Design method of titanium-aluminum power turbine blades and aero-engines
Patent Information
- Authority / Receiving Office
- CN · China
- Patent Type
- Applications(China)
- Current Assignee / Owner
- Filing Date
- 2026-04-03
- Publication Date
- 2026-08-11
AI Technical Summary
[0004]本发明提供了一种钛铝动力涡轮工作叶片设计方法及航空发动机，以解决现有技术中为减重而采取的增加叶片载荷或减薄叶型所导致的气动效率降低、工艺难度大、产品合格率低，以及现有设计方法未充分考虑钛铝材料特性而导致的结构脆性风险等技术问题
本钛铝动力涡轮工作叶片设计方法首先对原型高温合金涡轮叶片开展加工工艺初步分析，从加工可行性、提升产品加工合格率和降低产品加工成本等角度给出原型涡轮叶片工艺气泡图，再对原型动力涡轮工作叶片进行几何特征分析，确定叶型设计几何约束条件，考虑涡轮叶片上下游匹配关系和封严引气对优化叶片进行主要状态点三维仿真联算，通过多轮迭代优化至获得优化钛铝工作叶片的气动性能满足发动机要求，对优化钛铝涡轮工作叶片进行叶冠、叶身、榫头的细节结构优化设计，根据叶片温度场和气动载荷场等输入参数开展强度、振动和寿命计算分析，若不满足需求，返回迭代优化，本设计方法可直接用于高性能航空燃气涡轴/桨发动机，与原型高温合金叶片相比，不用采用增加叶片载荷减少叶片数实现叶片减重，钛铝叶片设计以原型叶片为基础，调整最小几何尺寸至满足钛铝叶片工艺需求即可；在保证叶片数和喉部面积不变条件下，不用采用减薄叶型设计实现减重，可沿用传统高温合金涡轮叶片设计经验，如保证叶型安装角变化、尖根面积比变化等；同时本设计方法结合了多专业的迭代优化设计，在气动性能、叶片结构设计、强度振动寿命和加工工艺的实现性均满足要求的情况下，有效减重，提高发动机的功重比，改进设计的钛铝动力涡轮工作叶片重量减轻约50%，在满足发动机涡轮效率的情况下，有效提高了发动机的功重比，降低了全包线范围内的整机耗油率。
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Abstract
Description
Technical Field
[0001] This invention relates to the field of aero-engine technology, and in particular, to a design method for titanium-aluminum power turbine blades. Furthermore, this invention also relates to an aero-engine incorporating the aforementioned titanium-aluminum power turbine blade design method. Background Technology
[0002] With increasingly stringent performance requirements for aero gas turbine / turboprop engines, weight has become a significant factor limiting engine performance improvements. Reducing weight can significantly improve the engine's power-to-weight ratio, while also lightening the aircraft's load, ensuring better maneuverability, reducing fuel consumption, and lowering emissions.
[0003] As a core component for the power output of advanced high-power aero-gas turbine / gas turbine propeller engines, the blades of the power turbine not only bear very high centrifugal loads, thermal loads, and aerodynamic loads, but also require long service life and high reliability under these harsh operating conditions. To achieve the goals of high performance and light weight in power turbines, existing technologies typically employ two methods: First, increasing blade load to reduce the number of blades and thus reduce blade weight. However, excessively increasing the blade load can increase the lateral pressure gradient between blades, enhance secondary flow losses, and the change in the number of blades can also introduce new vibration problems to downstream blades. Second, without changing the number of blades, reducing the blade profile thickness. However, excessively thin blades can affect the strength of the crowned working blades themselves, and also lead to a lower turbine blade casting yield. Summary of the Invention
[0004] This invention provides a design method for titanium-aluminum power turbine blades and an aero-engine, which solves the technical problems in the prior art, such as reduced aerodynamic efficiency, high process difficulty, low product qualification rate caused by increasing blade load or thinning the blade profile in order to reduce weight, and structural brittleness risk caused by the failure of the existing design method to fully consider the characteristics of titanium-aluminum materials.
[0005] According to one aspect of the present invention, a method for designing titanium-aluminum power turbine blades is provided, the method comprising: S1. Conduct a preliminary analysis of the processing technology of the prototype high-temperature alloy turbine blade and provide a bubble diagram of the prototype turbine blade process. S2. Perform geometric feature analysis on the prototype power turbine working blades to determine the geometric constraints for blade design. S3. Based on the upstream and downstream matching relationship of turbine blades and the sealing and bleed air, perform three-dimensional simulation and joint calculation of the main state points of the optimized blades, and perform multiple rounds of iterative optimization until the aerodynamic performance of the optimized titanium-aluminum working blades meets the engine requirements. S4. Optimize the detailed structure design of the blade crown, blade body, and tenon of the optimized titanium-aluminum turbine working blades; S5. Perform strength, vibration and life calculation and analysis based on input parameters such as blade temperature field and aerodynamic load field. If the requirements are not met, proceed to step S2 for iterative optimization.
[0006] As a further improvement to the above technical solution, step S2 also includes: without changing the number of blades and meeting the preset size constraints, based on the prototype blade and combined with the titanium-aluminum turbine blade processing technology, improving and optimizing the blade trailing edge diameter and / or the radial distribution of the blade mounting angle and / or the blade tip root area ratio parameters.
[0007] As a further improvement to the above technical solution, step S3 includes: performing three-dimensional joint calculations on the prototype blade and the optimized blade respectively. During the simulation calculation, the mesh division of the optimized blade adopts the mesh template of the prototype blade, and the sealing and bleed settings remain the same.
[0008] As a further improvement to the above technical solution, step S3 includes: during the performance parameter comparison process, the turbine expansion ratio of the optimized blade and the prototype blade are consistent, the throat area of the optimized blade is adjusted to be the same as that of the prototype blade, and the performance parameters and flow field structure of the optimized blade and the prototype blade are compared.
[0009] As a further improvement to the above technical solution, step S4 also includes: after the design of the three-dimensional structural model of the titanium-aluminum power turbine working blade is completed, the requirements for temperature field calculation, strength, vibration and life calculation of the main state points are put forward for downstream heat transfer and strength vibration life.
[0010] As a further improvement to the above technical solution, the blade includes a serrated crown, double radial teeth, blade body, lower edge plate, parallelogram extension root, and double dovetail tenon.
[0011] As a further improvement to the above technical solution, step S4 also includes: the minimum geometric dimension of the tenon of the blade is 1mm, and the minimum joint dimension of the blade crown is 1mm.
[0012] As a further improvement to the above technical solution, step S2 also includes: the key styling parameters of the blade, including the leading edge diameter, inlet and outlet construction angles, throat width, and number of blades, are designed to be consistent with the prototype blade, and the styling cross section is adjusted using the 11-parameter method to adjust the relevant styling parameters.
[0013] As a further improvement to the above technical solution, step S5 also includes: if the requirements are met, proceed to step S6; Step S6 includes: Output a 3D model of the titanium-aluminum turbine blades and draw engineering drawings.
[0014] According to another aspect of the present invention, an aero-engine is also provided, which includes the above-described titanium-aluminum power turbine blade design method.
[0015] The present invention has the following beneficial effects: This titanium-aluminum turbine blade design method first conducts a preliminary analysis of the manufacturing process of a prototype high-temperature alloy turbine blade, providing a bubble diagram of the prototype turbine blade's process from the perspectives of manufacturing feasibility, improving product yield, and reducing product manufacturing costs. Next, it performs geometric feature analysis on the prototype turbine blade, determining the geometric constraints for blade design. Considering the upstream and downstream matching relationship of the turbine blade and the impact of sealing bleed air on the optimized blade, it conducts three-dimensional simulation calculations of the main state points. Through multiple rounds of iterative optimization, the aerodynamic performance of the optimized titanium-aluminum turbine blade is obtained to meet engine requirements. Detailed structural optimization designs of the blade crown, blade body, and tenon are then performed on the optimized titanium-aluminum turbine blade. Strength, vibration, and life calculation analyses are conducted based on input parameters such as the blade temperature field and aerodynamic load field. If the requirements are not met, the process returns to iterative optimization. This design method can be directly applied to high-performance aero-gas turbine / propeller engines. Compared to the prototype high-temperature alloy blades, this design eliminates the need to reduce blade weight by increasing blade load and decreasing the number of blades. The titanium-aluminum blade design is based on the prototype blades, adjusting the minimum geometric dimensions to meet the manufacturing requirements of titanium-aluminum blades. While maintaining the same number of blades and throat area, weight reduction is not achieved through thinning the blade profile; instead, traditional high-temperature alloy turbine blade design experience can be applied, such as ensuring variations in blade profile installation angle and tip-to-root area ratio. Furthermore, this design method incorporates iterative optimization from multiple disciplines, effectively reducing weight and improving the engine's power-to-weight ratio while meeting requirements for aerodynamic performance, blade structure design, strength, vibration life, and manufacturing feasibility. The improved titanium-aluminum power turbine blades are approximately 50% lighter, effectively increasing the engine's power-to-weight ratio and reducing overall fuel consumption across the entire turbine envelope while maintaining turbine efficiency.
[0016] In addition to the objectives, features, and advantages described above, the present invention has other objectives, features, and advantages. The invention will now be described in further detail with reference to the figures. Attached Figure Description
[0017] The accompanying drawings, which form part of this application, are used to provide a further understanding of the invention. The illustrative embodiments of the invention and their descriptions are used to explain the invention and do not constitute an undue limitation of the invention. In the drawings: Figure 1 This is a simplified flowchart of a preferred embodiment of the present invention; Figure 2 This is a schematic diagram of a three-dimensional model of the blade in a specific embodiment of the present invention; Figure 3 This is a comparative schematic diagram of the leaf root cross-section design of a specific embodiment of the present invention; Figure 4 This is a comparative schematic diagram of the leaf mid-section shape design of a specific embodiment of the present invention; Figure 5 This is a comparative schematic diagram of the blade tip cross-section design of a specific embodiment of the present invention.
[0018] Legend: 11. Leaf crown; 12. Double radial comb teeth; 13. Leaf blade; 14. Lower edge plate; 15. Extension root; 16. Double dovetail tenon. Detailed Implementation
[0019] The embodiments of the present invention will be described in detail below with reference to the accompanying drawings. However, the present invention can be implemented in many different ways as defined and covered below.
[0020] Figure 1 This is a simplified flowchart of a preferred embodiment of the present invention; Figure 2 This is a schematic diagram of a three-dimensional model of the blade in a specific embodiment of the present invention; Figure 3 This is a comparative schematic diagram of the leaf root cross-section design of a specific embodiment of the present invention; Figure 4 This is a comparative schematic diagram of the leaf mid-section shape design of a specific embodiment of the present invention; Figure 5 This is a comparative schematic diagram of the blade tip cross-section design of a specific embodiment of the present invention.
[0021] like Figure 1 As shown in this embodiment, the design method for titanium-aluminum power turbine blades includes: S1. Conduct a preliminary analysis of the processing technology of the prototype high-temperature alloy turbine blade and provide a bubble diagram of the prototype turbine blade process. S2. Perform geometric feature analysis on the prototype power turbine working blades to determine the geometric constraints for blade design. S3. Based on the upstream and downstream matching relationship of turbine blades and the sealing and bleed air, perform three-dimensional simulation and joint calculation of the main state points of the optimized blades, and perform multiple rounds of iterative optimization until the aerodynamic performance of the optimized titanium-aluminum working blades meets the engine requirements. S4. Optimize the detailed structure of the working blades of the titanium-aluminum turbine by designing the crown 11, blade body 13, and tenon. S5. Perform strength, vibration and life calculation and analysis based on input parameters such as blade temperature field and aerodynamic load field. If the requirements are not met, proceed to step S2 for iterative optimization.
[0022] It should be noted that titanium-aluminum alloys possess characteristics such as low density (3.9 g / cm3), high specific stiffness and high-temperature specific strength, as well as excellent creep resistance and oxidation resistance. They are considered a novel lightweight high-temperature material that can replace some nickel-based superalloys in the hot-section components of aero-engines. Understandably, this titanium-aluminum power turbine blade design method first conducts a preliminary analysis of the processing technology of the prototype high-temperature alloy turbine blade, providing a bubble diagram of the prototype turbine blade's process from the perspectives of processing feasibility, improving product yield, and reducing product processing costs. Next, it performs geometric feature analysis on the prototype power turbine blade, determining the geometric constraints of the blade profile design. Considering the upstream and downstream matching relationship of the turbine blade and the sealing bleed air effect on the optimized blade, it conducts three-dimensional simulation calculations of the main state points. Through multiple rounds of iterative optimization, the aerodynamic performance of the optimized titanium-aluminum working blade is obtained to meet engine requirements. Detailed structural optimization designs are then performed on the blade crown 11, blade body 13, and tenon of the optimized titanium-aluminum turbine working blade. Strength, vibration, and life calculation analyses are conducted based on input parameters such as the blade temperature field and aerodynamic load field. If the requirements are not met, iterative optimization is returned. This design method can be directly applied to high-performance aviation gas turbines. Compared to the prototype high-temperature alloy blades, the turboshaft / propeller engine does not require increasing blade load to reduce the number of blades to achieve blade weight reduction. The titanium-aluminum blade design is based on the prototype blade, and the minimum geometric dimensions are adjusted to meet the manufacturing requirements of titanium-aluminum blades. Under the condition of keeping the number of blades and throat area unchanged, there is no need to use the blade profile thinning design to achieve weight reduction. The design experience of traditional high-temperature alloy turbine blades can be used, such as ensuring the change of blade profile installation angle and the change of tip-root area ratio. At the same time, this design method combines iterative optimization design of multiple disciplines. While meeting the requirements of aerodynamic performance, blade structure design, strength, vibration life and manufacturing process feasibility, it effectively reduces weight and improves the power-to-weight ratio of the engine. The weight of the improved titanium-aluminum power turbine working blades is reduced by about 50%. While meeting the requirements of engine turbine efficiency, it effectively improves the engine's power-to-weight ratio and reduces the overall fuel consumption rate of the engine across the entire envelope.
[0023] In one specific embodiment, the blade includes a serrated crown 11, double radial serrations 12, a blade body 13, a lower edge plate 14, a parallelogram-shaped extension root 15, and a double dovetail tenon 16; In one specific embodiment, the prototype power turbine working blade is an uncooled crowned turbine blade with an inlet relative total temperature of 810.5K, a blade height of 175.4mm, an axial chord length of 31.0mm, a trailing edge diameter of 0.5mm, and a leading edge diameter ranging from 1.16mm to 1.81mm. For in-situ replacement considerations, the blade tenon and blade crown 11 geometry are not adjusted. Based on the titanium-aluminum blade process analysis of this embodiment, the power turbine working blade needs to be adjusted in shape, and it is recommended that the trailing edge diameter of the blade be greater than 1.0mm. Specifically, in step S1, a process analysis is conducted. The titanium-aluminum blade process technicians conduct a preliminary analysis of the processing technology of the prototype high-temperature alloy turbine blade. From the perspectives of processing feasibility, improving the product processing qualification rate and reducing the product processing cost, the process difficulties of the prototype turbine blade in the processing of titanium-aluminum materials are identified and marked, and a process bubble diagram is formed. In some preferred embodiments, step S2 further includes: improving and optimizing the blade based on the prototype blade and in conjunction with the titanium-aluminum turbine blade processing technology, without changing the number of blades and meeting preset size constraints, adjusting parameters such as the blade trailing edge diameter and / or the radial distribution of the blade mounting angle and / or the blade tip-root area ratio; in some preferred embodiments, step S2 further includes: the key styling parameters of the blade, including the leading edge diameter, inlet and outlet construction angles, throat width, and number of blades, are consistent with the prototype blade, and the relevant styling parameters are adjusted using the 11-parameter method for the styling section, thereby ensuring the smoothness of the blade surface and avoiding unreasonable geometric features; in a specific embodiment, based on the prototype blade, ensuring that the key styling parameters such as the leading edge diameter, inlet and outlet construction angles, throat width, and number of blades are not adjusted, the trailing edge diameter of the improved blade is adjusted to 1.0 mm, the relevant styling parameters are adjusted using the 11-parameter method for the styling section, and the comparison reference of the blades before and after optimization is used. Figures 3 to 5 Specifically, the original blade trailing edge diameter was 0.5 mm, which is the thinnest area of the blade. For cast titanium-aluminum blades, the trailing edge is prone to undercasting, and subsequent machining and polishing are also prone to deformation. However, after adjusting the trailing edge diameter to 1.0 mm, the yield rate of cast titanium-aluminum blades is high. Therefore, sacrificing the turbine process coordination to improve the yield rate of cast titanium-aluminum blades reduces production costs. After adjusting the trailing edge diameter, the 11-parameter method of molding can better fit the shape of the original blade, while also better controlling the blade throat area, thus maximizing turbine performance. Without changing the number of blades to maintain aerodynamic frequency characteristics consistent with the original design and meet relevant dimensional constraints such as the inner and outer diameters of the flow channel and installation position, the blades were initially improved and optimized based on the prototype blades and combined with the experience of titanium-aluminum blade processing technology. First, the key shaping parameters such as leading edge diameter, inlet and outlet construction angles, throat width, and number of blades were kept consistent with the prototype blades. This ensured that the newly designed titanium-aluminum blades were basically equivalent to the prototype blades in aerodynamic function, avoiding significant impact on the matching of upstream and downstream components. The trailing edge diameter of all blade height sections was uniformly adjusted from 0.5mm in the prototype blades to 1.0mm, directly meeting the minimum processing size requirements of titanium-aluminum materials. The shaping section adopted the mature 11-parameter method for parametric control. By adjusting relevant shaping parameters, such as the distribution of the blade installation angle (i.e., the angle between the arc chord of the blade and the engine axis or crest line) along the blade height and the ratio of the cross-sectional area of the blade tip to the root, the aerodynamic losses that may be caused by the thickening of the trailing edge were compensated, and a better aerodynamic configuration was explored. Through this step, one or more preliminary optimized blade geometric models were obtained. In some preferred embodiments, step S3 includes: performing three-dimensional joint calculations on the prototype blade and the optimized blade respectively. During the simulation calculation, the mesh division of the optimized blade adopts the mesh template of the prototype blade, and the sealing bleed air settings remain the same. Specifically, the commercial ANSYS-CFX software is used to perform three-dimensional joint calculations on the prototype blade and the optimized blade respectively. During the simulation calculation, the mesh division of the optimized blade adopts the mesh template of the prototype blade, and the sealing bleed air settings remain the same, thereby ensuring the comparability of numerical simulation results. The preliminary optimized blade model obtained in step S2 is put into the aerodynamic performance verification stage. Considering the matching relationship between upstream and downstream components of the turbine blade and the influence of sealing bleed air, the aerodynamic performance of the new blade and its impact on the overall engine performance are accurately evaluated. The commercial computational fluid dynamics software ANSYS-CFX is used to perform three-dimensional flow field simulation joint calculations on the prototype blade and the optimized blade. The mesh division of the optimized blade directly adopts the mesh template and topology of the prototype blade, ensuring the consistency of mesh quality, quantity and distribution, eliminating the calculation error caused by mesh differences. The boundary condition settings such as flow rate, position and angle of sealing bleed air are also kept exactly the same as the simulation model of the prototype blade, ensuring consistent boundary conditions. In some preferred embodiments, step S3 includes: during the performance parameter comparison process, the turbine expansion ratio of the optimized blade is consistent with that of the prototype blade, the throat area of the optimized blade is adjusted to be the same as that of the prototype blade, and the performance parameters and flow field structure of the optimized blade and the prototype blade are compared; specifically, during the performance parameter comparison process, firstly, the turbine expansion ratio of the optimized blade and the prototype blade is ensured to be consistent, secondly, the throat area of the optimized blade is adjusted to be the same as that of the prototype blade, and then the performance parameters and flow field structure of the optimized blade and the prototype blade are compared; in a specific embodiment, the numerical calculation results show that: compared with the prototype blade, the total pressure recovery coefficient of the optimized blade is reduced by 0.21%, and the slack efficiency of the optimized power turbine is reduced by 0.40%, but there is still a certain efficiency margin compared with the overall requirements, and the total pressure loss of the downstream exhaust support plate remains unchanged, indicating that the optimized blade has no adverse effect on the downstream components.
[0024] In some preferred embodiments, step S4 further includes: after the three-dimensional structural model design of the titanium-aluminum power turbine blade is completed, the requirements for temperature field calculation, strength, vibration and life calculation of the main state points are proposed for downstream heat transfer and strength vibration life; so as to improve the design while ensuring that the engine performance, strength vibration life and processing technology feasibility all meet the requirements; after the aerodynamic performance meets the requirements, the structural detail optimization stage is entered to ensure that all structural details meet the processing technology requirements of titanium-aluminum materials, and further optimize the structural reliability; In some preferred embodiments, step S4 further includes: the minimum geometric dimension of the tenon of the blade is 1 mm, and the minimum joint dimension of the blade crown 11 is 1 mm. It should be noted that, compared with traditional high-temperature alloys, titanium-aluminum alloys have lower ductility, which makes them prone to brittle fracture when subjected to stress concentration or dynamic loads (such as impact or vibration). Therefore, when designing the working blades of crowned power turbines, it is necessary to consider the minimum trailing edge thickness, as well as the geometric dimensions such as the blade root extension 15 and tenon during machining. In a specific embodiment, the prototype power turbine working blade crown 11 is a combination of serrated crown crown 11 and double radial serrations 12, and the tenon is a combination of parallelogram-shaped extension root 15 and double dovetail tenon 16. Considering both in-situ replacement and titanium-aluminum machining processes, the minimum geometric dimensions of the blade tenon and crown 11 are above 1.0 mm to meet the subsequent machining requirements of titanium-aluminum blades. Therefore, the improved titanium-aluminum blade of this embodiment only adjusts the blade shape, and the blade trailing edge diameter is adjusted from 0.5 mm to 1.0 mm. The recommended range for the blade installation angle (angle with the blade tip line) is 46°~72°, and the recommended value for the tip-root area ratio is 0.495. Specifically, since the prototype power turbine blades themselves adopt a combination of serrated crown blades and double radial grates, as well as a combination of parallelogram-shaped extension roots and double dovetail tenons, these structures have proven to be highly efficient in terms of aerodynamics and heat transfer. Considering both in-situ replacement and titanium-aluminum machining processes, the geometric contours of the blade crown and tenons remain unchanged, but the dimensions of all their geometric features are reviewed to ensure that their minimum values are all above 1.0 mm, such as the thickness of the grates tip and the radius of the tenon corners, to meet the subsequent machining requirements of the titanium-aluminum blades. In addition to the trailing edge diameter of 1.0 mm determined in step S2, after multiple rounds of optimization iterations, the final determined blade mounting angle (the angle between the blade tip and the airfoil line) is distributed along the blade height in the range of 46° to 72°, and the tip-to-root area ratio (the ratio of the blade tip cross-sectional area to the blade root cross-sectional area) is taken as 0.495. After completing the three-dimensional structural model design, calculation requirements are submitted to downstream heat transfer, strength, and vibration professionals, providing boundary conditions such as the temperature field and aerodynamic load field at the main state points. In some preferred embodiments, step S5 further includes: if the requirements are met, proceeding to step S6; performing a comprehensive verification of the strength, vibration, and lifespan of the titanium-aluminum power turbine blades optimized in step S4. The calculation requires applying realistic load boundaries, including: the enormous centrifugal load generated by high-speed rotation, the thermal load caused by the temperature gradient, and the aerodynamic load generated by airflow. Step S6 includes: A 3D model of the titanium-aluminum turbine blade was output for engineering drawing. It should be noted that centrifugal load, temperature load, and aerodynamic load were applied during the strength and life calculation of the improved titanium-aluminum power turbine blade. The calculation results show that the static strength of the blade blade 13 meets the requirements under both design and maximum conditions. Furthermore, compared to the prototype blade, the improved titanium-aluminum power turbine blade shows improvements in both blade 13 creep life and low-cycle fatigue life. In this specific embodiment, the vibration characteristics of the improved titanium-aluminum power turbine blade and disk at key state points were calculated. Compared to the prototype blade, the vibration characteristics of the titanium-aluminum blade are basically the same, meeting the evaluation criteria and exhibiting no resonant speed points. The final titanium-aluminum turbine blade meets the strength, vibration, and life requirements. Compared to the prototype blade, the weight of the titanium-aluminum power turbine blade is reduced by approximately 50%. On the other hand, a preferred embodiment of the present invention also provides an aero-engine that applies the above-mentioned titanium-aluminum power turbine blade design method.
[0025] In the description of this invention, it should be noted that the terms "upper", "lower", "front", "rear", etc., indicate the orientation or positional relationship based on the orientation or positional relationship shown in the accompanying drawings. They are only for the convenience of describing this invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation. Therefore, they should not be construed as limiting this invention.
[0026] In the description of this invention, it should be noted that, unless otherwise explicitly specified and limited, the terms "installation," "connection," and "linking" should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention based on the specific circumstances.
[0027] The above description is merely a preferred embodiment of the present invention and is not intended to limit the invention. Various modifications and variations can be made to the present invention by those skilled in the art. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the scope of protection of the present invention.
Claims
1. A method of designing a titanium aluminide power turbine blade, characterized by, The design method includes: S1. Conduct a preliminary analysis of the processing technology of the prototype high-temperature alloy turbine blade and provide a bubble diagram of the prototype turbine blade process. S2. Perform geometric feature analysis on the prototype power turbine working blades to determine the geometric constraints for blade design. S3. Based on the upstream and downstream matching relationship of turbine blades and the sealing and bleed air, perform three-dimensional simulation and joint calculation of the main state points of the optimized blades, and perform multiple rounds of iterative optimization until the aerodynamic performance of the optimized titanium-aluminum working blades meets the engine requirements. S4. Optimize the detailed structure design of the blade crown, blade body, and tenon of the optimized titanium-aluminum turbine working blades; S5. Perform strength, vibration and life calculation and analysis based on input parameters such as blade temperature field and aerodynamic load field. If the requirements are not met, proceed to step S2 for iterative optimization.
2. The design method of a titanium aluminide power turbine blade according to claim 1, wherein, Step S2 further includes: without changing the number of blades and meeting the preset size constraints, improving and optimizing the blade based on the prototype blade and in combination with the titanium-aluminum turbine blade processing technology, adjusting the blade trailing edge diameter and / or the radial distribution of the blade mounting angle and / or the blade tip root area ratio parameters.
3. The design method for titanium-aluminum power turbine blades according to claim 1, characterized in that, Step S3 includes: performing three-dimensional joint calculations on the prototype blade and the optimized blade respectively. During the simulation calculation, the mesh division of the optimized blade adopts the mesh template of the prototype blade, and the sealing and bleed air settings remain the same.
4. The design method for titanium-aluminum power turbine blades according to claim 1, characterized in that, Step S3 includes: during the performance parameter comparison process, the turbine expansion ratio of the optimized blade is consistent with that of the prototype blade, the throat area of the optimized blade is adjusted to be the same as that of the prototype blade, and the performance parameters and flow field structure of the optimized blade and the prototype blade are compared.
5. The design method of a titanium aluminide power turbine blade according to claim 1, wherein Step S4 also includes: after the design of the three-dimensional structural model of the titanium-aluminum power turbine working blade is completed, the requirements for temperature field calculation, strength, vibration and life calculation of the main state points are put forward for downstream heat transfer and strength vibration life.
6. The design method of a titanium aluminide power turbine blade of claim 1, wherein, The blade includes a serrated crown (11), double radial serrations (12), blade body (13), lower edge plate (14), parallelogram extension root (15), and double dovetail tenon (16).
7. The design method of a titanium aluminide power turbine blade of claim 6, wherein Step S4 further includes: the minimum geometric dimension of the tenon of the blade is 1 mm, and the minimum joint dimension of the blade crown is 1 mm.
8. The method of designing a titanium aluminide power turbine blade of claim 6 wherein, Step S2 also includes: the key styling parameters of the blade include leading edge diameter, inlet and outlet construction angle, throat width, and the number of blades designed to be consistent with the prototype blade, and the styling cross section is adjusted using the 11-parameter method to adjust the relevant styling parameters.
9. The design method of a titanium aluminide power turbine blade according to claim 1, wherein Step S5 also includes: if the requirements are met, proceed to step S6; Step S6 includes: Output a 3D model of the titanium-aluminum turbine blades and draw engineering drawings.
10. An aeroengine characterised in that, The application includes the titanium-aluminum power turbine blade design method according to any one of claims 1-9.