Investigation on drag reduction performance of aero engine blade with micro-texture

2018 ◽  
Vol 72 ◽  
pp. 380-396 ◽  
Author(s):  
Chen Zhang ◽  
Koirala Saurav Bijay
Keyword(s):  
Drag Reduction ◽  
Aero Engine ◽  
Engine Blade

Bionic microstructure on titanium alloy blade with belt grinding and its drag reduction performance

2020 ◽  
pp. 095440542094974
Author(s):  
Guijian Xiao ◽  
Yi He ◽  
Yun Huang ◽  
Shui He ◽  
Wenxi Wang ◽  
...  
Keyword(s):  
Titanium Alloy ◽  
Drag Reduction ◽  
Cfd Simulation ◽  
Dynamic Performance ◽  
Belt Grinding ◽  
Grinding Method ◽  
Aero Engine ◽  
Engine Blade ◽  
Bionic Structure ◽  
Set Up

Researches show that surface with bionic structure plays an important role in improving the aerodynamic performance on aero engine parts. Belt grinding, a popular method to process titanium alloy parts such as aero-engine blade, is also found that it can be used to obtain bionic microstructure through special grinding method and parameters. In order to explore the performance of bionic microstructure processed by belt grinding and its effects on airflow dynamics, several groups of simulation and an experiment are carried out in this paper. Firstly, the mechanism of drag reduction of bionic microstructure is discussed. It shows that the effect of drag reduction of bionic microstructure is related to protrusion height, which is related to the shape and size of the bionic microstructure. Then, three groups of typical belt grinding bionic microstructure are set up. In addition, the drag reduction values are calculated in CFD simulation. The results are analyzed and discussed. Further, to verify the airflow dynamics of drag reduction of belt grinding bionic microstructure, an experiment of aero-engine blade is carried out. Finally, the effects of airflow dynamic performance of blade with belt grinding bionic microstructure are obtained in CFD simulation. In general, the shape of wave ribs, compared to V-ribs and trapezoidal ribs, has the best performance in drag reduction. To a certain extent, the improvement of airflow dynamic performance is higher with the increasing of the size of bionic microstructure, which suggests lower feed rate and higher grinding pressure for bionic structure.

Fabrication and EDM Corrosion Resistance of Copper Electroforming Layer on Tube Electrode for Aero-Engine Blade Cooling Hole in EDM Process

2018 ◽  
Vol 764 ◽  
pp. 133-141 ◽  
Author(s):  
Zhi Yong Li ◽  
Qing Wei Cui ◽  
Bin Chen ◽  
Ji Xu ◽  
Hun Guo
Keyword(s):  
Corrosion Resistance ◽  
Loss Rate ◽  
Pure Copper ◽  
Blade Cooling ◽  
Tube Electrode ◽  
Aero Engine ◽  
Engine Blade ◽  
Cooling Hole ◽  
Edm Process ◽  
Main Material

The process parameters of fundamental electroforming solution were optimized firstly. Furthermore, some pure copper electroforming samples were prepared in the condition of different nana La2O3 addition quantity. Three main material properties evaluated. In addition, the EDM machining experiments were conducted to verify the characteristics of electrical corrosion resistance resulting from the prepared copper tube electroforming samples for cooling hole of Inconel718 nickel alloy. EDM experimental results demonstrate that copper electroforming layer with grain size 15.9μm, microhardness 98.2HV, with 1.2g/L addition quantity of nana La2O3, and its electrode loss rate decrease 13.29% and 7.26% than pure copper and copper electroforming layer without nana La2O3 addition respectively.

Roughness modeling for polishing an aero-engine blade with an abrasive cloth wheel

2020 ◽  
Vol 34 (8) ◽  
pp. 3353-3361
Author(s):  
Chao Xian ◽  
Yaoyao Shi ◽  
Xiaojun Lin ◽  
De Liu
Keyword(s):  
Aero Engine ◽  
Engine Blade

scholarly journals Surface Fitting for non-Grid Data from in-Situ Measuring Systems of Aero-engine Blade

2020 ◽  
Vol 206 ◽  
pp. 03023
Author(s):  
Qing Mao ◽  
Sen Wang ◽  
Shugui Liu
Keyword(s):  
Dynamic Performance ◽  
Surface Fitting ◽  
Data Conversion ◽  
Machining Accuracy ◽  
Nurbs Surface ◽  
Grid Data ◽  
Measuring Systems ◽  
Aero Engine ◽  
Engine Blade

High machining accuracy of aero-engine blade largely determines the carrying capacity, endurance, acceleration and the dynamic performance of the aero-engine, so a reliable machining error inspection and evaluation technique is imperative. In order to give a reliable error evaluation, the non- uniform rational B-spline (NURBS) technique is adopted to reconstruct the surface within a specified accuracy. Usually, data points measured from aero-engine blade are non-grid data in situ measuring systems. To overcome the difficulty of NURBS surface fitting from non-grid data, a new method based on data conversion is proposed, in which chord length parameterization and uniform parameter sampling are combined together to realize the data convertation, and subsequently hierarchical fitting strategy is applied to finish the NURBS surface reconstruction. The way proposed for data conversion is easy to realize, and by which gemetrical features of original measured data are also reserved well, which make the whole method outstanding in low time cost. Experimental results show that the method is fast, effective. The source code has been implemented in VC++, while the resulting pictures are constructed in Matlab with the obtained control points, knot vectors, and the orders.

Analysis of Aero-engine Blade Surface Laser Point Cloud 3D Reconstruction Error

2018 ◽  
Vol 47 (5) ◽  
pp. 512002
Author(s):  
孙彬 SUN Bin ◽  
杜虎兵 DU Hu-bing ◽  
王建华 WANG Jian-hua ◽  
李兵 LI Bing
Keyword(s):  
3D Reconstruction ◽  
Point Cloud ◽  
Reconstruction Error ◽  
Blade Surface ◽  
Aero Engine ◽  
Engine Blade ◽  
Surface Laser
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