Shape optimization of transonic compressor blade using quasi-three-dimensional flow physics

AIAA Journal ◽  
2002 ◽  
Vol 40 ◽  
pp. 389-391
Author(s):  
J. Chung ◽  
K. D. Lee
Keyword(s):  
Shape Optimization ◽  
Three Dimensional ◽  
Compressor Blade ◽  
Three Dimensional Flow ◽  
Flow Physics ◽  
Transonic Compressor ◽  
Dimensional Flow

Multi-dimensional limiting process for three-dimensional flow physics analyses

2008 ◽  
Vol 227 (12) ◽  
pp. 6001-6043 ◽  
Author(s):  
Sung-Hwan Yoon ◽  
Chongam Kim ◽  
Kyu-Hong Kim
Keyword(s):  
Three Dimensional ◽  
Three Dimensional Flow ◽  
Flow Physics ◽  
Dimensional Flow

Quantitative Density Visualization in a Transonic Compressor Rotor

1977 ◽  
Vol 99 (3) ◽  
pp. 460-475 ◽  
Author(s):  
A. H. Epstein
Keyword(s):  
Boundary Layer ◽  
Three Dimensional ◽  
Imaging Systems ◽  
Three Dimensional Flow ◽  
Transonic Compressor ◽  
Dimensional Flow ◽  
Compressor Rotor ◽  
Density Maps ◽  
Shock System ◽  
High Work

The flow in a 59-cm dia high work, transonic compressor rotor has been visualized using a fluorescent gas, 2,3, butanedione, as a tracer. The technique allows the three-dimensional flow to be imaged as a set of distinct planes. Quantitative static density maps were obtained by correcting the images for distortion and nonlinearities introduced by the illumination and imaging systems. These images and maps were used to analyze the three-dimensional nature of the blade’s boundary layer and shock system.

Efficiency Enhancement by Shape Optimization of Centrifugal Fan Installed in Refuse Collecting System

2009 ◽  
Author(s):  
Choon-Man Jang ◽  
Sang-Yoon Lee ◽  
Sang-Ho Yang
Keyword(s):  
Shape Optimization ◽  
Response Surface ◽  
Response Surface Method ◽  
Three Dimensional ◽  
Design Flow ◽  
Centrifugal Fan ◽  
Three Dimensional Flow ◽  
Dimensional Flow ◽  
Surface Method ◽  
Collecting System

Shape optimization in the design of turbomachinery based on the three-dimensional flow analysis has been developed remarkably in recent years with the rapid enhancement of computational power. In the present study, optimal design of a centrifugal fan installed in refuse collecting system has been performed using response surface method and three-dimensional Navier-Stokes analysis to increase fan efficiency. The centrifugal fan is used to increase suction pressure for the moving of a waste through the pipe line of the system. Two design variables, which are used to define the shape of an inlet guide, are introduced to increase the efficiency of the fan. In the shape optimization using the response surface method, data points for response evaluations are selected, and linear programming method is used for an optimization on a response surface. To analyze three-dimensional flow field in the centrifugal fan, general analysis code, CFX, is employed in the present work: SST turbulence model is employed to estimate the eddy viscosity. Unstructured grids are used to represent a composite grid system including blade, casing and inlet guide. Throughout the shape optimization of a centrifugal fan, the fan efficiency is successfully increased by decreasing local losses in the blade passage. The result of shape optimization shows that the efficiency of the optimized shape at the design flow condition is enhanced by 1.42% based on the reference fan. It is found that recirculation flow region of optimum one is relatively small compared to the reference one. The reduction of recirculation region can be decreased the shaft power of an impeller, thus it can be increased the efficiency of the fan.

Using Sweep and Dihedral to Control Three-Dimensional Flow in Transonic Stators of Axial Compressors

2000 ◽  
Vol 123 (1) ◽  
pp. 40-48 ◽  
Author(s):  
V. Gu¨mmer ◽  
U. Wenger ◽  
H.-P. Kau,
Keyword(s):  
Numerical Analysis ◽  
High Speed ◽  
Three Dimensional ◽  
Navier Stokes ◽  
Three Dimensional Flow ◽  
Axial Compressors ◽  
Transonic Compressor ◽  
Dimensional Flow ◽  
Boundary Layer Development ◽  
Radial Loading

The paper describes an advanced three-dimensional blading concept for highly loaded transonic compressor stators. The concept takes advantage of the aerodynamic effects of sweep and dihedral. To the knowledge of the authors this is the first approach reported in the open literature that combines those two basic types of lean in an engine-worthy aerofoil design. The paper makes a contribution to the understanding of the endwall effect of both features with special emphasis put on sweep. The advanced three-dimensional blading concept was applied to an Engine Section Stator (ESS) of an aero-engine fan. In order to demonstrate how three-dimensional flow can be controlled, numerical analysis of the flow structure in a conventional and an advanced stator configuration was performed using a three-dimensional Navier–Stokes solver. The numerical analysis showed the advanced blade improving both radial loading distribution and the three-dimensional endwall boundary layer development. In particular, a strong hub corner stall could be largely alleviated. High-speed rig testing of the advanced ESS confirmed the concept and showed good qualitative agreement between measurement and prediction. The work presented was closely linked to the development of the BR710 engine on which the advanced ESS is in service today.

Shape Optimization of High-Speed Axial Compressor Blades Using 3D Navier-Stokes Flow Physics

2001 ◽  
Author(s):  
June Chung ◽  
Jeonghwan Shim ◽  
Ki D. Lee
Keyword(s):  
Stokes Flow ◽  
Design Method ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Navier Stokes ◽  
Three Dimensional Flow ◽  
Compressor Blades ◽  
Flow Physics ◽  
Dimensional Flow ◽  
Blade Section

A CFD-based design method for transonic axial compressor blades was developed based on three-dimensional Navier-Stokes flow physics. The method starts with a three-dimensional flow analysis of an initial blade, followed by the sectional design optimization performed on a grid plane at a span station with spanwise flux components held fixed. This approach allows the sectional design to include the three-dimensional effects in compressor flows and thus overcome the difficulties associated with the use of quasi-three-dimensional flow physics in sectional designs. The “sectional three-dimensional” analysis at a span station, regardless of the initial flow condition, produced a flow solution nearly identical to the three-dimensional flow solution at the span station. After the validation of the sectional three-dimensional analysis, the developed design method was successfully applied to multiple span stations of NASA Rotor 37 blade in the inverse mode of finding a target geometry corresponding to a specified target pressure distribution. The method was also applied to optimize the adiabatic efficiencies of the blade section of Rotor 37 at 70 percent span station. The design results from two design attempts with different initial geometry indicate that there is not a lot of room for improvement for the blade section of Rotor 37 at 70 percent span station, but the present design method is capable of producing a large performance gain for a blade with lower efficiency.

Sign in / Sign up

Export Citation Format

Share Document