This review indicates the possible future directions for research on endwall flows in axial flow compressors. Theoretical investigations on the rotor blade endwall flows in axial flow compressors reported here include the secondary flow calculation and the development of the momentum integral equations for the prediction of the annulus wall boundary layer. The equations for secondary vorticity at the rotor exit are solved analytically. The solution includes the effects of rotation and the viscosity. The momentum integral equations derived include the effect of the blade boundary layers. The axial flow compressor facility of the Department of Aerospace Engineering at The Pennsylvania State University, which is used for the experimental investigations of the endwall flows, is described in some detail. The overall performance and other preliminary experimental results are presented. Extensive radial flow surveys are carried out at the design and various off design conditions. These are presented and interpreted in this report. The following experimental investigations of the blade endwall flows are carried out. (1) Rotor blade endwall flows: The following measurements are carried out at four flow coefficients. (a) The rotor blade static pressures at various axial and radial stations (with special emphasis near the blade tips). (b) The hub wall static pressures inside the rotor blade passage at various axial and tangential stations. (2) IGV endwall flows: The following measurements are carried out at the design flow coefficient. (a) The boundary layer profiles at various axial and tangential stations inside the blade passage and at the blade exit. (b) Casing static pressures and limiting streamline angles inside the blade passage.

/pdf/end-wall-flow-characteristics-and-overall-performance-of-an-1pyhw1fgt2.pdf

End wall flow characteristics and overall performance of an axial flow compressor stage

In this paper an extension of our secondary flow calculation method is presented in order to estimate the energy exchange and the secondary losses in axial and radial compressors.Although it is well known today that end-wall shear layers play a major role in the performance of the compressors, there are only few secondary flow methods able to predict realistically the behaviour of real machines. For this purpose a new theory was developed which extends Mellor’s basic principles and uses our previous work, including the complete form of meridional vorticity transport equation.A coherent model for the real work exchange between the fluid and the machine has been developed, as well as for the distribution of secondary losses, not only at the compressor’s exit but also at every station through the machine. An expression for the added work due to the secondary field is also given. Finally the influence of secondary losses in the overall efficiency is well estimated.This work has been successfully applied to a highly loaded compressor cascade, as well as to a transonic axial compressor and to a radial one-stage one. Comparison between theoretical and experimental results is also presented.Copyright © 1990 by ASME

/pdf/energy-exchange-and-secondary-losses-prediction-in-high-1zw8e9xzkt.pdf

Energy Exchange and Secondary Losses Prediction in High Speed Axial and Radial Compressors

The Use of Radial Equilibrium and Streamline Curvature Methods for Turbomachinery Design and Prediction

Secondary Flows in Axial-Flow Compressors

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.Copyright © 1991 by ASME

/pdf/3-d-loss-prediction-based-on-secondary-flow-and-blade-shear-399k52du81.pdf

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

The Simulation of Axial Compressor Performance Using an Annulus Wall Boundary Layer Theory

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The Simulation of Axial Compressor Performance Using an Annulus Wall Boundary Layer Theory