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.
partianalysisofm00maul.pdf (3.517Mb)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.
Description
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.
Rights
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.Collections
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