Practical Use of Three-Dimensional Inverse Method for Compressor Blade Design

1999 ◽  
Vol 121 (2) ◽  
pp. 321-325 ◽  
Author(s):  
S. Damle ◽  
T. Dang ◽  
J. Stringham ◽  
E. Razinsky
Keyword(s):  
Inverse Method ◽  
Three Dimensional ◽  
Blade Design ◽  
Original Design ◽  
Design Modification ◽  
Simple Modification ◽  
Wide Range ◽  
Flow Quantity ◽  
Operating Points ◽  
Better Than

The practical utility of a three-dimensional inverse viscous method is demonstrated by carrying out a design modification of a first-stage rotor in an industrial compressor. In this design modification study, the goal is to improve the efficiency of the original blade while retaining its overall aerodynamic, structural, and manufacturing characteristics. By employing a simple modification to the blade pressure loading distribution (which is the prescribed flow quantity in this inverse method), the modified blade geometry is predicted to perform better than the original design over a wide range of operating points, including an improvement in choke margin.

scholarly journals Practical Use of 3D Inverse Method for Compressor Blade Design

1998 ◽  
Author(s):  
S. Damle ◽  
T. Dang ◽  
J. Stringham ◽  
E. Razinsky
Keyword(s):  
Inverse Method ◽  
Blade Design ◽  
Pressure Loading ◽  
Original Design ◽  
Design Modification ◽  
Simple Modification ◽  
Wide Range ◽  
Flow Quantity ◽  
Operating Points ◽  
Better Than

The practical utility of a 3D inverse viscous method is demonstrated by carrying out a design modification of a first-stage rotor in an industrial compressor. In this design modification study, the goal is to improve the efficiency of the original blade while retaining its overall aerodynamic, structural and manufacturing characteristics. By employing a simple modification to the blade pressure loading distribution (which is the prescribed flow quantity in this inverse method), the modified blade geometry is predicted to perform better than the original design over a wide range of operating points, including an improvement in choke margin.

Evaluation and Analysis of the Onlay Patellar Component in Total Knee Arthroplasty

2010 ◽  
Vol 97-101 ◽  
pp. 3773-3776 ◽  
Author(s):  
Chien Wei Liu ◽  
Chia Chi Lo ◽  
Ching Sung Wang ◽  
Chen Tung Yu
Keyword(s):  
Total Knee Arthroplasty ◽  
Knee Arthroplasty ◽  
Three Dimensional ◽  
Element Model ◽  
Clinical Results ◽  
Original Design ◽  
Design Modification ◽  
Patellar Component ◽  
Significant Difference ◽  
Total Knee

Complications in total knee arthroplasty (TKA), which may include the inaccuracy of the implantation and the poor component design, can cause major failures in the TKA. Therefore, the present investigation studies the onlay knee implants commonly used clinically to find the major causes of the damage to artificial patella by the computer aided analysis of the three-dimensional finite element model of the artificial patello-femoral joint built through reverse engineering. Results showed that although a significant difference is found in the condition and the state of the stress distribution generated as the patello-femoral joint changes with the flexion of the knees, this variation is still within the tolerable range; but the patellar lateral tilt is something that caught our attention. Furthermore, through the comparison between the study and the clinical results, this investigation concludes that the bone cement on the implant interface is the major cause for the breaking of the pegs, and is not related to the original design of the patella. This study also discovers that slight design modification on the parts of commonly used artificial joints may effectively reduce surgical failure rate; therefore, a more robust design configuration for patellar pegs is proposed.

scholarly journals The Science and Engineering of Stem Cell–Derived Organoids-Examples from Hepatic, Biliary, and Pancreatic Tissues

2020 ◽  
Author(s):  
Ogechi Ogoke ◽  
Mitchell Maloy ◽  
Natesh Parashurama
Keyword(s):  
Stem Cell ◽  
Cellular Therapy ◽  
Disease Modeling ◽  
Historical Context ◽  
Three Dimensional ◽  
Self Organization ◽  
Wide Range ◽  
Clinical Interest ◽  
And Function ◽  
Better Than

Organoid engineering promises to revolutionize medicine with wide ranging applications of scientific, engineering, and clinical interest, including precision and personalized medicine, gene editing, drug development, disease modeling, cellular therapy, and a basic understanding of human development. Organoids are a three-dimensional (3D), miniature, caricature of a target organ, are initiated with stem/progenitor cells, and are extremely promising tools to model organ function. The biological basis for organoids is that they foster stem cell-self renewal, differentiation, and self-organization, recapitulating tissue structure or function better than 2D systems. In this review, we first discuss the importance of epithelial organs and the general properties of epithelial cells to provide context for the liver, pancreas, and gall bladder and rationale for organoid cultures. Next, we develop a general framework to understand self-organization, tissue hierarchy, and organoid cultivation. For each of these areas, we provide historical context, and review both a wide range of biological and/or biophysical/mathematic perspectives that enhances understanding of organoids. Next, we review existing techniques and progress in hepatobiliary and pancreatic organoid engineering. To do this, we review organoids from both primary tissues, cell lines, and stem cells, and introduce engineering studies when applicable. Noninvasive assessment of 1 organoids can reveal underlying biology and enable improved assays for growth, metabolism, and function. Applications of organoid for cell therapy are also discussed. Taken together, we establish a broad strong scientific foundation for organoids and provide an in-depth review of hepatic, biliary and pancreatic organoids.

scholarly journals Experimental Investigation on Ducted Counter-Rotating Axial Flow Fans

2011 ◽  
Author(s):  
Hussain Nouri ◽  
Florent Ravelet ◽  
Farid Bakir ◽  
Christophe Sarraf
Keyword(s):  
Inverse Method ◽  
Pressure Fluctuations ◽  
Axial Flow ◽  
Axial Distance ◽  
Large Patch ◽  
Rotation Rates ◽  
Wall Pressure Fluctuations ◽  
Wide Range ◽  
High Efficient ◽  
Operating Points

An experimental study on counter-rotating axial-flow fans was carried out. The fans of diameter D = 375 mm were designed using an inverse method. The counter-rotating fans operate in a ducted-flow configuration and the overall performances are measured in a normalized test bench. The rotation rate of each fan is independently controlled. The axial spacing between the fans can vary from 10 to 50 mm by steps of 10 mm. The results show that the efficiency is strongly increased compared to a conventional rotor or to a rotor-stator stage. The effects of varying the rotation rates ratio on the overall performances are studied and show that the system is highly efficient on a wide range of flow-rates and pressure rises. However, the change of the axial distance between rotors from 10 to 50 mm does not seem to change the overall performances. This system has thus a very flexible use, with a large patch of high efficient operating points in the parameter space. Further local studies including velocity measurements and wall-pressure fluctuations in the space between the rotors are needed to better understand the interactions between the rotors and to optimize the system.

A Three-Dimensional Inverse Method for Turbomachinery: Part II—Experimental Verification

1990 ◽  
Vol 112 (3) ◽  
pp. 355-361 ◽  
Author(s):  
J. E. Borges
Keyword(s):  
Flow Velocity ◽  
Experimental Verification ◽  
Inverse Method ◽  
Three Dimensional ◽  
Inverse Technique ◽  
Low Speed ◽  
Static Efficiency ◽  
Radial Inflow Turbine ◽  
Rotor Loss ◽  
Better Than

The performance of an impeller of a low-speed radial-inflow turbine, designed using a three-dimensional inverse technique, was evaluated experimentally. This performance was compared with that achieved by a rotor typical of the present technology. Besides measuring overall quantities, in special efficiency, some traverses of flow velocity were carried out. The results of the tests showed that the new design had a peak total-to-static efficiency 1.4 points better than the conventional build. The traverses indicated that the level of swirl at exhaust of the new impeller was only half as big as that for the conventional rotor, in spite of the fact that both impellers were designed to have zero swirl at outlet. It is also shown that the rotor loss for the new impeller is considerably lower than for the conventional wheel. This research points to the desirability of using a three-dimensional inverse method for the design of turbomachines with significant three-dimensional flows.

Direct Constrained Computational Fluid Dynamics Based Optimization of Three-Dimensional Blading for the Exit Stage of a Large Power Steam Turbine

2002 ◽  
Vol 125 (1) ◽  
pp. 385-390 ◽  
Author(s):  
P. Lampart ◽  
S. Yershov
Keyword(s):  
Steam Turbine ◽  
Mass Flow Rate ◽  
Mass Flow ◽  
Flow Rate ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Steam Turbines ◽  
Original Design ◽  
Large Power ◽  
Wide Range

The paper describes results of direct constrained optimization using Nelder-Mead’s method of deformed polyhedron and a Reynolds-averaged Navier-Stokes (RANS) solver to optimize the shape of three-dimensional blading for the exit stage of a large power steam turbine. The computations of the flowfield in the stator and rotor are compressible, viscous, and three-dimensional. Turbulence effects are taken into account using the modified model of Baldwin-Lomax. The objective function is the stage efficiency, with the exit energy considered a loss, and with constraints imposed on the mass flow rate in the form of a penalty function if the mass flow rate falls beyond the required range. The blade sections (profiles) are assumed not to change during the optimization. Two optimization tasks are reported in this paper, first—optimizing the stator straight and compound circumferential lean, and also stator and rotor stagger angles to keep the flow rate unchanged, giving a total number of optimized parameters equal to 5; second—optimizing the stator straight and compound axial sweep, also with stator and rotor stagger angles, also giving five optimized parameters. The process of optimization is carried out for a nominal load; however, due to the fact that exit stages of steam turbines operate over a wide range of flow rates away from the nominal conditions, the original and final geometries are also checked for low and high loads. The process of optimization gives new designs with new three-dimensional stacking lines of stator blades, and with significantly increased efficiencies, compared to the original design, at least for a larger part of the assumed range of load.

Optimum Aerodynamic Design of Centrifugal Compressor Impeller Using an Inverse Method Based on Meridional Viscous Flow Analysis

2017 ◽  
Author(s):  
Nobuhito Oka ◽  
Masato Furukawa ◽  
Kazutoyo Yamada ◽  
Sasuga Itou ◽  
Seiichi Ibaraki ◽  
...  
Keyword(s):  
Viscous Flow ◽  
Optimum Design ◽  
Inverse Method ◽  
Design Method ◽  
Flow Analysis ◽  
Three Dimensional ◽  
Blade Design ◽  
Aerodynamic Design ◽  
Compressor Impeller ◽  
Optimum Aerodynamic

An optimum aerodynamic design method for centrifugal compressor impeller has been developed. The present optimum design method is using a genetic algorithm (GA) and a two-dimensional inverse blade design method based on a meridional viscous flow analysis. In the meridional viscous flow analysis, an axisymmetric viscous flow is numerically analyzed on a two-dimensional meridional grid to determine the flow distribution around the impeller. Full and splitter blade effects to the flow field are successfully evaluated in the meridional viscous flow analysis by a blade force modeling. In the inverse blade design procedure, blade loading distribution is given as the design variable. In the optimization procedure, the total pressure rise and adiabatic efficiency obtained from the meridional viscous flow analysis are employed as objective functions. Aerodynamic performance and three-dimensional flow fields in the Pareto-optimum design and conventional design cases have been investigated by three-dimensional Reynolds averaged Navier-Stokes (3D-RANS) and experimental analyses. The analyses results show performance improvements and suppressions of flow separations on the suction surfaces in the optimum design cases. Therefore, the present aerodynamic optimization using the inverse method based on the meridional viscous flow analysis is successfully achieved.

3D Inverse Method for Turbomachine Blading With Splitter Blades

2000 ◽  
Author(s):  
X. Qiu ◽  
T. Dang
Keyword(s):  
Shock Wave ◽  
Inverse Method ◽  
Navier Stokes ◽  
Blade Design ◽  
Design Modification ◽  
Blade Row ◽  
Stator Blade ◽  
Control Of Flow ◽  
And Control

The use of a full 3D and viscous inverse method for turbomachine blading with splitter blades is demonstrated by carrying out a design modification of a transonic axial stator blade row with splitter blades. In this design modification study, the goal is to improve the aerodynamics of the full blade and the splitter blade, including weakening of shock wave and control of flow incidence. The improved blade design is “validated” using a well-known 3D Navier-Stokes analysis solver.

Design Modification of Rotor 67 by 3D Inverse Method — Inviscid-Flow Limit

1997 ◽  
Author(s):  
T. Q. Dang ◽  
A. C. Nerurkar ◽  
D. R. Reddy
Keyword(s):  
Inverse Method ◽  
Thickness Distribution ◽  
Inviscid Flow ◽  
Blade Surface ◽  
Pressure Loading ◽  
Current Version ◽  
Original Design ◽  
Design Modification ◽  
Pressure Distributions ◽  
Flow Limit

A design modification of Rotor 67 is carried out with a full 3D inverse method. The blade camber surface is modified to produce a prescribed pressure loading distribution, with the blade tangential thickness distribution and the blade stacking line at midchord kept the same as the original Rotor 67 design. Because of the inviscid-flow assumption used in the current version of the method, Rotor 67 geometry is modified for use at a design point different from the original design value. In the subsonic section, smooth pressure loading shapes generally produce blades with well-behaved blade surface pressure distributions. In the supersonic section, this study shows that the strength and position of the passage shock correlate with the characteristics of the blade pressure loading shape. In general, “smooth” prescribed blade pressure loading distributions generate blade designs with reverse cambers which have the effect of weakening the passage shock.

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