Investigation of 10-stage axial-flow X24C-2 compressor, 1, performance at inlet pressure of 21 inches mercury absolute and inlet temperature of 538 degrees R Page: 4 of 41
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NACA RM No. E7G11
measurements. For the phase of the investigation reported herein,
runs with an inlet temperature of approximately 5380 R were made at
30, 40, 47, 55, 85, 72, 80, and 89 percent of design speed at an
inlet pressure of 21 inches of mercury absolute. At design speed,
however, excess pressure drop through the compressor-inlet piping
limited the inlet pressure to 19.5 inches of mercury absolute. At
each speed runs were made over the entire range of surge-free air
flows. Compressor pressure ratio, weight flow, adiabatic
temperature-rise efficiency, pressure coefficient, and other per-
formance characteristics as well as the results of interstage
static-pressure measurements are presented.
The 1240-2 compressor was designed for an air-weight flow of
54.6 pounds per second and a pressure ratio of 4 at 12,000 rpm
with sea-level inlet conditions. The compressor consists of a row
of inlet-guide vanes, 10 rows of rotor blades, nine rows of stator
blades, and two rows of outlet-guide vanes. The pertinent blade
data are given in table I. The compressor has a maximum over-all
diameter of 235 inches at the outlet and is 44 inches in length
from the inlet section to the -outlet section. It is composed of
three component parts: the inlet section, the stator casing, and
Inlet section. - The cast-aluminum inlet section (fig. 1) of
the X240-2 compressor has an annular air passage with an inner and
outer diameter of 75 and 21 inches, respectively. The length of
the inlet section, exclusive of the inlet-guide vanes, is 69 inches.
Four airfoil-shaped struts support the front bearing housing. Pas-
sages within these struts provide for the front bearing lubrication
and the accessory drive.
The inlet-guide vanes are fully shrouded and the inner shroud
is securely bolted to the rear of the inlet section. The inner
and outer shrouds are tapered to provide a converging air passage
from the inlet to the outlet of the blades. The inner-shroud
diameter of the inlet-guide vanes increases from 7 to 9 inches
and the outer-shroud diameter decreases from 21 to 19 inches, the
stator-casing inner diameter. The inlet-guide vanes turn the air
in the direction of rotor rotation. The 34 aluminum blades have a
uniform chord length from base to tip. A hemispherical hub is
attached to the entrance of the inlet section to provide smooth
air entry into the compressor proper.
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Schum, Harold J. & Buckner, Howard A., Jr. Investigation of 10-stage axial-flow X24C-2 compressor, 1, performance at inlet pressure of 21 inches mercury absolute and inlet temperature of 538 degrees R, report, July 15, 1947; (digital.library.unt.edu/ark:/67531/metadc63835/m1/4/: accessed December 16, 2018), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.