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The flow in multistage axial flow compressors is particularly complex in nature because of the proximity of moving bladerows, the growth of end-wall boundary layers and the presence of tip and seal leakages and secondary flow. The problems associated with these phenomena are at their most acute in the latter, subsonic stages of the core compressor, where Reynolds numbers are modest and the blading has low aspect ratio. Indeed, much of the inefficiency of axial stages is believed to be associated with the interaction between blading and end-wall flows. The fact that the end-wall flow phenomena result in conditions local to the blade which are quite different from those over the major part of the annulus was appreciated by many of the earliest workers in the axial turbomachinery field. However, experiments on blading designs aimed specifically at attacking the end-loss have been sparse. This thesis includes results from tests of conventional and end-bent blading in a four-stage, low-speed, axial compressor, built specifically for the task, at a scale where high spatial measurement resolution could be readily achieved within the flowpath. Two basic design styles are considered: a zero a0 stage with DCA aerofoils and a low-reaction controlled-diffusion design with cantilevered stators. The data gives insight into the flow phenomena present in 'buried' stages and has resulted in a much clearer understanding of the behaviour of end-bent blading. A 3D Navier-Stokes solver was calibrated on the two low-reaction stators and was found to give good agreement with most aspects of the experimental results. An improved design procedure is suggested based on the incorporation of end-bends into the throughflow and iterative use of the 3D Navier-Stokes solver.

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This thesis is concerned with the development of a theoretical method for predicting the turbulent flow and heat transfer in the cavity between a rotating and a stationary cone. The motivation for the work stems from the need, in the design process for the gas turbine aero-engine, for a fast and reliable predictive method for such flows. The method developed here is the integral method, which reduces the governing partial differential equations to ordinary differential equations. A number of solution methods for these equations are described, and the optimum in terms of speed and accuracy is indicated. Predicted moment coefficients compare well with experimental data. For half-cone angles greater than approximately 60° but poorly for half cone angle less than approximately 45°. The poor agreement for small cone angles is thought to be due to the presence of Taylor-type vortices, which cannot be incorporated into the integral method. Heat transfer is incorporated into the method using the Reynolds analogy. Due to the lack of experimental data, heat transfer predictions are compared with those from a finite difference program and show encouraging agreement. A computer program which solves the full Reynolds-averaged Navier-Stokes and energy equations in steady and axisymmetric form, using a finite-difference method is modified for use in the conical geometry. Comparison of the predicted moment coefficients with experimental data shows no marked improvement over the integral method. Examination of the secondary flow predicted by the program shows it to be similar to that of the integral method. The failure of the program to predict Taylor-type vortices may be attributed to the fact that they are non-axisymmetric and/or unsteady. The assumptions underlying the Integral method are investigated via the finite difference program and it is concluded that they are valid for half cone angles as small as 15°. Based on the results of the finite difference program, the Integral method is modified to allow for a rectangular outer shroud, and a new model for the stator is described. It is concluded that both the integral method and the finite difference program can be used safely in rotor-stator systems where the half cone angle is greater than about 60°.

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