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.

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.

Off-Design Analysis of Transonic Bypass Fan Systems Using Streamline Curvature Through-Flow Method

2019 ◽  
Vol 36 (2) ◽  
pp. 137-146 ◽  
Author(s):  
Sercan Acarer ◽  
Ünver Özkol
Keyword(s):  
Swirling Flow ◽  
Design Analysis ◽  
Simple Extension ◽  
Test Cases ◽  
Streamline Curvature ◽  
Through Flow ◽  
Numerical Effort ◽  
Work Input ◽  
Design Calculations ◽  
Transonic Fan

Abstract The two-dimensional streamline curvature through-flow modeling of turbomachinery is still a key element for turbomachinery preliminary analysis. Basically, axisymmetric swirling flow field is solved numerically. The effects of blades are imposed as sources of swirl, work input/output and entropy generation. Although the topic is studied vastly in the literature for compressors and turbines, combined modeling of the transonic fan and the downstream splitter of turbofan engine configuration, to the authors’ best knowledge, is limited. In a prior study, the authors presented a new method for bypass fan modeling for inverse design calculations. Moreover, new set of practical empirical correlations are calibrated and validated. This paper is an extension of this study to rapid off-design analysis of transonic by-pass fan systems. The methodology is validated by two test cases: NASA 2-stage fan and GE-NASA bypass fan case. The proposed methodology is a simple extension for streamline curvature method and can be applied to existing compressor methodologies with minimum numerical effort.

Spanwise Mixing in Multistage Axial Flow Compressors: Part II—Throughflow Calculations Including Mixing

1986 ◽  
Vol 108 (1) ◽  
pp. 10-16 ◽  
Author(s):  
S. J. Gallimore
Keyword(s):  
Diffusion Process ◽  
Turbulent Diffusion ◽  
Physical Mechanism ◽  
Axial Flow ◽  
Important Influence ◽  
Axial Compressors ◽  
Streamline Curvature ◽  
Loss Distributions ◽  
Total Temperature ◽  
Flow Through

The important influence of spanwise mixing on the flow through multistage axial compressors has been investigated by incorporating the effect into an axisymmetric streamline curvature throughflow program. The mixing was modeled as a turbulent diffusion process based on the experimental observations reported in Part I of this paper, which showed that this was the dominant physical mechanism. The inclusion of the mixing was found to be crucial in accurately predicting spanwise variations of exit total temperature in multistage machines. The effect of mixing on loss distributions inferred from measurements was found to be significant so that upstream loss sources could only be determined from downstream distributions when the effect of mixing was included.

Throughflow Calculations for Transonic Axial Flow Turbines

1978 ◽  
Vol 100 (2) ◽  
pp. 212-218 ◽  
Author(s):  
J. D. Denton
Keyword(s):  
Transonic Flow ◽  
Gas Turbines ◽  
Pressure Ratio ◽  
Axial Flow ◽  
Steam Turbines ◽  
Flow Measurements ◽  
High Pressure Ratio ◽  
Streamline Curvature ◽  
Flow Through ◽  
Good Agreement

The development of a streamline curvature throughflow program to predict the flow through the low pressure stages of large steam turbines is described. The program can also be used for gas turbines. Difficulties encountered in dealing with transonic flow and multiple high pressure ratio stages are discussed. Comparisons of the predictions of the program with flow measurements in steam and gas turbines show reasonably good agreement with most of the discrepancies being attributable to errors in the empirical data input to the program.

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.

Flow through axial-flow-turbomachinery blading

2018 ◽  
Author(s):  
Marcel Escudier
Keyword(s):  
Flow Velocity ◽  
Compressible Flow ◽  
Dimensional Analysis ◽  
Incompressible Flow ◽  
Compressible Fluid ◽  
Axial Flow ◽  
Linear Cascade ◽  
Dimensional Parameters ◽  
Flow Through

This chapter is concerned primarily with the flow of a compressible fluid through stationary and moving blading, for the most part using the analysis introduced in Chapter 11. The principles of dimensional analysis are applied to determine the appropriate non-dimensional parameters to characterise the performance of a turbomachine. The analysis of incompressible flow through a linear cascade of aerofoil-like blades is followed by the analysis of compressible flow. Velocity triangles for flow relative to blades, and Euler’s turbomachinery equation, are introduced to analyse flow through a rotor. The concepts introduced are applied to the analysis of an axial-turbomachine stage comprising a stator and a rotor, which applies to either a compressor or a turbine.

Studies of calcium-45 desaturation from kidney slices in flow-through chambers

1978 ◽  
Vol 234 (1) ◽  
pp. R34-R38
Author(s):  
T. Uchikawa ◽  
A. B. Borle
Keyword(s):  
Kinetic Parameters ◽  
Rat Kidney ◽  
Kidney Cells ◽  
Tissue Slices ◽  
Kidney Slices ◽  
System A ◽  
Order Of Magnitude ◽  
Exponential Equations ◽  
Flow Through ◽  
Best Fit

This paper describes a method to measure calcium fluxes and calcium exchangeable pools in tissue slices by continuous perifusion in flow-through chambers. 45Ca desaturation from rat kidney slices can be analyzed as in an open three-compartment catenary system. A set of equations is given to calculate all the relevant kinetic parameters from the triple exponential equations which best fit the desaturation curves. The results show that the kinetic parameters obtained in kidney slices by this new method are in the same order of magnitude as those previously observed in cultured monkey kidney cells.

An Improved Hybrid Alternative WENO Scheme for High Mach Number Flows

2021 ◽  
Author(s):  
Uttam Singh Rajput ◽  
Krishna Mohan Singh
Keyword(s):  
High Speed ◽  
Compressible Flows ◽  
Weno Scheme ◽  
Test Cases ◽  
Present Scheme ◽  
Low Dissipation ◽  
Scale Structures ◽  
High Mach ◽  
Fifth Order ◽  
High Resolution Method

Abstract This study presents the development of a fifth-order hybrid alternative mapped weighted essentially non-oscillatory scheme (HAW-M) for high-speed compressible flows. A new, improved smoothness indicator has been developed to design the HAW-M scheme. The performance of the present scheme has been evaluated through different one and two-dimensional test cases. The developed scheme shows higher accuracy and low dissipation. Further, it captures the fine-scale structures smoothly than the existing high-resolution method.

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