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Optimum Profiles of endwall contouring for Enhanced Net Heat Flux Reduction and Aerodynamic Performance

Journal of Harbin Institute of Technology(New Series) 2024年第2期31卷 80-92页

作者： Arjun K S Tide P S Biju N Division of Mechanical Engineering School of EngineeringCochin University of Science&TechnologyKalamassery 682022India

Successfully utilized non-axisymmetric endwalls to enhance turbine efficiencies(aerodynamic and turbine inlet temperatures)by controlling the characteristics of the secondary flow in a blade *** is accomplished by steady-state numerical hydrodynamics and deep knowledge of the field of *** of the interaction between mainstream and purge flow contributing supplementary losses in the stage,non-axisymmetric endwalls are highly susceptible to the inception of purge flow exit compared to the flat and any advantage rapidly *** conclusions reveal that the supreme endwall pattern could yield a lowering of the gross pressure loss at the design stage and is related to the size of the top-loss location being productively *** has led to diminished global thermal exchange lowered in the passage of the vane *** reverse flow adjacent to the suction side corner of the endwall is migrated farther from the vane surface,as the deviated pressure spread on the endwall accelerates the flow and progresses the reverse flow core still *** depleted association between the tornado-like vortex and the corner vortex adjacent to the suction side corner of the endwall is the dominant mechanism of control in the contoured end *** this publication,we show that the non-axisymmetric endwall contouring by selective numerical shape change method at most prominent locations is advantageous in lowering the thermal load in turbines to augment the net heat flux reduction as well as the aerodynamic performance using multi-objective optimization.

关键词： endwall contouring turbine vane heat transfer phantom cooling coolant injection net heat flux reduction aerodynamic performance

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Optimization of endwall contouring in axial compressor S-shaped ducts

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Chinese Journal of Aeronautics 2015年第4期28卷 1076-1086页

作者： Jin Donghai Liu Xiwu Zhao Weiguang Gui Xingmin School of Energy and Power Engineering Beihang University AVIC Aviation Powerplant Research Institute

This paper presents a numerical investigation of the potential aerodynamic benefits of using endwall contouring in a fairly aggressive duct with six struts based on the platform for endwall design *** platform is constructed by integrating adaptive genetic algorithm（AGA）, design of experiments（DOE）, response surface methodology（RSM） based on the artificial neural network（ANN）, and a 3D Navier–Stokes *** visual analysis method based on DOE is used to define the design space and analyze the impact of the design parameters on the target function（response）.Optimization of the axisymmetric and the non-axisymmetric endwall contouring in an S-shaped duct is performed and evaluated to minimize the total pressure *** optimal ducts are found to reduce the hub corner separation and suppress the migration of the low momentum *** non-axisymmetric endwall contouring is shown to remove the separation completely and reduce the net duct loss by 32.7%.

关键词： Adaptive genetic algorithm(AGA) Artificial neural network(ANN) Corner separation Design of experiments(DOE) endwall contouring Optimization Response surfacemethodology (RSM) S-shaped duct

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endwall aerodynamic losses from turbine components within gas turbine engines

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Propulsion and Power Research 2017年第1期6卷 1-14页

作者： Phil Ligrani Geoffrey Potts Arshia Fatemi Eminent Scholar in Propulsion Professor of Mechanical and Aerospace EngineeringPropulsion Research CenterDepartment of Mechanical and Aerospace EngineeringUniversity of Alabama in Huntsville5000 Technology DriveOlin B.King Technology Hall S236HuntsvilleAlabama 35899USA Aero/Thermal&Heat Transfer Solar TurbinesInc.2200 Pacific HighwayP.O.Box 85376Mail Zone C-9San DiegoCalifornia 92186-5376USA Robert Bosch GmbH(CR/ARF2) Robert Bosch Central Research 130-1Robert Bosch Campus 1Renningen 71272Germany

A survey of research on aerodynamic loss investigations for turbine components of gas tuibine engines is *** and numerically predicted results are presented from investigations undertaken over the past 65 plus *** particular interest are losses from the development of secondary flows from airfoil/endwall *** most important of the airfoilAmdwall secondary flows are passage vortices,counter voitices,and corner *** structure and development of these secondaiy flows are described as they affect aerodynamic perfonnance within and downstream of turbine passage flows in compressible,high speed flows with either subsonic or transonic Mach number distributions,as well as within low-speed,incompressible *** discussed are methods of endwall contouring,and its consequences in regard to airfoil/endwall secondary flows.

关键词： Aerodynamic losses Gas turbine engines Turbine components Airfoil/endwall interactions Secondary flows Vorticity endwall contouring

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