructions stored in the computer-readable memory produce a manufacture including instruction means that implement the functions in the flowFigure 1 one process or multiple processes and / or blocks Figure 1 the functions specified in one block or multiple blocks.

[0095] These computer program instructions can also be loaded onto a computer or other programmable data processing device, so that a series of operation steps are executed on the computer or other programmable device to generate a computer-implemented process. Thus, the instructions executed on the computer or other programmable device provide steps for implementing the functions specified in Figure 1 one process or multiple processes and / or blocks Figure 1 one block or multiple blocks.

[0096] In the description of the present invention, it should be understood that the orientation or positional relationship indicated by terms such as "center", "longitudinal", "lateral", "front", "rear", "left", "right", "vertical", "horizontal", "top", "bottom", "inner", "outer", etc. is based on the orientation or positional relationship shown in the drawings. It is only for the convenience of describing the present invention and simplifying the description, rather than indicating or implying that the device or element referred to must have a specific orientation, be constructed and operated in a specific orientation. Therefore, it should not be construed as a limitation on the protected content of the present invention. When the absolute position of the object being described changes, the relative position relationship may also change accordingly.

[0097] In the description of the present invention, where feasible, each technical feature can be combined with other technical features.

[0098] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of the present invention, rather than to limit them; although the present invention has been described in detail with reference to the foregoing embodiments, those of ordinary skill in the art should understand that they can still modify the technical solutions recorded in the foregoing embodiments, or perform equivalent replacements for some of the technical features, but these modifications or replacements do not make the essence of the corresponding technical solutions deviate from the spirit and scope of the technical solutions of the embodiments of the present invention.

Claims

1. A turbine blade, characterized in that, The leading edge center stacking line of the turbine blade includes a first curve segment, a straight line segment, and a second curve segment that are sequentially adjacent; the first curve segment is the root section, and the second curve segment is the tip section; Wherein, the included angle between the first position M2 at 40% of the blade height from the first curve segment and the blade height direction is the first reverse bend angle, and the first reverse bend angle is 9° - 11°.

2. The turbine blade according to claim 1, wherein The first position M2 forms an obtuse angle with the pressure surface of the turbine blade.

3. The turbine blade according to claim 1, characterized in that, The included angle between the second position M5 at 40% of the blade height from the second curve segment and the blade height direction is the second reverse bend angle.

4. The turbine blade according to claim 1, characterized in that, The second reverse bend angle is 27° - 29°.

5. The turbine blade according to claim 1, characterized in that, The second position M5 forms an obtuse angle with the pressure surface of the turbine blade.

6. The turbine blade according to claim 1, characterized in that, The included angles between the third position M3 and the fourth position M4 at 50% of the blade height from the first curve segment or the second curve segment and the blade height direction are both 0°.

7. An aeroengine, characterized in that, Including the turbine blade according to any one of claims 1 - 6.

8. A turbine blade design method, characterized in that, Including the following steps: Determine the leading edge center stacking line of the turbine blade; wherein, the leading edge center stacking line of the turbine blade includes a first curve segment, a straight line segment, and a second curve segment that are sequentially adjacent; the first curve segment is the root section, and the second curve segment is the tip section; Determine that the first reverse bend angle is 9° - 11°, wherein the included angle between the first position M2 at 40% of the blade height from the first curve segment and the blade height direction is the first reverse bend angle.

9. The turbine blade design method according to claim 8, wherein Also include the following steps: Determine that the second reverse bend angle is 27° - 29°, wherein the included angle between the second position M5 at 40% of the blade height from the second curve segment and the blade height direction is the second reverse bend angle.

10. The turbine blade design method according to claim 8, characterized in that, Also include the following steps: The included angles between the third position M3 and the fourth position M4 at 50% of the blade height from the first curve segment or the second curve segment and the blade height direction are both 0°.

11. A turbine blade design device, characterized in that, Including: A memory; And A processor coupled to the memory, the processor being configured to execute the turbine blade design method according to any one of claims 8 - 10 based on instructions stored in the memory.

12. A computer-readable storage medium, characterized in that, On which a computer program is stored, and when the program is executed by the processor, it implements the turbine blade design method according to any one of claims 8 - 10.

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