A new forward-swept rotor designed by Allison Engine Company was
tested in NASA Lewis Research Center's CE-18 facility. This testing
was a follow-on project sponsored by NASA Lewis to study range
enhancements in small turbomachinery. The test was conducted against
a baseline rotor design that was also tested in CE-18. The design
point for the rotor was a rotor pressure ratio of 2.69, a mass
flow of 10.52 lbm/sec, and an adiabatic efficiency of 89.1 percent.
Test data indicate that the rotor met the pressure ratio of 2.69
with a 10.77 lbm/sec flow rate, a 87.5-percent adiabatic efficiency,
and a 19.5-percent stall margin. The baseline rotor achieved a
pressure ratio of 2.69 at a 10.77 lbm/sec flow rate with a stall
margin of only 9.2 percent and an adiabatic efficiency of 87.0
percent. The major differences are the significant stall margin
increase and the substantially higher off-design peak efficiencies
of the forward-swept rotor. The substantially higher performance
over the baseline rotor design makes the new design a viable technology
candidate for future products.
Previous articleLast updated May 5, 1997
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