Calculations for axial compressor blading with uniform inlet enthalpy and radial enthalpy gradient
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A computer program was used to calculate the radial distribution of flow parameters in an axial compressor stage designed to have a symmetrical velocity diagram at the mean radius and particular variations of reaction from hub to tip. Uniform energy addition was assumed to occur in the rotor. Both cases of uniform enthalpy and uniform radial enthalpy gradient at the entrance to the stage were considered. Advantages were found in the selection of fully symmetric blading and in the use of the inlet enthalpy gradient as a design parameter. (Author)
NPS Report NumberNPS67-81-008
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