The Effect of Inlet Temperature and Pressure on the Efficiency of Single-Stage Impulse Turbine Having a 13.2-Inch Pitch-Line Diameter Wheel Page: 4 of 25
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RACA AIR No. E51.~
1.5, 2.0, 3.0, 4.0, 5.C
1.5, 2.0, 3.0 -
The results were
(In. Sg absolute)
in references 1,
2, and 3.
g acceleration due to gravity, 32.2 (ft)/(eec)2, or dimensional
constant, 32.2 (lb)/(elug)
M, mass flow of air plus fuel, (slugs)/(sea)
N turbine speed, (rpm)
Pd static pressure of -turbine discharge at plenan chamber,
(In. g absolute)
p1 total pressure at nozzle-box inlet, (ti. g absolute)
Rb gas constant for ocmbustion products, '(ft-lb)/(lb)(P)
Ti total temperature at nozzle-box inlet, (OR)
1 blade pitah-line speed, (fps)
v theoretical jet speed, (fps)
Wt weight flow of air plus fuel, (lb)/(seo)
qT turbLne officsnoy defined as ratio of shaft power to theo-
reticoal power computed from total temperature and pressure
at turbine inlet and static pressure at turbine discharge
.. . .
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Chanes, Ernest R. & Carman, L. Robert. The Effect of Inlet Temperature and Pressure on the Efficiency of Single-Stage Impulse Turbine Having a 13.2-Inch Pitch-Line Diameter Wheel, report, September 1945; (digital.library.unt.edu/ark:/67531/metadc61853/m1/4/: accessed January 23, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.