Part I. Analysis of a multi-stage axial compressor with high reaction blading. Part II. A design study of a multi-stage axial compressor with blading of high aspect ratio
PART I: An analysis of a multi-stage axial compressor with high reaction blading is carried out. The usual methods of linearizing the equations for flow through the compressor fail for this type of blading. A numerical-solution of the non-linear equations is worked through for off-design operat...
| Summary: | PART I:
An analysis of a multi-stage axial compressor with high reaction blading is carried out. The usual methods of linearizing the equations for flow through the compressor fail for this type of blading. A numerical-solution of the non-linear equations is worked through for off-design operation. Flow velocities through the first six stages are calculated for the off-design flow rates in order to insure that the flow does indeed come to a steady state repeating pattern. Entering flow angles for both rotor and stator are calculated for this repeating flow condition. The off-design incidence angles for the stators at low flow rates indicate a possible deterioration of efficiency.
PART II:
A method for designing blades of high aspect ratio in a multi-stage axial compressor is investigated. This method requires a calculation of the flow induced by all blade rows. The method is illustrated for the limiting condition of hub ratio equal to unity and then is carried out for the more realistic case of finite hub ratio.
An example of a blade design for a particular flow is carried out. The results are compared with those of a previous design for the same flow conditions but based on a theory applicable for blading of low aspect ratio.
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