Paper 6: Recent Developments in the Aerodynamic Design of Axial Flow Compressors

1968 ◽  
Vol 183 (14) ◽  
pp. 50-58
Author(s):  
J. P. Gostelow ◽  
J. H. Horlock ◽  
H. Marsh
Keyword(s):  
Computer Aided Design ◽  
Axial Flow ◽  
Meridional Flow ◽  
Streamline Curvature ◽  
Wall Boundary Layer ◽  
Through Flow ◽  
The Matrix ◽  
Recent Developments ◽  
Flow Compressor ◽  
Aided Design

Work on subsonic compressors is reviewed and traditional British and American methods of design are compared. Transonic compressors are now well established and recent progress, demonstrating the necessity for properly shaped blades in machines having high tip speeds, is examined. Advances in the computer-aided design of turbomachinery are described: these include the ‘Matrix through-flow’ and ‘Streamline curvature’ methods of calculating the meridional flow. Experimental results give preliminary confirmation of a method of annulus wall boundary layer prediction. Finally, current and future developments are discussed and an attempt is made to describe how an axial flow compressor may be designed a decade hence.

Calculation of Fluid Motion in Axial Flow Turbomachines

1968 ◽  
Author(s):  
D. J. L. Smith ◽  
J. F. Barnes
Keyword(s):  
Experimental Work ◽  
Fluid Motion ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Axial Flow ◽  
Streamline Curvature ◽  
Through Flow ◽  
Loss Distributions ◽  
The Matrix ◽  
Made In

In the last few years considerable progress has been made in calculating the three-dimensional flows through turbomachines. The two methods which appear to be widely used are what have come to be known as the “Streamline Curvature” and the “Matrix Through Flow” methods. At the National Gas Turbine Establishment, these advanced methods have been applied to existing turbomachines and this paper presents some of the calculated and experimental results for four axial flow machines. By making use of fairly simple loss distributions it has been found that these methods can assist towards the understanding of observed phenomena and, in the case of the axial compressor, they offer some prospect of being able to calculate the onset of surge. Also included is a brief report of work in progress to generate a computer program for the solution of the compressible velocity distribution around the surfaces of turbomachine blades, together with an indication of possible future experimental work.

Paper 16: Some Problems in the Application of Meridional Flow Programmes to the Design of Large Steam Turbines

1969 ◽  
Vol 184 (7) ◽  
pp. 38-48
Author(s):  
D. Lindley ◽  
J. Westmoreland ◽  
J. F. T. Whybrow
Keyword(s):  
Analytical Methods ◽  
Meridional Flow ◽  
Single Stage ◽  
Damping Factor ◽  
Steam Turbines ◽  
Streamline Curvature ◽  
Blade Thickness ◽  
Through Flow ◽  
Pressure Steam ◽  
The Matrix

After an introduction to the aerodynamic problems facing the designer of large steam turbines, two analytical methods that have been used to analyse the flow in such turbines are reviewed, and their limitations discussed. Results are given for an analysis of a single-stage machine similar to that found in an intermediate pressure steam turbine using the matrix through-flow programme to investigate the effects of varying blade twist, tilt, blade thickness, and camberline shape. In addition, details are given of a comparison made between results obtained from a streamline curvature and a matrix through-flow programme used to analyse a single-stage turbine. Finally, the problems of using these programmes are discussed, and details of the effect of grid shape and damping factor are given.

WirePATH Rapid Tooling Process and Supporting Software Development

2003 ◽  
Author(s):  
Alexander Lee ◽  
James Brink ◽  
David Anderson ◽  
Karthik Ramani
Keyword(s):  
Computer Aided Design ◽  
Electrical Discharge Machining ◽  
Computer Software ◽  
Wire Edm ◽  
Overall Design ◽  
Design Changes ◽  
Mold Making ◽  
Recent Developments ◽  
New Applications ◽  
Aided Design

Recent developments in Computer Aided Design (CAD) have drastically reduced overall design cycle time and cost. In this paper, wirePATH, a new method for rapid direct tooling, is presented. By using specialized interactive segmentation computer software and wire electrical discharge machining (wire EDM), wirePATH can reduce manufacturing time and cost for injection molds, casting patterns, and dies. Compared to other conventional-mold making methods, wirePATH can reduce fabrication time by as much as 40 to 70%. Wirepath can use a combination of wire EDM and other processes. Our method provides a new means to produce a greater variety in products by changing only portions of the tooling. Segments allow a part of a mold to be replaced to accommodate design changes and repair. WirePATH enables new applications of wire EDM to more complex shapes by bridging the gaps between CAD, our method, wire EDM and conventional manufacturing processes.

Wall Boundary Layer Development Near the Tip Region of an IGV of an Axial Flow Compressor

1984 ◽  
Vol 106 (2) ◽  
pp. 337-345
Author(s):  
B. Lakshminarayana ◽  
N. Sitaram
Keyword(s):  
Boundary Layer ◽  
Guide Vane ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Axial Flow ◽  
Inlet Guide Vane ◽  
Wall Boundary Layer ◽  
Wall Boundary ◽  
Boundary Layer Development ◽  
Flow Compressor

The annulus wall boundary layer inside the blade passage of the inlet guide vane (IGV) passage of a low-speed axial compressor stage was measured with a miniature five-hole probe. The three-dimensional velocity and pressure fields were measured at various axial and tangential locations. Limiting streamline angles and static pressures were also measured on the casing of the IGV passage. Strong secondary vorticity was developed. The data were analyzed and correlated with the existing velocity profile correlations. The end wall losses were also derived from these data.

Assessment of HTGR Helium Compressor Analysis Tool Based on Newton-Raphson Numerical Application to Throughflow Analysis

2006 ◽  
Author(s):  
Ji Hwan Kim ◽  
Hyeun Min Kim ◽  
Hee Cheon No
Keyword(s):  
Axial Flow ◽  
Meridional Flow ◽  
Analysis Tool ◽  
Numerical Application ◽  
Good Convergence ◽  
Streamline Curvature ◽  
Performance Map ◽  
Compressor Performance ◽  
Newton Raphson ◽  
Good Agreement

This study describes the development of a computer program for analyzing the off-design performance of axial flow helium compressors, which is one of the major concerns for the power conversion system of a high temperature gas-cooled reactor (HTGR). The compressor performance has been predicted by the aerodynamic analysis of meridional flow with allowances for losses. The governing equations have been derived from Euler turbomachine equation and the streamline curvature method, and then they have been merged into linearized equations based on the Newton-Raphson numerical method. The effect of viscosity is considered by empirical correlations to introduce entropy rises caused by primary loss sources. Use of the method has been illustrated by applying it to a 20-stage helium compressor of the GTHTR300 plant. As a result, the flow throughout the stages of the compressor has been predicted and the compressor characteristics have been also investigated according to the design specification. The program results show much better stability and good convergence with respect to other throughflow methods, and good agreement with the compressor performance map provided by JAEA.

Effect of Axially Non-Uniform Rotor Tip Clearance on the Performance of a High Speed Axial Flow Compressor Stage

1994 ◽  
Author(s):  
K. Mohan ◽  
S. A. Guruprasad
Keyword(s):  
High Speed ◽  
Axial Flow ◽  
Separated Flow ◽  
Tip Clearance ◽  
Compressor Stage ◽  
Tip Leakage Flow ◽  
Suction Surface ◽  
Wall Boundary Layer ◽  
Improved Performance ◽  
Flow Compressor

An axially non-uniform type of rotor tip clearance was conceived and tried on a single stage compressor. This concept is based on the advantages of a smaller tip clearance in the front portion of the blade and a larger clearance in the rear portion which allows a higher tip leakage flow to interact with the passage secondary flow, casing wall boundary layer, separated flow on the blade suction surface and the scraping vortex, which are more prominent at the rear portion of the blade. Experimental results indicated that an axially non-uniform clearance can provide improved performance of a compressor stage. Providing the tip clearance in the compressor casing instead of at the blade tip indicated certain advantages. An ‘optimum’ value of rotor tip clearance was noticed for this compressor stage, both for axially uniform and axially non-uniform clearance.

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