Research Papers

Characterization of an Aircraft Auxiliary Power Unit Test Rig for Cycle Optimization Studies

[+] Author and Article Information
Jan Zanger

Institute of Combustion Technology,
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

Teresa Siebel

Institute of Combustion Technology,
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

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 141(1), 011029 (Oct 17, 2018) (9 pages) Paper No: GTP-18-1446; doi: 10.1115/1.4041119 History: Received July 05, 2018; Revised July 17, 2018

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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Fig. 2

GTCP36-28 cycle layout and instrumentation

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Fig. 1

Mobile APU test rig container

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Fig. 9

Turbine inlet T4 and outlet temperature T5 as a function of bleed air mass flow m˙bl

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Fig. 7

Electric ηel and overall ηov efficiency as a function of overall power output Pov

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Fig. 3

Operating range of GTCP36-28

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Fig. 4

Turbine shaft speed N as a function of bleed air mass flow m˙bl

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Fig. 5

Compressor air mass flow m˙air as a function of bleed air mass flow m˙bl

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Fig. 6

Fuel mass flow m˙fuel as a function of overall power output Pov

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Fig. 11

NOx, CO, and UHC exhaust gas emissions as a function of bleed air mass flow m˙bl

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Fig. 8

Compressor outlet pressure p3 and temperature T3 as a function of bleed air mass flow m˙bl

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Fig. 10

Global air number λcc,global of the combustion chamber as a function of bleed air mass flow m˙bl



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