Some Effects of Blade Trailing-Edge Thickness on Performance of a Single-Stage Axial-Flow Compressor Page: 3 of 16
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NACA RM E51F28
efficiency. The data of references I to 3 indicate that to obtain max-
imum blade-section efficiency, the thickness of the trailing edge
should be as small as possible. On the other hand, no appreciable
trailing-edge-thickness effect on blade performance for thicknesses up
to 20 percent of the maximum blade thickness is indicated in refer-
ence 4.
Results for isolated airfoils presented in reference 5 show that
an increase in lift and an increase in profile losses occur when
trailing-edge thickness is increased. If the lift increases, a
decrease in blade-section lift-drag ratio will not necessarily result
in a decrease in compressor efficiency because blade-profile losses are
only a small part of the total losses of a compressor. Therefore the
investigation was conducted to determine the effect of blade trailing-
edge thickness on the performance of a typical axial-flow compressor
stage.
A single row of compressor blades with modified NACA blower blade
sections of 65-(14)10, 65-(9.6)09, and 65-(7.3)08 at the hub, mean,
and tip radius, respectively, was installed in a 14-inch diameter
single-stage compressor test rig. The performance of this blade row
was compared over a range of flows at six equivalent tip speeds from
450 to 915 feet per second for trailing-edge thicknesses of 0.045,
0.030, and 0.015 inch.
As a check on the results obtained from the compressor tests, a
brief supplementary investigation was made on a two-dimensional cascade
of NACA 65-(12)10 blades with trailing-edge thicknesses of 0.045 and
0.010 inch.
SYMBOLS0B
The following symbols are used in this report:
P absolute total pressure, (Ib/sq ft)
r radius to blade element, (ft)
Ut blade-tip velocity (ft/sec)
Ut/A4e equivalent tip speed, (ft/sec)
W weight flow, (lb/sec)
Wr//6 weight flow corrected to NACA standard sea-level conditions,
(lb/sec)..mod
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Moses, J. J. & Serovy, G. K. Some Effects of Blade Trailing-Edge Thickness on Performance of a Single-Stage Axial-Flow Compressor, report, October 26, 1951; (https://digital.library.unt.edu/ark:/67531/metadc58924/m1/3/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.