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Yang W.,Beihang University | Qiao L.,Beihang University | Zhang P.,China Aviation Industry Group Corporation
Proceedings of the World Congress on Intelligent Control and Automation (WCICA) | Year: 2010

Cutting aircraft structural parts needs to use high-performance modular tool system, the choice of insert grades to ensure process efficiency and quality as the key, now rely mainly on human experience and the tool vendor's recommendations to select, leading to job shop files and machine programming difficult to regulate. This paper presents insert grade options for SANDVIK tool application case: first select candidate grades matching processing requirements in rule-based reasoning (RBR), and then find preferred grade by use of Analytic Hierarchy Process (AHP) and fuzzy evaluations, the results and the actual processing of situation is similar, this method is expected to be applied in the advanced tool intelligent recommendation and tool operation training. © 2010 IEEE.

Fu W.-G.,Dalian Maritime University | Sun P.,Dalian Maritime University | Li L.-L.,China Aviation Industry Group Corporation | Pan R.-C.,China Aviation Industry Group Corporation
Reneng Dongli Gongcheng/Journal of Engineering for Thermal Energy and Power | Year: 2014

To conduct an experimental study of the last-stage sector-shaped cascade of a compressor, designed were controllable guide blades to simulate the speed and direction of the air flow at the inlet of the cascade. On this basis, the numerical simulation and test method were used to conduct a study of the aerodynamic characteristics of the blades and the law governing the distribution of the parameters of the air flow at the outlet of the guided blades was analyzed at various turning angles. It has been found that the numerical simulation results are in a relatively good agreement with the test ones. With the guided blades being designed rationally, the sector-shaped cascade test can replace the compressor stage test to study the performance and flow field configuration of the stator. During the test, the influence of the guide blade clearances forced the boundary layer to become thick and when the rotating angle was 0, +2 and +4 degrees respectively, the location of the maximal Mach number at the outlet was eventually elevated to 25% of the blade height towards the pitch diameter while that was located at 15% of the blade height when a numerical simulation was conducted due to an insufficient consideration of the change in the boundary layer.

Ma C.-Y.,China Aviation Industry Group Corporation | Hou M.-J.,China Aviation Industry Group Corporation | Yang L.,China Aviation Industry Group Corporation | Liang J.,China Aviation Industry Group Corporation
Reneng Dongli Gongcheng/Journal of Engineering for Thermal Energy and Power | Year: 2014

In the light of such a problem of the PIV technology encountered in measuring the flow filed of a highly subsonic plane cascade in a shock type wind tunnel as tracer particle placement, by using a high pressure atomization type particle generator and a spreader installed before the pressure stabilizer section, the authors had effectively forced the tracer particles uniformly blended with the main stream and successfully measured the velocity fields in the flow passages and the wake of a diffusion cascade at the design attack angle with two-dimensional velocity vector fields being obtained in a range of Mach number at the inlet from 0.3 to 0.73. To verify the reliability of the PIV test results, the flow field of the cascade was numerically simulated. A comparison of the results shows that the two-dimensional velocity vector fields measured in the mid-section of the cascade by using the PIV technology can rationally reflect the flow configuration in the flow passages and the wake of the blades and are relatively close to the numerical simulation results. For the flow fields in a trans-sonic or supersonic cascade at a large attack angle, it is necessary to take account of the influence of the pollution to the wall surfaces caused by the tracer particles on the measurements. On this basis, the PIV technology put forward by the authors can be applied for measurement of the flow fields in a high subsonic cascade based on the absorption type and composite jet flow etc. flow control technologies.

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