期刊文献+
共找到1,282篇文章
< 1 2 65 >
每页显示 20 50 100
Fatigue Life Estimation for an Aircraft Engine Fan Blade
1
作者 尹珩苏 晏晶 +2 位作者 陈浩 吕志强 黄洪钟 《Journal of Donghua University(English Edition)》 EI CAS 2016年第2期188-191,共4页
In this paper,stress states under corresponding condition of an aero-engine fan blade using finite element stress-strain analysis for three work cycles in the 900 h load spectrum are obtained.Through the nominal stres... In this paper,stress states under corresponding condition of an aero-engine fan blade using finite element stress-strain analysis for three work cycles in the 900 h load spectrum are obtained.Through the nominal stress method,we calculated the fatigue notch factor and combined the material characteristics of TC6 to correct the material curve to the fan blades curve. Finally,the fatigue life of a fan blade was estimated using the linear cumulative damage rule and nonlinear cumulative damage theory. 展开更多
关键词 fan blade nominal stress method fatigue notch factor cumulative fatigue damage theory
下载PDF
NON-DIMENSIONAL DESIGN PARAMETERS FOR FOD TOLERANT FAN BLADES
2
作者 T.Shioya 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 1991年第2期113-120,共8页
Non-dimensional design concept for FOD tolerant fan blades is introduced based on the analyses of simplified impact models. The fan blades arc idealized as either beams or plates of elastic or rigid-plastic materials.... Non-dimensional design concept for FOD tolerant fan blades is introduced based on the analyses of simplified impact models. The fan blades arc idealized as either beams or plates of elastic or rigid-plastic materials. The case of constant force impact as well as that of mass impact is analyzed. The centrifugal force effects are also considered in the beam models. The critical fracture conditions arc shown in simple npn-dimensional formulae or diagrams for each case. 展开更多
关键词 NON-DIMENSIONAL DESIGN PARAMETERS FOR FOD TOLERANT fan bladeS
下载PDF
Numerical Study on the Duct Noise Control of Single-Stage Axial Flow Fan with Wave Leading Edge Stator Blade Configurations 被引量:1
3
作者 Jianxin Lian Hang Tong +2 位作者 Liangji Zhang Weiyang Qiao Weijie Chen 《Journal of Applied Mathematics and Physics》 2023年第8期2503-2514,共12页
This study focuses on a single-stage axial flow fan, investigating the effect of three kinds of wave leading edge stator blades on its noise reduction. The DDES method and the duct acoustic analogy theory based on the... This study focuses on a single-stage axial flow fan, investigating the effect of three kinds of wave leading edge stator blades on its noise reduction. The DDES method and the duct acoustic analogy theory based on the penetrable data surface were used for noise prediction. The results showed that the three kinds of wave leading edge blades were effective in reducing the rotor-stator interaction tonal noise and also have a certain inhibitory effect on broadband noise. The A10W15 stator blade can effectively reduce broadband noise in the frequency range of 2200 - 4200 Hz. When the amplitude is increased to 20, the noise reduction effect is further enhanced. However, when the amplitude is increased to 30, the broadband noise reduction effect is no longer significant. Further research shows that the wave leading edge stator blades can significantly change the pressure fluctuation distribution on the leading edge and suction surface, which control the modal energy distribution. Finally, this paper analyzed multiple factors affecting the broadband noise reduction, such as the noise source cut-off and cut-on effect and correlation. The purpose of this paper is to explore the laws of the influence of wave leading edge blades on the duct noise of real fan, and to reveal its noise control mechanism. . 展开更多
关键词 fan Wave Leading Edge blade Duct Noise Broadband Noise Noise Source Analysis
下载PDF
Foreign Object Damage to Fan Rotor Blades of Aeroengine Part II: Numerical Simulation of Bird Impact 被引量:8
4
作者 关玉璞 赵振华 +1 位作者 陈伟 高德平 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2008年第4期328-334,共7页
Bird impact is one of the most dangerous threats to flight safety. The consequences of bird impact can be severe and, therefore, the aircraft components have to be certified for a proven level of bird impact resistanc... Bird impact is one of the most dangerous threats to flight safety. The consequences of bird impact can be severe and, therefore, the aircraft components have to be certified for a proven level of bird impact resistance before being put into service. The fan rotor blades of aeroengine are the components being easily impacted by birds. It is necessary to ensure that the fan rotor blades should have adequate resistance against the bird impact, to reduce the flying accidents caused by bird impacts. Using the contacting-impacting algorithm, the numerical simulation is carded out to simulate bird impact. A three-blade computational model is set up for the fan rotor blade having shrouds. The transient response curves of the points corresponding to measured points in experiments, displacements and equivalent stresses on the blades are obtained during the simulation. From the comparison of the transient response curves obtained from numerical simulation with that obtained from experiments, it can be found that the variations in measured points and the corresponding points of simulation are basically the same. The deforming process, the maximum displacements and the maximum equivalent stresses on blades are analyzed. The numerical simulation verifies and complements the experiment results. 展开更多
关键词 aerospace propulsion system bird impact numerical simulation fan rotor blade transient response
下载PDF
Foreign Object Damage to Fan Rotor Blades of Aeroengine Part I:Experimental Study of Bird Impact 被引量:14
5
作者 关玉璞 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2007年第5期408-414,共7页
The conditions of experiment for bird impact to blades have been improved. The experiment of bird impact to the fan rotor blades of an aeroengine is carried out. Through analyzing the transient state response of blade... The conditions of experiment for bird impact to blades have been improved. The experiment of bird impact to the fan rotor blades of an aeroengine is carried out. Through analyzing the transient state response of blades impacted by bird and the change of blade profile before and after the impact, the anti-bird impact performance of blades in the first fan rotor is verified. The basis of anti-foreign object damage design for the fan rotor blades of an aeroengine is provided. 展开更多
关键词 aerospace propulsion system bird impact experiment fan rotor blade transient response
下载PDF
Three-dimensional modeling and reconstructive change of residual stress during machining process of milling, polishing, heat treatment, vibratory finishing, and shot peening of fan blade 被引量:2
6
作者 Ji-Yin Zhang Chang-Feng Yao +2 位作者 Min-Chao Cui Liang Tan Yun-Qi Sun 《Advances in Manufacturing》 SCIE EI CAS CSCD 2021年第3期430-445,共16页
Residual stress during the machining process has always been a research hotspot,especially for aero-engine blades.The three-dimensional modeling and reconstructive laws of residual stress among various processes in th... Residual stress during the machining process has always been a research hotspot,especially for aero-engine blades.The three-dimensional modeling and reconstructive laws of residual stress among various processes in the machining process of the fan blade is studied in this paper.The fan blades of Ti-6Al-4V are targeted for milling,polishing,heat treatment,vibratory finishing,and shot peening.The surface and subsurface residual stress after each process is measured by the X-ray diffraction method.The distribution of the surface and subsurface residual stress is analyzed.The Rational Taylor surface function and cosine decay function are used to fit the characteristic function of the residual stress distribution,and the empirical formula with high fitting accuracy is obtained.The value and distribution of surface and subsurface residual stress vary greatly due to different processing techniques.The reconstructive change of the surface and subsurface residual stress of the blade in each process intuitively shows the change of the residual stress between the processes,which has a high reference significance for the research on the residual stress of the blade processing and the optimization of the entire blade process. 展开更多
关键词 fan blade Machining process Surface residual stress Subsurface residual stress Three-dimensional modeling Reconstructive change
原文传递
Internal structural optimization of hollow fan blade based on sequential quadratic programming algorithm 被引量:1
7
作者 YANG Jian-qiu WANG Yan-rong 《航空动力学报》 EI CAS CSCD 北大核心 2011年第4期787-793,共7页
Several structural design parameters for the description of the geometric features of a hollow fan blade were determined.A structural design optimization model of a hollow fan blade which based on the strength constra... Several structural design parameters for the description of the geometric features of a hollow fan blade were determined.A structural design optimization model of a hollow fan blade which based on the strength constraint and minimum mass was established based on the finite element method through these parameters.Then,the sequential quadratic programming algorithm was employed to search the optimal solutions.Several groups of value for initial design variables were chosen,for the purpose of not only finding much more local optimal results but also analyzing which discipline that the variables according to could be benefit for the convergence and robustness.Response surface method and Monte Carlo simulations were used to analyze whether the objective function and constraint function are sensitive to the variation of variables or not.Then the robust results could be found among a group of different local optimal solutions. 展开更多
关键词 hollow fan blade structural optimization sequential quadratic algorithm finite element method Monte Carlo simulations
原文传递
Numerical simulation of a UAV impacting engine fan blades
8
作者 Jingyu YU Bingjin LI +4 位作者 Jun LIU Naidan HOU Yingchun ZHANG Yafeng WANG Yulong LI 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2021年第10期177-190,共14页
A 3D digital model of a small Unmanned Aerial Vehicle(UAV)is obtained by using the method of scanning reverse modeling and joint mapping.A numerical simulation of a small UAV strikes on rotary engine blades,presented ... A 3D digital model of a small Unmanned Aerial Vehicle(UAV)is obtained by using the method of scanning reverse modeling and joint mapping.A numerical simulation of a small UAV strikes on rotary engine blades,presented in this paper,was performed with a Transient Nonlinear Finite Element code PAM-CRASH software.A test of motor strike on plate was developed and the dynamic response of the plate were obtained to validate the numerical simulation method of a UAV strike on blades.Based on this,dynamic damage response caused by UAV on the engine blades were studied.It is indicated that the impact process between the UAV and a single blade can be divided into two typical stages:cutting and impact.Cutting mainly leads to the failure of the leading edge material,and impact mainly leads to the plastic deformation of the blade.At the same time,it is compared with the damage impacted by bird with the same mass.For the same mass of bird and UAV,the damage caused by UAV striking fan blade is more serious,and 1.345 kg UAV striking fan blade of typical civil aviation engine is enough to cause damage to flight safety. 展开更多
关键词 AIRWORTHINESS Bird impact Engine fan blade Explicit dynamics UAV
原文传递
Influence Factors for Impact Actions and Transient Trajectories of Fan Blades after Fan Blade Out in Typical 2-Shaft High Bypass Ratio Turbofan Engine
9
作者 XU Xue LI Hongxin FENG Guoquan 《Journal of Thermal Science》 SCIE EI CAS CSCD 2022年第1期96-110,共15页
To enhance the understanding of design characters, which have prominent influences during the fan blade out event, a simplified geometrical and dynamic analysis method was derived, and a typical 2-shaft high bypass ra... To enhance the understanding of design characters, which have prominent influences during the fan blade out event, a simplified geometrical and dynamic analysis method was derived, and a typical 2-shaft high bypass ratio turbofan engine was selected and modeled. Based on analytical deriving and engineering experience learned from the real engine failure case, three determinative impact actions were recognized from the fan blade out process. The transient trajectories of these impact actions were researched in analytical method, and then thickness of acoustic lining, quantity of fan blades and threshold load of structural fuse were analyzed as key design characters. 36 serialized fan blade out transient dynamic simulations were conducted by using the 2-shaft high bypass ratio turbofan engine model within different combinations of the three key design factors. The results from geometrical and dynamic analysis matched mainly well with the results from simulations. Characteristic phenomenon in simulation can be explained theoretically. Five conclusions can be summarized from these results. (1) If thickness fan acoustic lining was thinner, the deviation between simplified analytical calculation and simulation were not outstanding to predict Blade-Casing the first impact time and angular position. (2) An appropriate thickness of acoustic lining could make a lower impact stress of fan casing at the first impact. (3) Different thickness of acoustic linings leaded to two impact modes for blade 2, which were tip impact and root impact. (4) Different impact conditions between blade 1 and blade 2 caused remarkable speed components distinction of blade 1, and leaded to a wide range of transient trajectory of blade 1 during FBO event. (5) Thicker acoustic lining in this research can usually find the porper threshold loads setting, which can give a satisfactory outbound vibration. Two details were raised for further research, which were impact behavior of composite material fan blade and honeycomb and influences of wider FBO threshold load ranges in design cases with thinner acoustic lining. 展开更多
关键词 fan blade out transient trajectory design character structural fuse high bypass ratio TURBOfan
原文传递
Parametric study on the flutter sensitivity of a wide-chord hollow fan blade
10
作者 Xiaojie ZHANG Yanrong WANG +1 位作者 Weiyu CHEN Xianghua JIANG 《Chinese Journal of Aeronautics》 SCIE EI CAS CSCD 2022年第11期277-293,共17页
In recent years, the hollow fan blades have been widely used to meet the demand for light weight and good performance of the aero-engine. However, the relationship between the hollow structure and the aeroelastic stab... In recent years, the hollow fan blades have been widely used to meet the demand for light weight and good performance of the aero-engine. However, the relationship between the hollow structure and the aeroelastic stability has not been studied yet in the open literature. In this paper,it has been investigated for an H-shaped hollow fan blade. Before studying the flutter behavior, the methods of parametric modeling and auto-generation of Finite Element Model(FEM) are presented. The influence of the feature parameters on the vibration frequency and mode shape(as the input of flutter calculation) of the first three modes are analyzed by the Orthogonal Experimental Design(OED) method. The results show that the parameters have a more remarkable impact on the first torsional mode and thus it is concerned in the flutter sensitivity analysis. Compared with the solid blade, the minimum aerodynamic damping of the hollow blade decreases, indicating that the hollow structure makes the aeroelastic stability worse. For the parameters describing the hollow section, the rib number N has the greatest influence on the minimum aerodynamic damping, followed by the wall thickness W5. For the parameters in the height of hollow segment, the aerodynamic damping increases with the increase of parameters M1 and M2. This means that reducing the height of the hollow segment is helpful to improve the aeroelastic stability. Compared with the impact of parameters in hollow section, the variation of aerodynamic damping caused by the height of the hollow segment is small. 展开更多
关键词 Aerodynamic damping FLUTTER Hollow fan blade Hollow structure Orthogonal experimental design
原文传递
Motion Characteristic Analysis of a Parallel Mechanism with 2-DOF for Industrial Fan Blades' Scribing
11
作者 QIN Xian JIANG Yong-jian DENG Jia-ming 《International Journal of Plant Engineering and Management》 2013年第4期221-230,共10页
Abstract:With the application background of 16 inch industrial fan blades' scribing process, a simple and prac tical 2DOF parallel plane scribing device is proposed to replace the traditional manual scribing. The di... Abstract:With the application background of 16 inch industrial fan blades' scribing process, a simple and prac tical 2DOF parallel plane scribing device is proposed to replace the traditional manual scribing. The direct and inverse kinematics solutions, workspace and singular configuration of the mechanism are analyzed and solved. Some contour curve equations are fitted based on the data points which are measured by a three coordinate meas uring machine. According to the blade's contour curve, each input link's motion characteristic is obtained by u sing MATLAB, which provides a new way to realize blades' automatic scribing process technology. 展开更多
关键词 industrial fan blades parallel mechanism motion characteristic analysis MATLAB simulation a-nalysis
原文传递
Numerical Simulation of Axial Inflow Characteristics and Aerodynamic Noise in a Large-Scale Adjustable-Blade Fan 被引量:4
12
作者 Lin Wang Chunguo An +4 位作者 Nini Wang Yaming Ping Kun Wang Ming Gao Suoying He 《Fluid Dynamics & Materials Processing》 EI 2020年第3期585-600,共16页
Numerical simulation are conducted to explore the characteristics of the axial inflow and related aerodynamic noise for a large-scale adjustable fan with the installation angle changing from−12°to 12°.In suc... Numerical simulation are conducted to explore the characteristics of the axial inflow and related aerodynamic noise for a large-scale adjustable fan with the installation angle changing from−12°to 12°.In such a range the maximum static(gauge)pressure at the inlet changes from−2280 Pa to 382 Pa,and the minimum static pressure decreases from−3389 Pa to−8000 Pa.As for the axial intermediate flow surface,one low pressure zone is located at the junction of the suction surface and the hub,another is located at the suction surface close to the casing position.At the outlet boundary,the low pressure is negative and decreases from−1716 Pa to−4589 Pa.The sound pressure level of the inlet and outlet noise tends to increase monotonously by 11.6 dB and 7.3 dB,respectively.The acoustic energy of discrete noise is always higher than that of broadband noise regardless of whether the inlet or outlet flow surfaces are considered.The acoustic energy ratio of discrete noise at the inlet tends to increase from 0.78 to 0.93,while at the outlet it first decreases from 0.79 to 0.73 and then increases to 0.84. 展开更多
关键词 Adjustable blade axial flow fan variable installation angle condition axial static pressure aerodynamic noise
下载PDF
Effect of Tip-Blade Cutting on the Performance of Large Scale Axial Fan
13
作者 尹超 胡骏 +1 位作者 严伟 张晨凯 《Transactions of Nanjing University of Aeronautics and Astronautics》 EI CSCD 2015年第6期623-630,共8页
The effect of tip-blade cutting on the performance of a large scale axial fan was investigated using computational fluid dynamics(CFD)methods.Experiments verified the numerical simulations.The original fan was compare... The effect of tip-blade cutting on the performance of a large scale axial fan was investigated using computational fluid dynamics(CFD)methods.Experiments verified the numerical simulations.The original fan was compared with the one with tip-cutting in terms of dimensionless characteristic and aerodynamic performance in tip region under the conditions of the maximum efficiency point and near-stall point.The results showed that double leakage flow occurred in tip clearance at maximum efficiency point and spillage of leakage flow from leading edge occurred in tip-blade region at near-stall point for the both two fans;and that tip-cutting with 6% of blade height could reduce the intensity of tip-leakage vortex and increase flow capacity in tip blade region,and hold the stall margin almost the same as the original fan.The maximum efficiency of the fan with tip-cutting was improved by1%,and the ability of total pressure rising was obviously greater than the original fan. 展开更多
关键词 large axial fan tip-blade cutting numerical simulation tip-leakage vortex flow capacity
下载PDF
Numerical Study on Internal Flow of Small Axial Flow Fan with Splitter Blades
14
作者 Lifu Zhu Yingzi Jin +2 位作者 Yuzhen Jin Yanping Wang Li Zhang 《Open Journal of Fluid Dynamics》 2013年第2期75-80,共6页
The splitter blades are widely used in axial compressors and play an active role in the improvement of the overall performance of compressors. However, little research on the application of splitter blades to small ax... The splitter blades are widely used in axial compressors and play an active role in the improvement of the overall performance of compressors. However, little research on the application of splitter blades to small axial flow fans is conducted. This paper designs a splitter blade small axial flow fan (model B) with a small axial flow fan as the prototype fan (model A) by adding short blades at the second half part of the passageway among long blades of model A. The steady simulation for the two models was conducted with the help of RNG k-ε turbulence model provided by software Fluent, and static characteristics and internal flow characteristics of the two models were compared and analyzed. Results show that splitter blades can improve the unsteady flow in the small flow rate region and also have a positive role to increase static pressure rise and efficiency in the higher flow rate region. The variation of static pressure gradient on the meridian plane in model B is well-distributed. The static pressure on the blade surface of model B distributes more uniformly. Splitter blades can suppress the secondary flow from pressure side to suction side in the leading edge because the pressure difference between suction side and pressure side in model B is generally lower than that of model A. And it also can restrain the vortex shedding and flow separation, and further it may be able to get the aerodynamic noise lower because static pressure gradient on the blade surface is well-distributed and the vortex shedding is not developed. Therefore, the performance of the fan with splitter blades is better than that of the prototype fan. The findings of this paper can be a basis for the design of high performance small axial flow fans. 展开更多
关键词 SMALL AXIAL FLOW fan SPLITTER blade Internal FLOW Performance
下载PDF
Effects of circumferential configuration concerning splitter blade on the aerodynamic performance in a transonic axial fan
15
作者 薛亮 韩万金 《Journal of Harbin Institute of Technology(New Series)》 EI CAS 2010年第1期75-81,共7页
For a certain type of transonic axial fan, the flow field of a fan rotor with splitter blade was computed by numerical simulation, and the shape of the rotor was modified. The effects of different circumferential dist... For a certain type of transonic axial fan, the flow field of a fan rotor with splitter blade was computed by numerical simulation, and the shape of the rotor was modified. The effects of different circumferential distributions concerning the splitter cascades upon the aerodynamic performance were investigated. The studies show that the optimum splitter cascade is not very close to the suction side of main blade. The load between the main blade and the splitter blade can be soundly distributed in terms of the adjustment of circumferential position of the splitter blade. The best aerodynamic performance can be successfully obtained according to the optimum shape of the expanding fluid channel reasonably formed by the splitter blade and the main blade. 展开更多
关键词 transonic axial fan splitter blade shock wave flow loss compressor
下载PDF
钛合金包边复合材料风扇叶片的鸟撞数值仿真
16
作者 金峰 刘璐璐 +3 位作者 朱信颖 罗刚 赵振华 陈伟 《航空发动机》 北大核心 2024年第4期107-113,共7页
为降低鸟体撞击航空发动机中带钛合金包边树脂基复合材料风扇叶片的试验成本,开展了数值仿真研究,为钛合金包边在航空发动机风扇叶片上的应用提供参考和依据。对风扇叶片进行简化,采用ABAQUS有限元软件构建了鸟撞带钛合金包边和不带钛... 为降低鸟体撞击航空发动机中带钛合金包边树脂基复合材料风扇叶片的试验成本,开展了数值仿真研究,为钛合金包边在航空发动机风扇叶片上的应用提供参考和依据。对风扇叶片进行简化,采用ABAQUS有限元软件构建了鸟撞带钛合金包边和不带钛合金包边的风扇叶片模型,其中,钛合金包边和复合材料叶片之间用粘结界面单元进行粘接,研究了不同鸟体冲击角度和速度下2种风扇叶片的损伤。结果表明:在鸟体冲击速度相同时,随着冲击角度的增大,风扇叶片的损伤增大且能量吸收率提高,在冲击角度也相同时,带钛合金包边的风扇叶片损伤更小且能量吸收率更高;在鸟体冲击角度相同时,随着冲击速度的加快,风扇叶片的损伤增大且能量吸收率提高;在鸟体冲击下,粘结界面单元最终发生拉伸破坏,在低速度冲击下还会发生剪切损伤。 展开更多
关键词 复合材料 风扇叶片 钛合金包边 鸟撞 数值仿真 航空发动机
下载PDF
基于改进YOLOv8的风机桨叶缺陷检测算法
17
作者 李冰 张易牧 +2 位作者 魏乐涛 王月 翟永杰 《电子测量技术》 北大核心 2024年第13期89-99,共11页
叶片作为风力发电机组的重要部件,容易受到自然环境的影响,导致出现侵蚀、裂纹、胶衣脱落等损伤,从而影响风力发电效率和机组的安全运行。针对复杂环境下风机桨叶缺陷检测精度较低的问题,提出了一种改进YOLOv8的风机桨叶缺陷检测算法。... 叶片作为风力发电机组的重要部件,容易受到自然环境的影响,导致出现侵蚀、裂纹、胶衣脱落等损伤,从而影响风力发电效率和机组的安全运行。针对复杂环境下风机桨叶缺陷检测精度较低的问题,提出了一种改进YOLOv8的风机桨叶缺陷检测算法。通过对骨干特征提取网络中的单一模块SPPF融入LSKA注意力机制,以增强网络对于重要特征的关注度,提高模型的性能;其次,Neck部分采用加权双向特征金字塔Bi-FPN结构,并使用FasterBlock改进C2f模块,提出了Bi-YOLOv8-faster轻量级网络结构,增强模型多尺度特征融合能力,提高小目标检测精度;最后,采用辅助边框计算损失的Inner-IoU方法对损失函数进行优化,提高模型缺陷检测的准确率和泛化能力。通过对风机桨叶图像进行缺陷检测实验,结果表明,所提方法对缺陷检测的精确率提升了7.3%、mAP50提升了3.3%、参数量降低了27%。 展开更多
关键词 风机桨叶 YOLOv8 注意力机制 缺陷检测 Inner-IoU
原文传递
多翼离心风机蜗壳气动性能与出风均匀性优化设计
18
作者 刘江 沈春根 林传生 《排灌机械工程学报》 CSCD 北大核心 2024年第6期591-597,604,共8页
以某型号风暖浴霸吹风系统的多翼离心风机为研究对象,利用ANSYS Fluent 2020 R2对原型风机的出口风量与均匀度进行仿真分析,结果显示仿真与实测误差在5%以内,验证了用CFD数值模拟方法来优化浴霸多翼离心风机的可靠性.将蜗壳型线参数化,... 以某型号风暖浴霸吹风系统的多翼离心风机为研究对象,利用ANSYS Fluent 2020 R2对原型风机的出口风量与均匀度进行仿真分析,结果显示仿真与实测误差在5%以内,验证了用CFD数值模拟方法来优化浴霸多翼离心风机的可靠性.将蜗壳型线参数化,通过正交试验设计,针对蜗舌放置角α、蜗舌半径R、等角螺线常数A(蜗壳周向面积)与风轮移动距离L(蜗舌与叶轮间隙)4个因素,制定了16组参数组合方案并进行了CFD数值模拟,得到各方案的出口风量与均匀度,并由均值与极差分析确定了最优参数组合.通过数值计算结果可知,优化后的风机在蜗舌附近区域湍流强度减小,内部流动改善.测试结果显示,优化后的风机出口风量提升7.3%,均匀度提升4.5%,全压效率提升5.9%.显著提升了风暖浴霸离心风机的出风性能和出口风速分布均匀性,对提高风暖浴霸取暖效率和增强人体舒适性有重要意义. 展开更多
关键词 多翼离心风机 蜗壳 蜗舌 正交试验 CFD数值模拟
下载PDF
某钛合金宽弦空心风扇叶片共振特性仿真分析
19
作者 王宪 张昕喆 +1 位作者 张翔 李国举 《计算机仿真》 2024年第10期48-53,486,共7页
宽弦空心风扇叶片特有的空腔及加强筋结构,在大幅减轻叶片重量,降低整机载荷的同时,也更易使叶片在高速旋转过程中产生共振现象。为有效规避共振引起的叶片疲劳断裂、振动失效等问题,一般需要对叶片在不同转速下的共振特性进行系统分析... 宽弦空心风扇叶片特有的空腔及加强筋结构,在大幅减轻叶片重量,降低整机载荷的同时,也更易使叶片在高速旋转过程中产生共振现象。为有效规避共振引起的叶片疲劳断裂、振动失效等问题,一般需要对叶片在不同转速下的共振特性进行系统分析。为此,采用有限元方法对某型号航空发动机钛合金宽弦空心风扇叶片在不同转速下的强度和模态进行了仿真分析,并借助Campbell共振图进一步对其频率裕度进行了校核。研究结果表明:靠近叶片前缘的加强筋最易受共振影响而发生振动形变,转速在2900r/min-3800r/min区间时叶片具有良好的频率裕度。 展开更多
关键词 宽弦空心风扇叶片 强度分析 模态分析 频率裕度 有限元仿真
下载PDF
风机叶片新型耐磨超疏水涂层的防覆冰性能研究 被引量:1
20
作者 王宇辰 高志强 +4 位作者 贾建文 杜华云 卫欢 侯利锋 卫英慧 《材料保护》 CAS CSCD 2024年第4期56-62,共7页
风力发电机叶片在服役过程中经常会受到覆冰影响,超疏水材料由于其特殊的湿润性,在防冰领域具有较大的应用潜力。基于此,以风力发电机叶片为基底,在其表面旋涂由环氧树脂(EP)、聚二甲基硅氧烷(PDMS)和改性的SiO2等配制的无氟悬浮液,固... 风力发电机叶片在服役过程中经常会受到覆冰影响,超疏水材料由于其特殊的湿润性,在防冰领域具有较大的应用潜力。基于此,以风力发电机叶片为基底,在其表面旋涂由环氧树脂(EP)、聚二甲基硅氧烷(PDMS)和改性的SiO2等配制的无氟悬浮液,固化后制得耐磨防冰的超疏水试样。采用扫描电镜、红外光谱仪和接触角测量仪分别对超疏水涂层的微观形貌、成分组成和疏水性能进行研究。结果表明:超疏水涂层的接触角为166.65°,滚动角为2.5°。相比于无涂层风机叶片,涂层在-10℃和-15℃延长结冰时间40%左右,并且涂层结冰后冰层的粘结强度明显小于风机叶片的。涂层在800目砂纸上磨损10 m后接触角为150.5°。制备的耐磨超疏水涂层具有超疏水效果和良好的防冰性能。 展开更多
关键词 风机叶片 超疏水涂层 制备 防覆冰 耐磨性
下载PDF
上一页 1 2 65 下一页 到第
使用帮助 返回顶部