A Comparison of the Matrix and Streamline Curvature Methods of Axial Flow Turbomachinery Analysis, From a User’s Point of View

1975 ◽  
Vol 97 (4) ◽  
pp. 549-558 ◽  
Author(s):  
W. R. Davis ◽  
D. A. J. Millar
Keyword(s):  
Flow Analysis ◽  
Axial Compressor ◽  
Axial Flow ◽  
Computer Time ◽  
Cascade Model ◽  
Point Of View ◽  
Ease Of Use ◽  
Flow Equations ◽  
Streamline Curvature ◽  
The Matrix

In recent years two general methods for flow analysis in turbomachinery have been developed, one generally called the Streamline Curvature Method, the other the Matrix Through-Flow Method. Both methods solve the same flow equations but the differences in technique introduce different operational constraints and difficulties. A comparative assessment of the relative merits of the two methods has been difficult because the various authors did not use similar cascade models to represent cascade loss and deviation, a necessary adjunct to each technique. This paper outlines the two methods, and a common cascade model for both, and compares two programs written to implement the two techniques for ease of use, computer time and storage requirements, flexibility and inherent limitations. The programs are used to compute the flow field in three axial flow compressor applications: an interconnecting duct, a transonic fan, and three stage axial compressor. The predicted performance for the above machines was fairly good, although no attempt was made to “tune” the cascade model for the specific type of machine, as the relative merits of each method were of interest. It is concluded that there is a small operational advantage to the matrix method.

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.

Effect of Stator Variability on Axial Compressor Performance

2019 ◽  
Author(s):  
Kirubakaran Purushothaman ◽  
N. R. Naveen Kumar ◽  
Vidyadheesh Pandurangi ◽  
Ajay Pratap
Keyword(s):  
Guide Vane ◽  
Flow Analysis ◽  
Axial Compressor ◽  
Axial Flow ◽  
Low Pressure ◽  
Inlet Guide Vane ◽  
Jet Engines ◽  
Stator Blade ◽  
And Performance ◽  
Flow Compressor

Abstract Variability in stator vanes is a widely used technique to improve the stability and efficiency of axial flow compressor in gas turbine engines. Most of the modern aircraft jet engines use variable stator vanes in both low pressure and high pressure compressors primarily for off-design performance. This study discusses in detail about the effect of stator variability in a three stage low pressure axial compressor at design and off-design conditions. Computational flow analysis were carried out for the three stage low pressure compressor with variability in inlet guide vane and first stage stator blade. Detailed investigation on flow physics was carried out in rotor blade passages with stator variability. At off-design speeds, the reduction in flow velocity is lower than the reduction in blade tip speed. This leads to mismatch in flow angles and inlet blade angles causing high incidence and large flow separation in blade passage. This results in poor aerodynamic stability of the axial compressor at off-design speeds. In this study, aerodynamic performance of compressor is evaluated from 70% to 100% design speeds with different stagger angle setting of inlet guide vane at each speed. Further, to improve 2nd stage rotor performance, variability was introduced in 1st stage stator blade and performance was evaluated. Compressor test results are compared with CFD data for design and off-design speeds.

A Comparison of the Streamline Throughflow and Streamline Curvature Methods for Axial Turbomachinery

1998 ◽  
Author(s):  
Anthony J. Gannon ◽  
Theodor W. von Backström
Keyword(s):  
Stream Function ◽  
Compressible Flows ◽  
Swirling Flow ◽  
Axial Flow ◽  
Computer Time ◽  
Computational Grids ◽  
Test Cases ◽  
Streamline Curvature ◽  
Order Of Magnitude ◽  
Flow Through

The axial flow turbo machinery throughflow equation states that radial gradients of rothalpy, entropy and moment of momentum affect the conservation of tangential vorticity. The streamline throughflow method (STFM) transforms this equation, expressed in terms of stream function in a radial-axial co-ordinate system, to an equation for streamline radial position in a stream function-axial co-ordinate system. The paper assesses the accuracy and efficiency of the STFM relative to the streamline curvature method (SCM) by comparing streamline positions and velocity profiles to analytical results. Test cases include flow through a single actuator disc, flow through twin actuator discs using a coarse computational grid, compressible flows through an almost choked nozzle, through single and twin actuator discs, and swirling flow using sloped stations. Results from the STFM and SCM agreed about equally well with analytical solutions for the same number of streamlines. The STFM, however, was much more tolerant of distorted computational grids and used an order of magnitude less computer time to converge. The test cases show that the STFM is suitable for annuli with large variations in hub and tip radius, for highly swirling and compressible flow, and is more robust and converges faster than the SCM. To demonstrate the practical applicability of the STFM a multistage compressor was simulated and STFM results compared with experiment.

Flow Analysis of Axial Compressor AV63-15 Variable Stator Simulation

2012 ◽  
Vol 532-533 ◽  
pp. 474-478
Author(s):  
Wei Hua Cheng ◽  
Mian Chang Li ◽  
Chuan Peng Li
Keyword(s):  
Flow Analysis ◽  
Three Dimensional ◽  
Axial Compressor ◽  
Axial Flow ◽  
Operating Conditions ◽  
Axial Flow Compressor ◽  
Air Supply ◽  
The Difference ◽  
And Performance ◽  
Flow Compressor

This paper conducts numerical simulation to a 15-stage civil axial flow compressor and obtains its main parameters distribution and performance curve by a full three-dimensional viscid flow computation software. The computation result indicates that, the developed axial flow compressor meets the anticipated design requirements, and satisfies the customers’ indicators. Under the designed compression ratio, the difference between the maximum air supply quantity in summer and the minimum air supply quantity in winter is 22%. By comparing the operating conditions and data analysis, obtained the change trend of axial velocity, static pressure and temperature, and Ma, and discovered that, under opening of 48° and outlet back pressure of 550KPa, flow separation occurred on the section of machine set close to hud, which indicated that operating condition was close to surging condition.

The Preliminary Analysis of Axial Turbines by a Simplified Throughflow Procedure

1982 ◽  
Vol 24 (1) ◽  
pp. 5-10
Author(s):  
N. A. Mitchell
Keyword(s):  
Axisymmetric Flow ◽  
Design Procedure ◽  
Computer Time ◽  
One Dimensional ◽  
Flow Equations ◽  
Streamline Curvature ◽  
Flow Through ◽  
Axial Turbines ◽  
Turbine Design ◽  
Performance Calculation

A new iterative scheme for calculating the axisymmetric flow through a turbine, which converges to a given value of turbine exit pressure, is described. It is intended to be used at a preliminary stage in a turbine design procedure instead of a one-dimensional calculation, since it enables spanwise variations of turbine performance to be calculated with reasonable accuracy and with minimum data preparation in approximately 1/30 of the computer time of a conventional axisymmetric calculation. The method solves the full axisymmetric flow equations on three streamlines through the machine at hub, midspan, and tip, although an approximation is introduced regarding the curvature of the centre streamline. Agreement with a full streamline curvature analysis is shown to be good, and comparisons with a one-dimensional Ainley-Mathieson based performance calculation show how the method is sensitive to root and tip behaviour.

Performance of Two Transonic Axial Compressor Rotors Incorporating Inlet Counterswirl

1987 ◽  
Vol 109 (1) ◽  
pp. 142-148 ◽  
Author(s):  
C. H. Law ◽  
A. J. Wennerstrom
Keyword(s):  
Static Pressure ◽  
Axial Compressor ◽  
Axial Flow ◽  
Leading Edge ◽  
Axial Compressors ◽  
Streamline Curvature ◽  
Static Pressure Distribution ◽  
Pressure Distributions ◽  
Blade Section ◽  
Flow Compressor

A single-stage axial-flow compressor which incorporates rotor inlet counterswirl to improve stage performance is discussed. Results for two rotor configurations are presented, including design and experimental test data. In this compressor design, inlet guide vanes were used to add counterswirl to the inlet of the rotor. The magnitude of the counterswirl was radially distributed to maximize the overall stage efficiency by minimizing the rotor combined losses (diffusion losses and shock losses). The shock losses were minimized by simultaneously optimizing the rotor blade section geometry, through-blade static pressure distribution, and leading edge aerodynamic/geometric shock sweep angles. Results from both the design and experimental performance analyses are presented and comparisons are made between the experimental data and the analyses and between the performance of both rotor designs. The computation of the flow field for both rotor designs and for the analysis of both tests was performed in an identical fashion using an axisymmetric, streamline-curvature-type code. Results presented include tip section blade-to-blade static pressure distributions and rotor through-blade and exit distributions of various aerodynamic parameters. The performance of this compressor stage represents a significant improvement in axial compressor performance compared to previous attempts to use rotor inlet counterswirl and to current, more conventional, state-of-the-art axial compressors operating under similar conditions.

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.

The Uniqueness of Turbomachinery Flow Calculations Using the Streamline Curvature and Matrix Through-Flow Methods

1971 ◽  
Vol 13 (6) ◽  
pp. 376-379 ◽  
Author(s):  
H. Marsh
Keyword(s):  
Mach Number ◽  
Flow Pattern ◽  
Iterative Procedure ◽  
Flow Analysis ◽  
Alternative Procedure ◽  
Streamline Curvature ◽  
Through Flow ◽  
The Matrix ◽  
Uniqueness Of The Solution ◽  
Flow Through

When calculating the flow through turbomachines by an iterative procedure, it is assumed that on each cycle of iteration there is only one solution for the flow pattern. The uniqueness of the solution obtained by the method of streamline curvature is examined and a set of Mach number conditions are derived which are sufficient to ensure that the flow pattern is unique. The Mach number limitations are the same as those which are necessary to avoid ambiguity in the matrix through-flow analysis. An alternative procedure is then described in which the solution for the flow pattern is always unique.

Sign in / Sign up

Export Citation Format

Share Document