第四屆噴氣推進(jìn)與動力工程國際會議

內(nèi)容概要

《第4屆噴氣推進(jìn)與動力工程國際會議論文集》主要目的是總結(jié)或回顧近年來噴氣推進(jìn)與動力工程領(lǐng)域取得的主要進(jìn)展，促進(jìn)領(lǐng)域內(nèi)學(xué)者和專家之間廣泛交流，使之成為國內(nèi)外科技人員激情創(chuàng)新、合作奮進(jìn)的舞臺。會議交流使用的正式語言為英語。

書籍目錄

Contents Session A.Turbomachinery,Internal Flow and Acoustics The Numerical Simulation of Sand Trajectory in Fan Air Flow Channel of Turbo-fan Engine Effects of Adverse Pressure Gradient on the Maximum Values of Reynolds Stresses in a Turbulent Boundary Layer MA Wei,Ottavy Xavier,LU Li-peng,Leboeuf Francis (24) Prediction and Analysis of Distortion Inlet on Compressor Performance and Stability Using Three Dimensional Model Numerical Investigations on the Leakage Flow and Rotordynamic Characteristics of Labyrinth Seal Study of Small Flow Rate High Pressure Ratio Backswept Impeller Design A Model for Concentrated Vortices and an Unsteady Wake Model for Turbine Study on Counter-Flow Thrust Vecotring Nozzle Jet Attachment and Control Numerical Study of Cascade Self Noise The Influence of Axial Turbine Element Stage Stator/Rotor Axial Spacing on Flow Status and Performance Experimental Investigation of Novel Casing Treatment with Bias Flow Application and Optimization of Non-Axisymmetric End Wall in a High Pressure Turbine Minimizing Secondary Flow Losses in a High Pressure Turbine with Nonaxisymmetric Endwall Theoretical and Numerical Investigation of the Hydrodynamic Stability of the Planar Taylor-Culick Flow Experimental Investigation of Axial Velocity Density Ratio in Large Camber Compressor Cascade Optimization of Multi-Stage Axial Compressor Based on Stochastic Ranking Differential Evolution Algorithm PIV Investigation of Secondary Flows in a Low-Speed Axial Compressor Rotor Passage Performance Improvement of a Degraded Heavy Duty Gas Turbine Using CFD Design Tools Research of Coaxial Gas Ejector Numerical Research of the Best Depth and Location of the Circumferential Groove of Subsonic Numerical Simulation of Turbine Performance with Low Reynolds Number at High Altitude Numerical Simulation of Three-Dimensional Separated Flow in a Linear Compressor Cascade A Numerical Study of Active Flow Control for Low Pressure Turbine Blades Influence of Turbulence Modeling on the Secondary Flow Predicition 2D Euler-Based Inverse Method.Development,Verification and Application Session B:Heat and Mass Transfer 20 Years of Experiences f0r the Conjugate Heat Transfer Analysis 0f Convection-cooled Turbine Vanes Industrial Applications of Heat Transfer Enhancement.Review and Problem Heat Tranvafer Augmentation Technol Ogies for Internal Cooling of Turbine Components of Gas Turbine Engines Thermodynamics Characteristic of the Flow and Heat Transfer in Rotating Cavity …… Session C:Multiphase Flows,Reacting Flows and Combustion Session D:Advanced Materials,Structural Strength,Vibration and Reliability Session E:Propulsion Engine Design,Control and Health Management Session F:Other Topics Related to Jet Propulsion and Power Engineering

章節(jié)摘錄

版權(quán)頁：   插圖：   The turbine researchers are always trying toimprove the aerodynamic performance and reduce thelosses in turbines.A main source of losses is secondaryflow loss.Secondary flows involving cross flow andthree-dimensional separation phenomena contributesignificantly to a reduction in overall efficiency andsecondary losses increase as the aerodynamic dutyincreases or aspect ratio decreases.In a turbine bladepassage,a number of vertical flow features arepresented,which are collectively known as thesecondary flows.A comprehensive and detailed reviewof these is given by Sieverding. In the past years,a variety of methods have beendeveloped to reduce secondary flows.One of the mostactive approaches is non-axisymmetric end-wallprofiling,whose application in turbines has been provedto be effective in reducing secondary losses andimproving overall efficiency by many turbineresearchers.During the past decades,emergingcomputational fluid dynamics (CFD) capabilities havemade it possible to design more complex threedimensional non-axisymmetric end walls.Nonaxisymmetric end-wall profiling using such capabilitieswas initially proposed by Rose.His study wasaimed at controlling and equalizing the end-wall staticpressure field at the platform of trailing edge,in order toreduce the turbine disk coolant leakage flow.LaterHartland et al.and Ingram et al.investigatednon-axisymmetric end-wall profiling in the Durhamlinear cascade and showed that significant reduction ofsecondary losses was achievable.Brennan et al.andRose et al.demonstrated an increase in stageefficiency of 0.4 from computations and 0.59±0.25%from measurements.Duden et al.and Eymann etal.investigated the combined effects of end-wallcontouring and airfoil profiling.

編輯推薦

《第4屆噴氣推進(jìn)與動力工程國際會議論文集》編著者第四屆噴氣推進(jìn)與動力工程國際會議科學(xué)委員會、組織委員會。為促進(jìn)學(xué)科發(fā)展、國際交流合作以及人才培養(yǎng)，我院將于2012年9月10日～12日在西安舉辦第四屆噴氣推進(jìn)與動力工程國際會議（4thISJPPE）。會議由我院主辦，北航、南航和德國亞琛工業(yè)大學(xué)（RWTHAachenUniversity）協(xié)辦。

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