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The thrust is primarily on the aerodynamic design but this cannot be divorced from the mechanical aspects and so some of these are touched upon but are not gone into so deeply.

The paper has been written from the point of view of the designer and tries to cover most of the points that need to be considered in order to produce a successful compressor.

The emphasis has been on the theory behind the design process and on minimizing the reliance on empirical rules.

However, because of the complexity of the flow, some empiricism still remains.

Experiments were subsequently performed on this rig to obtain both the overall pressure rise characteristics of the compressor and the stagnation.

Longman, 1989. - Volume 226 - H.

Apr 16, 2016. Abstract: This paper describes the introduction of three-dimension (3-D) blade designs into a 5-stage axial compressor with multi-stage computational fluid dynamic (CFD) methods.

Prior to a redesign, a validation study is conducted for the overall performance and flow details based on full-scale test.

The thrust is primarily on the aerodynamic design but this cannot be divorced from the mechanical aspects and so some of these are touched upon but are not gone into so.

Compressor Aerodynamics, 1989 ( Longman).

E., Wisler, D. C., Okiishi, T.

H., Walker, G. J., Hodson, H.

P., Shin, H.-W. Boundary layer development in axial compressors and turbines: Parts 1 to 4.

Shabbir, A., Celestina, M.

L., Adamczyk, J. J., Strazisar, A.

The effect of hub leakage flow on two high speed axial flow compressor rotors.

C., Barton, J. P., Young, K.

Endwall effects at two tip clearances in a multi-stage axial flow compressor with controlled diffusion blading.

Turbomachinery, 1994, 116, 635., 5.

A study of spike and modal stall phenomena in a low-speed axial compressor.

Turbomachinery, 1998, 120, 393 401., 6.

Effect of tip clearance flow on compressor stability and engine performance.

Stratford, B. The use of boundary layer techniques to calculate the blockage from the annulus wall boundary layer in a compressor.

ASME paper 67-WAGT-7, 1967.

C., Wasdell, D. Off-design prediction of compressor blade losses.

IMechE Conference Proceedings CP 1991-3, paper C423028, 1991.

Engng for Power, 1981, 98, 411., 11.

Van Zante, D. E., Adamczyk, J.

J., Strazisar, A.

J., Okiishi, T. Wake recovery performance benefit in a highspeed axial compressor.

Wennestrom, A. Experimental study of a high through-flow transonic axial compressor stage.

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