Mechanical design analysis of several noncritical air-cooled turbine disks and a corrugated-insert air-cooled turbine rotor blade Page: 4 of 51
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NACA RM E53E21
of 33.5 inches and speed of 8000 rpm. The results obtained, however, can
be generalized to a large extent and should be useful to anyone designing
a turbojet engine that will incorporate an air-cooled turbine rotor. In
the designs presented herein, it is acknowledged that prior library
reviews of the many German designs, such as those presented in reference 9,
may have left their influence.
The following symbols are used in this report:
A cross-sectional metal area, sq in. or sq ft
D diameter of bearing bore, mm
g acceleration due to gravity, ft/sec2
N speed, rpm
n exponent in temperature-gradient equation, dimensionless
r radius, in.
T temperature, OF
V velocity, ft/sec
B angle between radial line and line of bearing contact (see fig. 5)
p metal density, lb/cu in.
a stress, psi
r radius or radial
T blade tip
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Moseson, Merland L.; Krasner, Morton H. & Ziemer, Robert R. Mechanical design analysis of several noncritical air-cooled turbine disks and a corrugated-insert air-cooled turbine rotor blade, report, July 22, 1953; (digital.library.unt.edu/ark:/67531/metadc59615/m1/4/: accessed January 22, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.