IEEE Electrification Magazine - December 2014 - 22

NASA Turbine Power Unit Test Run 1681 Electric Output

700

140

600

400
300
200
100
0

100

Time (s)

150

200

Load Output Amperes
Load Output Volts
Electric Output Power
Figure 8. Flight simulation test data.

conclusion

In this article, a method for selecting
an optimal EM for high-perfor100
mance EPGS is discussed. KCs for
EMs are identified, and MRs for EM
80
selection are presented as a part of a
60
high-performance EPGS.
It is concluded that the PMM
40
family is best suited for high-perfor20
mance EPGS applications. The
tooth-type PMM is replacing tooth0
250
less designs due to higher power
density and improvements in foil
bearings. However, depending on
the specific application, any of the
considered six machines may be
selected. Speed increase and implementation of foil bearings are powerful provisions for meeting the
needs of MEA and EOA initiatives.
120

500

160
Electric Output Power (kw)

Electric Output Volts and Amperes

800

would result in a fully gearless/oilfree gas turbine engine.

For Further reading

Figure 9. The gearless/oil-free MEA-IPU advanced concept engine.
(Photo courtesy of Honeywell International.)

Speed-control tests have been performed that involved
operating the system at a range of output power levels
from no load to its maximum output power of 138 kW.
Load transient tests have verified power quality during
step changes in load.
A flight simulation test has been performed that consisted of a run with a load duty cycle similar to what might
be required for a launch vehicle thrust vector control application. The gas generator, the turbine power unit, the power
conditioning, and the control unit operated flawlessly
throughout the test. Flight simulation test data are shown
in Figure 8.
Under Air Force Research Laboratory sponsorship, Honeywell developed a revolutionary new gas turbine engine
demonstrator, the MEA-integrated power unit (IPU). This
IPU incorporates an SRM, a PCU used for self-start and
power conditioning during generation, and magnetic radial
and axial thrust bearings. The system can deliver up to
250-kW peak power (see Figure 9). This advanced technology

I E E E E l e c t r i f i c ati o n M agaz ine / december 2014

E. D. Ganev, "Electrical power generation system and method for
mitigating corona discharge," U.S. patent 7,019,415, June 24, 2008.
M. Koerner and E. D. Ganev, "An electric power generation
system for launch vehicles," SAE 2006-30-61.
E. D. Ganev, "High-reactance permanent magnet machine for
high-performance power generation systems," SAE 2006-01-3076.
R. M. Klaass and C. DellaCorte, "The quest for oil-free gas
turbine engines," SAE 2006-01-3055.
E. D. Ganev, "High-performance electric drives for aerospace more electric architectures," in Proc. IEEE PES Conf.,
2007, 07GM0408.
E. D. Ganev, "Advanced electric drives for aerospace more
electric architecture," SAE 2008-01-2861.

biography
Evgeni Ganev (evgeni.ganev@honeywell.com) is a chief
engineer responsible for electromechanical power systems
at Honeywell International, an engineering and technology
organization in Torrance, California. He has worked on
many aerospace projects for high-speed electric drives,
power-generation systems, and actuation systems as well
as More electric architectures. His experience includes
space applications, commercial and military aircraft, and
military ground vehicles. His work has been materialized in
platforms such as the International Space Station, Space
Station MIR, Joint Strike Fighter, F22, Space Shuttle, Future
Combat System, Airbus A350, Next Generation Jammer, and
Electric Green Taxiing System. He has authored numerous
publications and holds patents covering electric machine
control, power electronics, and magnetic machinery.

Table of Contents for the Digital Edition of IEEE Electrification Magazine - December 2014