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: 5 of 41
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4 r NACA RM No. E7G11
Stator casing. - The stator casing (fig. 2) is split into
equal parts both axially and c ircumferentially. The casing has an
inside diameter of 19 inches and circumferential grooves to support
the nine stator and the two outlet-guide-vane diaphragms. The cas-
ing has an over-all flange-to-flange length of 371 inches.
4
The stator blades are stainless steel and are welded to the
stainless-steel inner and outer shrouds. These shrouds are semi-
circular so each half can be easily mounted in the compressor-
casing grooves. Two retaining screws hold each half of. the dia-
phragm in place. Sheet-metal stripe are welded to the inner shroud
of each stator row of blades (fig. 2(b))both at the inlet and the
outlet to minimize backflow and to form air seals with machined
shoulders on the rotor. The two rows of outlet-guido vanes are
aluminum alloy and are peened to the inner and outer shrouds. From
the outlet-guide vanes to the collector, the air passage forms a
diverging outlet area. In order to simplify the compressor-outlet
instrumentation in this investigation, the divergent area was
straightened by installing a machined insert as recommended in
reference 3.
Rotor. - The X240-2 compressor rotor (fig. 3) is composed of
10 rotor disks that are slotted for blade mounting. The first
nine disks are integral and are machined from a solid aluminum-
alloy forging; the tenth rotor disk, made of steel, is bolted to
the preceding nine rows. Metal is removed between each disk to
decrease weight and to permit the adaptation of the stator-blade
inner shrouds and the metal seal strips. The rotor has a constant
inner diameter of 9.500 inches for the first two stages, after
which the diameter gradually increases through the succeeding
stages to 14 inches at the tenth row. This rotor has a constant
diameter at the blade tips of 18.910 inches. The hub-tip ratios
at the first and the last stages are 0.50 and 0.74, respectively.
The rotor blades are steel and are attached to the rotor by
a bulb-type base in the same manner as the blades of the 19B and
19XB compressors (references 1 and 2). The blades decrease in
height progressively from the inlet to the outlet of the coan-
pressor. A 0.045-inch clearance was maintained between the rotor-
blade tips and the compressor casing. All rotor-blade tips are
grooved to a radial depth of 7/84 inch to minimize damage to the
compressor in case the blade tips rubbed the casing. An axial
clearance of approximately 0.125 inch between stator and rotor
blades was maintained.
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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; (https://digital.library.unt.edu/ark:/67531/metadc63835/m1/5/: accessed April 19, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.