Investigation to determine contraction ratio for supersonic-compressor rotor Page: 2 of 16
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NASA Incl illlibr ll il
NACA No E7L23 I Ii i. - . I jJ i h ll
M No. 7L3 3 1176 01425 9916
NATIONAL ADVISORY COMMEE FOR AERONAUTICS
RESEARCH MOIRADTD4
INVESTIGATION TO DETERMINE CONTRACTION RATIO
FOR SUPERSONIC-COMPRESSOR ROTOR
By Linwood C. Wright
SUMMARY
A method of applying the limiting contraction ratio to obtain
the maximum allowable blade thickness of a two-dimensional model
of a supersonic-compressor rotor is proposed. This method requires
the location of the point on the rear of the blade entrance where
the tangent line is parallel to the undisturbed relative flow
velocity in rotor coordinates. A graphical procedure for approxi-
mating this point with what is believed to be sufficient accuracy
is presented. For a given blade spacing, the blade-passage area
is then supposed to be simply a function of the blade thickness and
the sine of the angle between the stagger line and the flow direc-
tion. Experimental evidence that this supposition is reasonably
accurate is presented along with the suggestion that some additional
thickness may be obtained by further turning of the stream in the
supersonic region. In addition, the suggestion is made that the
two-dimensional characteristic lines be constructed to insure that
no subsonic nor too-low supersonic regions result before the mini-
mum section in the passage entrance from reflected compression
waves.
INTRODtUTION
A logical result of effort to extend and to improve the per-
formance of axial-flow compressors has been an increase in interest in
supersonic axial-flow compressors since 1942. A most promising
approach is that first proposed in references 1 to 3. Supersonic-
compressor rotor blades essentially comprise a series of small
rotating supersonic diffusers whose function is exactly the same
as that of conventional supersonic diffusers with internal dif-
fusion. Hence, it has been proposed at the NACA Langley Field
labbratory that the blade passages be considered as diffusers ant
designed on the basis of supersonic-diffuser data (references 1
and 2). Reference 3 reports results obtained on a supersonic-C-1 131
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Wright, Linwood C. Investigation to determine contraction ratio for supersonic-compressor rotor, report, April 30, 1948; (https://digital.library.unt.edu/ark:/67531/metadc58369/m1/2/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.