Analytical investigation of off-design performance of a transonic turbine Page: 5 of 24
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NACA M E54D05
Scr squared ratio of critical velocity at turbine inlet to critical
velocity at NACA standard sea-level temperature, (V/Vr)2
cr conditions at Mach number of 1.0
x axial component
0 stator inlet (fig. 1)
1 stator throat
2 station just inside rtator trailing edge
3 stator outlet, rotor inlet
4 rotor throat
5 station just inside rotor trailing edge
6 rotor outlet, turbine outlet
absolute total state
* NACA standard conditions
Analytical Performance and Losses
The over-all analytical performance and loss breakdown were cal-
culated in the same manner as described in reference 4, except that the
stator- and rotor-exit shock losses were based on the free-stream veloc-
ities (stations 3 and 6, fig. 1) rather than on those at stations 2
and 5. However, the difference in shock loss resulting from this as-
sumption is felt to be negligible, since the velocities at stations 2
and 3 are nearly equal, as are those at stations 5 and 6. Because it
was developed for subsonic turbines, the method assumes that the rotor
passage is convergent and the minimum area is at the exit of the pas-
sage. For the transonic turbine of reference 1, the minimum area is
about midway between blade entrance and blade exit, the difference in
flow area, however, between the minimum-area station and the blade exit
being only of the order of 0.1 of 1 percent. The value 0.45 of the
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Whitney, Warren J. & Stewart, Warner L. Analytical investigation of off-design performance of a transonic turbine, report, May 28, 1954; (https://digital.library.unt.edu/ark:/67531/metadc64479/m1/5/: accessed May 26, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.