The Experts below are selected from a list of 132 Experts worldwide ranked by ideXlab platform

Gui Xing-min - One of the best experts on this subject based on the ideXlab platform.

  • Aerodynamic design and numerical simulation of a highly loaded transonic two-stage fan
    2011
    Co-Authors: Gui Xing-min
    Abstract:

    The design procedure and result of a highly loaded transonic two-stage fan for a variable cycle engine were presented.The selection of key parameters was discussed during the design procedure.The throughflow calculation and blade design were completed using the S2m streamsurface-based streamline curvature met hod and Arbitrary Camber lines blading method.The design strategies of swept rot ors and stators were adopted to improve the efficiency and stall margin of the f an.Three-dimensional computation results indicate that the design targets of the two-stage fan are achieved except for the adiabatic efficiency.The fan has rela tively high peak efficiencies above 80% rotating speed.

  • Aerodynamic design of a small centrifugal compressor
    2010
    Co-Authors: Gui Xing-min
    Abstract:

    An aerodynamic design of a small centrifugal compressor for some pilotless aircraft was presented in this paper.One-dimensional thermal calculation was conducted to configure the flow path.And based on two-dimensional through flow design,the required aerodynamic performance was obtained by adjusting the distribution of velocity circulation of the blade rows.Then three-dimensional blade airfoils can be got by Arbitrary Camber lines blading.At last,three-dimensional CFD(computational fluid dynamics) calculation was used to analyze the result of the aerodynamic design.All performance parameters of the centrifugal compressor meet the design requirement at design point.And the performance curves at all speeds are really flat.Therefor the work stability of the compressor have a fairly broad scope.

  • Optimization design of a small centrifugal compressor
    2010
    Co-Authors: Gui Xing-min
    Abstract:

    Optimization design of some small centrifugal compressor with a small stall margin was discussed in this paper.In the optimization design,a method called Arbitrary Camber lines blading design method was used for both axial and centrifugal compressors.The optimization design method,beginning with a through flow calculation,and in combination with Arbitrary Camber lines blading,applied three-dimensional computational fluid dynamics calculation to analyze the result of the optimization design.By changing the control properties of through flow design and Arbitrary blading,meridional flow passage and three-dimensional blades were gained satisfactorily.As a result,not only the stall margin has been increased,but also the stage performance of the compressor has been improved significantly.

  • A blading design method for axial/centrifugal compressor airfoils using Arbitrary Camber lines
    2009
    Co-Authors: Gui Xing-min
    Abstract:

    A blading design method for both axial and centrifugal compressor blades was discussed by using Arbitrary Camber lines.This method was based on through flow calculation.Three dimensional blades consistent with the result of through flow calculation can be obtained by modifying the distribution of velocity circulation.Meanwhile,it can control main blade/splitter blading and the shape of trailing edge of the airfoil.It has been applied to the design of compressor blades of some micro-engines,and fairly ideal airfoils are obtained.Also,this method can be used for optimization of compressor blades.

Gui Xingmin - One of the best experts on this subject based on the ideXlab platform.

Antonio Delgado - One of the best experts on this subject based on the ideXlab platform.

An Li-pin - One of the best experts on this subject based on the ideXlab platform.

  • Verification of an Innovative Blading Method by Planar Cascade Test
    Gas Turbine Experiment and Research, 2013
    Co-Authors: An Li-pin
    Abstract:

    The advantage and feasibility of a newly developed blade modeling method(BMAA) was validated by a planar cascade test compared with the former CDA method and the Arbitrary Camber lines method. The test results show that the transonic blade generated by the new method achieved better aerodynamic performance than CDA method; and the performance of supersonic blade is equal to that of Arbitrary Camber lines; the blade generated by the new method have higher efficiency and blade aerodynamic load which are superior to the conventional blade.

  • Innovative Blading Method Based on Calculating Geometry
    Gas Turbine Experiment and Research, 2013
    Co-Authors: An Li-pin
    Abstract:

    Using the free-form curve theory,an innovative blading method--BMAA was developed.Uni form B-spline and Bezier curve were chosen separately to realize the smart control of Camber line and thick ness.Considering the practicability and facility,four points were selected to design the curve of angle.In the end,BMAA,tailored airfoil and arb itrary Camber lines methods were adopted to design a single-stage compressor.The results show that the blade designed by new methods is better than tailored airfoil for super sonic/transonic blading design;and the blading performance is equal to that of Arbitrary Camber lines.In ad dition,the convenience of controlling and smoothness of airfoil are superior to that of Arbitrary Camber lines.

Shan Peng - One of the best experts on this subject based on the ideXlab platform.

  • Numerical aero-optimization method for three-dimensional compressor rotor with parameterized aerodynamic variables
    2010
    Co-Authors: Shan Peng
    Abstract:

    Employing the strategy of "experimental design+ response surface model + genetic algorithm",a response surface model code based on the artificial neural network and a genetic algorithm code were developed;and this paper established a numerical aero-optimization platform for three-dimensional(3-D) axial-flow compressor blade.This integral platform contains also the commonly used Arbitrary Camber line airfoil and blade formatting code and 3-D computational fluid dynamics solver.A fulfilled inverse-design of a zero-stage compressor rotor of a turbojet engine was optimized by this platform.The optimization object is to achieve the maximum adiabatic efficiency at the design point,while the mass flow rate and total pressure ratio are kept unchanged as the constraints.The relative flow-angle and the inner-blade deviation-angle are chosen separately as the independent-variables in two optimization cases.In order to directly couple the optimization method with the modern design system,the aerodynamic variables with physical meanings were chosen instead of the commonly used geometric variables as the optimization independent-variables.As compared with the original rotor,the adiabatic efficiencies of two optimal rotors increase by 0.82 and 0.73 percentage points,respectively.It shows that 3-D optimization method based on the aerodynamic variables has a good performance.