Detailed information of the thermodynamic parameters, system performance, and operating behavior of aircraft auxiliary power units (APU) cycles is rarely available in literature. In order to set up numeric models and study cycle modifications, validation data with well-defined boundary conditions is needed. Thus, the paper introduces an APU test rig based on a Garrett GTCP36-28 with detailed instrumentation, which will be used in a further step as a demonstration platform for cycle modifications. The system is characterized in the complete feasible operating range by alternating bleed air load and electric power output. Furthermore, simulations of a validated numerical cycle model are utilized to predict the load points in the operating region which were unstable during measurements. The paper reports and discusses turbine shaft speed, compressor air mass flow, fuel mass flow, efficiencies, compressor outlet pressure and temperature, turbine inlet and outlet temperature as well as exhaust gas emissions. Furthermore, the results are discussed with respect to the difference compared to a Hamilton Sundstrand APS3200. Though the efficiencies of the GTCP36-28 are lower compared to the APS3200, the general behavior is in good agreement. In particular, the effects of separate compressors for load and power section are discussed in contrast to the GTCP36-28 system design comprising a single compressor. In general, it was shown that the GTCP36-28 is still appropriate for the utilization as a demonstration platform for cycle modification studies.
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January 2019
Research-Article
Characterization of an Aircraft Auxiliary Power Unit Test Rig for Cycle Optimization Studies
Jan Zanger,
Jan Zanger
Institute of Combustion Technology,
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: jan.zanger@dlr.de
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: jan.zanger@dlr.de
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Thomas Krummrein,
Thomas Krummrein
Institute of Combustion Technology,
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: thomas.krummrein@dlr.de
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: thomas.krummrein@dlr.de
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Teresa Siebel,
Teresa Siebel
Institute of Combustion Technology,
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: teresa.siebel@dlr.de
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: teresa.siebel@dlr.de
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Jürgen Roth
Jürgen Roth
Institute of Combustion Technology,
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: juergen.roth@dlr.de
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: juergen.roth@dlr.de
Search for other works by this author on:
Jan Zanger
Institute of Combustion Technology,
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: jan.zanger@dlr.de
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: jan.zanger@dlr.de
Thomas Krummrein
Institute of Combustion Technology,
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: thomas.krummrein@dlr.de
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: thomas.krummrein@dlr.de
Teresa Siebel
Institute of Combustion Technology,
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: teresa.siebel@dlr.de
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: teresa.siebel@dlr.de
Jürgen Roth
Institute of Combustion Technology,
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: juergen.roth@dlr.de
German Aerospace Center (DLR),
Stuttgart 70569, Germany
e-mail: juergen.roth@dlr.de
Manuscript received July 5, 2018; final manuscript received July 17, 2018; published online October 17, 2018. Editor: Jerzy T. Sawicki.
J. Eng. Gas Turbines Power. Jan 2019, 141(1): 011029 (9 pages)
Published Online: October 17, 2018
Article history
Received:
July 5, 2018
Revised:
July 17, 2018
Citation
Zanger, J., Krummrein, T., Siebel, T., and Roth, J. (October 17, 2018). "Characterization of an Aircraft Auxiliary Power Unit Test Rig for Cycle Optimization Studies." ASME. J. Eng. Gas Turbines Power. January 2019; 141(1): 011029. https://doi.org/10.1115/1.4041119
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