CN-122020887-A - Multidisciplinary optimization design method, system, equipment and medium for winglet blade with tip

CN122020887ACN 122020887 ACN122020887 ACN 122020887ACN-122020887-A

Abstract

The invention relates to the technical field of winglet design, and discloses a multidisciplinary optimization design method, a multidisciplinary optimization design system, multidisciplinary optimization design equipment and multidisciplinary optimization design media for winglet blades with tips, wherein the method comprises the steps of obtaining an initial geometric model of the winglet blade with the tips; and optimizing the initial geometric model based on the target function and a preset constraint condition to obtain an optimized geometric model, and generating the optimal winglet blade with the tip based on the optimized geometric model. The multi-disciplinary optimization method combines the multi-disciplinary optimization objective function with the preset constraint condition, meets the multi-disciplinary optimization requirement of the winglet blade with the tip, can realize multi-dimensional performance collaborative optimization, and can lock the optimal geometric parameter combination meeting the constraint condition based on the multi-disciplinary optimization of the initial geometric model, thereby ensuring the fitting design requirement of the blade performance, improving the design accuracy and reliability of the blade, and being beneficial to optimizing the optimal winglet structure of the winglet blade with the tip, and further realizing the optimal design of the winglet blade with the tip.

Inventors

CHEN YIHONG
LI WEI
SHAN YIJUN
JIANG KANGHE
ZENG FEI
WANG ZHENG
CHEN CHEN

Assignees

中国航发湖南动力机械研究所

Dates

Publication Date: 20260512
Application Date: 20260113

Claims (10)

1. A multidisciplinary optimization design method for a winglet-bearing blade, the method comprising: acquiring an initial geometric model of the winglet blade with the tip; Determining an objective function of the multidisciplinary optimization of the winglet-tipped blade; And optimizing the initial geometric model based on the objective function and a preset constraint condition to obtain an optimized geometric model, and generating the optimal winglet blade with the tip based on the optimized geometric model.
2. The multi-discipline optimization design method of a winglet-with-tip blade of claim 1, wherein the multi-discipline of the winglet-with-tip blade includes at least an aerodynamic discipline, a structural strength discipline, and a heat transfer discipline, the determining an objective function of the multi-discipline optimization of the winglet-with-tip blade comprising: Respectively determining optimization indexes corresponding to aerodynamic disciplines, structural strength disciplines and heat transfer disciplines; And determining an objective function of the multidisciplinary optimization of the winglet-bearing blade based on each optimization index.
3. The multi-discipline optimization design method of a winglet-with-blade of claim 2, wherein the optimization index corresponding to the aerodynamic discipline is turbine efficiency, the optimization index corresponding to the structural strength discipline is a maximum equivalent stress of a blade root, and the optimization index corresponding to the heat transfer discipline is an average temperature of a blade tip region, wherein the determining an objective function of the multi-discipline optimization of the winglet-with-blade based on each of the optimization indexes comprises: carrying out dimensionless treatment on the turbine efficiency, the maximum equivalent stress of the blade root and the average temperature of the blade tip region of the blade respectively to correspondingly obtain corresponding dimensionless parameters; and carrying out weighted summation on the dimensionless parameters to obtain the objective function of multidisciplinary optimization of the winglet blade with the tip.
4. A multi-disciplinary optimization design method for a winglet blade with a tip according to any one of claims 1 to 3, wherein the optimizing the initial geometric model based on the objective function and a preset constraint condition results in an optimized geometric model, comprising: Performing multidisciplinary optimization on the initial geometric model by using a preset optimization algorithm according to the objective function and a preset constraint condition to obtain an optimized geometric model, wherein the optimized geometric model comprises geometric parameter combinations of the winglet blade with the blade tip, which meet the preset constraint condition and enable the objective function to reach comprehensive optimization, and the preset constraint condition comprises that the average temperature of the blade tip area of the winglet blade with the blade tip after optimization is lower than a preset reference temperature and/or the maximum equivalent stress of the blade root of the winglet blade with the blade tip after optimization is lower than a preset reference stress.
5. The multi-disciplinary optimization design method of a winglet-with-blade of claim 1, wherein the obtaining an initial geometric model of the winglet-with-blade comprises: Generating an initial geometric model of the winglet blade with the tip by adopting a preset parametric modeling method, wherein the initial geometric model comprises a group of geometric parameters, and the geometric parameters are used for adjusting and controlling the geometric shape of the winglet.
6. The multi-disciplinary optimization design method of a winglet-with-tip blade of claim 1, wherein the generating an optimal winglet-with-tip blade based on the optimized geometric model comprises: performing simulation verification on the optimized geometric model; After the simulation verification of the optimized geometric model is passed, carrying out manufacturing process adaptation on the optimized geometric model based on preset manufacturing process requirements, and outputting corresponding production parameters; and generating the optimal winglet blade with the blade tip by using the production parameters.
7. The multi-disciplinary optimization design method of a winglet-bearing blade of claim 6, wherein the performing a simulation verification of the optimized geometric model comprises: Performing joint simulation of aerodynamic discipline, structural strength discipline and heat transfer discipline on the optimized geometric model respectively, and calculating performance indexes of corresponding discipline, wherein the performance indexes corresponding to the aerodynamic discipline comprise at least one of aerodynamic efficiency, total pressure loss coefficient, leakage flow and turbine efficiency, the performance indexes corresponding to the structural strength discipline comprise at least one of maximum equivalent stress, vibration characteristic and fatigue life of a blade root, and the performance indexes corresponding to the heat transfer discipline comprise at least one of average temperature, maximum temperature, temperature difference distribution and heat exchange coefficient of a blade tip region; judging whether each performance index meets an objective function and a preset constraint condition; if all the performance indexes meet the objective function and the preset constraint condition, determining that the simulation verification of the optimized geometric model is passed; And if any performance index does not meet the objective function or the preset constraint condition, returning to the step of determining the objective function with the winglet blade multidisciplinary optimization.
8. A multidisciplinary optimization design system for a winglet-bearing blade, the system comprising: The acquisition module is used for acquiring an initial geometric model of the winglet blade with the tip; the determining module is used for determining an objective function of the multidisciplinary optimization of the winglet-equipped blade; and the optimization module is used for optimizing the initial geometric model based on the objective function and a preset constraint condition to obtain an optimized geometric model, and generating an optimal winglet blade with a tip based on the optimized geometric model.
9. An electronic device comprising a controller, the controller comprising a memory and a processor, the memory and the processor being communicatively coupled to each other, the memory having stored therein computer instructions, the processor executing the computer instructions to perform the multi-disciplinary optimization design method with winglet blade of any of claims 1 to 7.
10. A computer-readable storage medium having stored thereon computer instructions for causing a computer to perform the multi-disciplinary optimization design method with winglet blade of any of claims 1 to 7.

Description

Multidisciplinary optimization design method, system, equipment and medium for winglet blade with tip Technical Field The invention relates to the technical field of winglet design, in particular to a multidisciplinary optimization design method, system, equipment and medium for a winglet blade with a tip. Background Turbines are one of the core components in aircraft gas turbine engines, which function to convert energy in high temperature, high pressure combustion gases into mechanical energy. The turbine blade is used as a key component of the turbine and rotates at a high speed under high temperature and high pressure, and the airflow condition of the surface of the turbine blade is extremely complex. The advantages and disadvantages of the vane design directly affect the performance and efficiency of the whole engine. In the actual turbine flow process, as a tiny gap (blade tip clearance) exists between the top end (blade tip) of a turbine blade and the inner wall of a static casing (shell) surrounding the blade, part of high-temperature gas can leak from the pressure side to the suction side of the blade to form blade tip leakage flow, and the leakage flow has the characteristics of strong three-dimension, strong shearing, unsteady and the like, not only can lead to the reduction of the functional capability of the turbine, but also can cause obvious aerodynamic loss, and the heat transfer coefficient of the blade tip area is rapidly increased, even the blade tip ablation is caused. Studies have shown that tip leakage losses account for approximately one third of the total aerodynamic losses of the turbine, and that secondary flow losses associated with leakage flow account for over half of the endwall losses. In order to inhibit the leakage flow of the blade tip and reduce the loss, solutions including clearance control, jet flow control, blade tip treatment, casing treatment and the like have been proposed in the prior art, wherein the blade tip treatment is used as a passive control means, and the purpose of inhibiting the leakage is achieved by changing the geometric configuration of the blade tip area to interfere with the leakage flow path. Common blade tip handling approaches include providing ribs, grooves, or winglets on the tip, where the winglet technology is widely investigated for its potential for controlling leakage flow. For example, relevant scholars find that the full-circumference small blade tip wing can improve efficiency under all expansion ratio working conditions of the turbine through experiments, relevant measurement shows that the small blade tip wing has the best control effect on leakage flow, relevant experiments indicate that a scheme that the small blade is arranged on the suction surface and the pressure surface simultaneously can reduce flow loss to the greatest extent, relevant scholars propose a small blade scheme that grooves are formed in the blade tip part, the efficiency of the turbine can be improved obviously under high-load working conditions, and in addition, relevant experiments further verify the advantages of the small blade on the pressure surface in improving the efficiency of the turbine. However, prior art winglet designs have focused on optimization of aerodynamic performance in a single discipline, or merely determined structural parameters empirically and experimentally, and lack a systematic multidisciplinary co-design scheme. Turbine blades involve multiple disciplines in actual operation, such as aerodynamic, coupled effects of heat transfer, and if only a single discipline is considered, it is often difficult to achieve optimum overall performance, and even the blade reliability may be reduced by ignoring heat transfer constraints. In addition, the traditional design scheme relies on manual trial and error and empirical adjustment, has long optimization period and low efficiency, and is difficult to fully develop the design potential of the winglet. Therefore, there is a need for a multi-disciplinary optimization design scheme that can systematically take into account the multi-disciplinary coupling effects of blade design and achieve an automated, high-efficiency design of winglet-tipped blades to optimize the optimal winglet-tipped structure and thereby achieve winglet-tipped blade design. Disclosure of Invention The invention provides a multidisciplinary optimization design method, a multidisciplinary optimization design system, multidisciplinary optimization design equipment and multidisciplinary optimization design medium for a winglet blade with a tip, and aims to solve the problem that the optimal design of the winglet blade with the tip is difficult to realize due to the fact that multidisciplinary coupling influence of blade design is ignored in the prior art, and design efficiency is seriously influenced. In a first aspect, the invention provides a multidisciplinary optimization design method for a winglet-bearing blade, the method co