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.

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Authors
Mauldin, James H.
Subjects
Advisors
Rannie, W.D.
Date of Issue
1963
Date
1963
Publisher
California Institute of Technology
Language
en_US
Abstract
ABSTRACT FOR 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. ABSTRACT FOR PART II A method for designing blades of high aspect ratio in a multistage 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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Thesis
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This thesis document was issued under the authority of another institution, not NPS. At the time it was written, a copy was added to the NPS Library Collection for reasons not now known. It has been included in the digital archive for its historical value to NPS. Not believed to be a CIVINS (Civilian Institutions) title.
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California Institute of Technology
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This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
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