A Secondary Flow Calculation Method for Single-Stage Axial Transonic Flow Compressors, Including Shock-Secondary Flow Interaction

1990 ◽  
Vol 112 (4) ◽  
pp. 652-668 ◽  
Author(s):  
J. Kaldellis ◽  
D. Douvikas ◽  
F. Falchetti ◽  
K. D. Papailiou
Keyword(s):  
Shear Layer ◽  
Secondary Flow ◽  
Calculation Method ◽  
Transonic Flow ◽  
External Flow ◽  
Single Stage ◽  
Zone Model ◽  
Flow Calculation ◽  
Viscous Shear ◽  
Wall Shear

A secondary flow calculation method is presented, which makes use of the meridional vorticity transport equation. Circumferential mean flow quantities are calculated using an inverse procedure. The method makes use of the mean kinetic energy integral equation and calculates simultaneously hub and tip secondary flow development. Emphasis is placed upon the use of a coherent two-zone model and particular care is taken to describe adequately the flow inside an unbounded (external), semi-bounded (annulus), and fully bounded (bladed) space. Along with the velocity field, the losses, the defect forces, and the corresponding additional work realized inside the viscous wall shear layer are calculated for stationary and rotating flow. An approximate model for the interaction of the viscous shear layers and the external flow is used, which takes into account the meridional and peripheral blockage. When shock waves are present in the external flow, an approximate interaction model is used, additionally, which calculates the static pressure field resulting from the interaction of the shock wave and the corresponding wall shear layer. The method has been applied to two single-stage transonic flow compressors and the results of the comparison between theory and experiment are presented and discussed.

A Secondary Flow Calculation Method for One Stage Axial Transonic Flow Compressors, Including Shock-Secondary Flow Interaction

1989 ◽  
Author(s):  
J. Kaldellis ◽  
D. Douvikas ◽  
F. Falchetti ◽  
K. D. Papailiou
Keyword(s):  
Shear Layer ◽  
Secondary Flow ◽  
Calculation Method ◽  
Transonic Flow ◽  
External Flow ◽  
Zone Model ◽  
Flow Calculation ◽  
One Stage ◽  
Viscous Shear ◽  
Wall Shear

A secondary flow calculation method is presented, which makes use of the meridional vorticity transport equation. Circumferentially mean flow quantities are calculated using an inverse procedure. The method makes use of the mean kinetic energy integral equation and calculates simultaneously hub and tip secondary flow development. Emphasis is placed upon the use of a coherent two-zone model and particular care is taken in order to describe adequately the flow inside an unbounded (external), semi-bounded (annulus) and fully-bounded (bladed) space. Along with the velocity field, the losses, the defect forces and the corresponding additional work realized inside the viscous wall shear layer are calculated for stationary and rotating flow. An approximate model for the interaction of the viscous shear layers and the external flow is used, which takes into account the meridional and the peripheral blockage. When shock waves are present in the external flow, an approximate interaction model is used, additionally, which calculates the static pressure field resulting from the interaction of the shock wave and the corresponding wall shear layer. The method has been applied to two one stage transonic flow compressors and the results of the comparison between theory and experiment are presented and discussed.

scholarly journals A Secondary Flow Calculation Method Based on the Meridional Vorticity Transport Equation

1988 ◽  
Author(s):  
J. Kaldellis ◽  
D. Douvikas ◽  
K. D. Papailiou
Keyword(s):  
Transport Equation ◽  
Secondary Flow ◽  
Calculation Method ◽  
Zone Model ◽  
Mean Flow ◽  
Flow Calculation ◽  
Flow Development ◽  
The Mean ◽  
Vorticity Transport ◽  
Inverse Procedure

A secondary flow calculation method is presented in this work, which makes use of the meridional vorticity transport equation. Circumferentially mean flow quantities are calculated using an inverse procedure. The method makes use of the mean kinetic energy integral equation and calculates simultaneously hub and tip secondary flow development. Emphasis is placed upon the use of a coherent two-zone model and particular care is taken in order to describe adequately the flow inside an unbounded (external), semi-bounded (annulus) and fully-bounded (bladed) space. The velocity field, the losses and the defect forces receive particular attention. Comparison between theoretical and experimental results is presented.

An Investigation of the Transverse Velocity Profile in the Case of Internal Viscous Aerodynamic Problems

1984 ◽  
Author(s):  
P. Kotidis ◽  
P. Chaviaropoulos ◽  
K. D. Papailiou
Keyword(s):  
Velocity Field ◽  
Flow Field ◽  
Velocity Profile ◽  
Shear Layer ◽  
Transverse Velocity ◽  
Transverse Plane ◽  
Zone Model ◽  
Viscous Shear ◽  
Rotational Part ◽  
Confined Flows

The development of transverse velocity profile is directly related to the development of secondary vorticity. In the internal aerodynamics case with potential external flow, although vorticity remains confined inside the viscous shear layer, secondary vorticity induced velocities exist outside of it. If the secondary vorticity field is known, the induced secondary velocity field is well approximated following Hawthorne’s classical analysis. In the present work, the above analysis is used to separate the velocity field in the transverse plane into a potential and a rotational part. In the case of confined flows, the rotational part is confined inside the viscous shear layer, while the potential part occupies the whole flow field. This last part is the consequence of the “displacement” effects of the shear layer in the transverse plane. Therefore, the present work allows a re-examination of the flow two-zone model (separation of the flow field in a viscous and an inviscid part) in confined flows. On the other hand, the limitations of Hawthorne’s theory are examined, while a parallel analysis is presented for the case where the secondary vorticity distribution varies not only along the blade height, but also circumferentially.

scholarly journals 3-D Loss Prediction Based on Secondary Flow and Blade Shear Layer Interaction

1991 ◽  
Author(s):  
D. T. Katramatos ◽  
J. K. Kaldellis
Keyword(s):  
Shear Layer ◽  
Secondary Flow ◽  
Axial Compressor ◽  
Prediction Method ◽  
Test Cases ◽  
Loss Distribution ◽  
Flow Angle ◽  
Flow Calculation ◽  
Loss Prediction ◽  
Profile Loss

The 3-D loss distribution along axial turbomachines has been investigated in the present work. For this purpose, our well documented secondary flow calculation method has been interactively coupled with our fast blade-to-blade shear layer calculation code, in order to predict the complete secondary flow and profile loss distribution. The presence of an even moderate secondary flow field modifies the flow angle distributions, thus making clear the need of a reliable profile loss prediction method for off-design cases, especially in the presence of separation. Accordingly, the blade-to-blade code predicts the profile loss distribution and subsequently provides the correct total pressure field for the secondary flow calculation. The combination of the above mentioned codes finally gives a realistic picture of the flow quantities at any S3 surface along a machine at a minimal computer cost. Several test cases, including axial compressor and turbine cascades as well as transonic axial compressor blade rows have been investigated. The results are in good agreement with the experimental data and are favourably compared with various recent correlations.

An Improved Streamline Curvature Method for Centrifugal Compressor Performance

2017 ◽  
Author(s):  
Zhang Chao-wei ◽  
Dong Xue-zhi ◽  
Liu Xi-yang ◽  
Gao Qing ◽  
Tan Chun-qing
Keyword(s):  
Secondary Flow ◽  
Centrifugal Compressor ◽  
Calculation Method ◽  
Pressure Ratio ◽  
Prediction Method ◽  
Zone Model ◽  
Streamline Curvature ◽  
Distribution Laws ◽  
Compressor Performance ◽  
Streamline Curvature Method

This paper describes an improved throughflow calculation method on S2m based on streamline curvature method for predicting the performance of centrifugal compressor. A general method of specifying the empirical data provides separate treatment of blockage, deviation and losses. The spanwise and streamwise distribution laws of losses are described. The paper describes a new aspect of method about the mixing loss. Two-zone model considering the “jet and wake” can obtain the secondary flow width. For this reason, the improved prediction method combined with two-zone model is proposed to correct the mixing loss. Due to the average static pressure at outlet unknown, the secondary flow width is obtained by iterations. This performance prediction method is validated with experimental and CFD data of three cases, including impeller(A), impeller(B) and impeller(C). The results show that the improved throughflow calculation method predicts the performance of centrifugal compressor more accurately than conventional throughflow calculation, with increased the accuracy of total pressure ratio and isentropic efficiency by about 3.18% and 1.30%.

Rapid energy flow calculation method for integrated electrical and thermal systems

2020 ◽  
Vol 123 ◽  
pp. 106317 ◽  
Author(s):  
Guoqiang Sun ◽  
Wenxue Wang ◽  
Xiao Lu ◽  
Yi Wu ◽  
Wei Hu ◽  
...  
Keyword(s):  
Calculation Method ◽  
Energy Flow ◽  
Thermal Systems ◽  
Flow Calculation

The Research on Flow Calculation Method of the Ball Solenoid Valve

2014 ◽  
Vol 721 ◽  
pp. 370-373
Author(s):  
Yi Yang ◽  
Liang Chu ◽  
Di Fan ◽  
Yu Ting Huang
Keyword(s):  
Calculation Method ◽  
Solenoid Valve ◽  
Matlab Simulink ◽  
Flow Calculation ◽  
Simulink Model ◽  
Flow Demand

This paper proposes a flow calculation method of the ball solenoid valve, by measuring diameter of the input valve spool, we can estimate the rated flow of the solenoid valve. Aiming at the calculation method, we have built a MATLAB/Simulink model to calculate the valve flow, and we also validated the model by the flow demand of one type of RBS system.

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