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Research Papers: Gas Turbines: Turbomachinery

Experimental Investigation of Inlet Distortion Effect on Performance of a Micro Gas Turbine

[+] Author and Article Information
Alireza Naseri

Department of Aerospace Engineering,
Amirkabir University of Technology
(Tehran Polytechnic),
424 Hafez Avenue,
Tehran 15875-4413, Iran
e-mails: naseri.alireza@aut.ac.ir;
anaseri@cttc.upc.edu

Shervin Sammak

Center for Research Computing,
University of Pittsburgh,
3700 Ohara Street,
Pittsburgh, PA 15261
e-mail: shervin.sammak@pitt.edu

Masoud Boroomand

Department of Aerospace Engineering,
Amirkabir University of Technology
(Tehran Polytechnic),
424 Hafez Avenue,
Tehran 15875-4413, Iran
e-mail: boromand@aut.ac.ir

Alireza Alihosseini

Department of Aerospace Engineering,
Amirkabir University of Technology
(Tehran Polytechnic),
424 Hafez Avenue,
Tehran 15875-4413, Iran
e-mail: aliralih@aut.ac.ir

Abolghasem M. Tousi

Department of Aerospace Engineering,
Amirkabir University of Technology
(Tehran Polytechnic),
424 Hafez Avenue,
Tehran 15875-4413, Iran
e-mail: tousi@aut.ac.ir

1Present address: Heat and Mass Transfer Technological Center (CTTC), Universitat Politècnica de Catalunya, Terrassa (Barcelona) 08222, Spain.

2Corresponding author.

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received December 5, 2017; final manuscript received December 8, 2017; published online May 24, 2018. Editor: David Wisler.

J. Eng. Gas Turbines Power 140(9), 092604 (May 24, 2018) (8 pages) Paper No: GTP-17-1647; doi: 10.1115/1.4039057 History: Received December 05, 2017; Revised December 08, 2017

An experimental study has been carried out to determine how inlet total-pressure distortion affects the performance of a micro gas turbine. An inlet simulator is designed and developed to produce and measure distortion patterns at the inlet to the gas turbine. An air jet distortion generator (AJDG) is used to produce nonuniform flow patterns and total pressure probes are installed to measure steady-state total-pressure distribution at the inlet. A set of wind tunnel tests have been performed to confirm the fidelity of distortion generator and measuring devices. Tests are carried out with the gas turbine exposed to inlet flow with 60 deg, 120 deg, and 180 deg circumferential distortion patterns with different distortion intensities. The performance of the gas turbine has been measured and compared with that of clean inlet flow case. Results indicate that the gas turbine performance can be affected significantly facing with intense inlet distortions.

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References

Davis, M. , Hale, A. , and Beale, D. , 2002, “ An Argument for Enhancement of the Current Inlet Distortion Ground Test Practice for Aircraft Gas Turbine Engines,” ASME J. Turbomach., 124(2), pp. 235–242. [CrossRef]
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SAE S-16 Committee, 2002, “Gas Turbine Inlet Flow Distortion Guidelines, Revision B,” SAE International, Warrendale, PA, Standard No. ARP1420B. http://standards.sae.org/arp1420b/
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Figures

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Fig. 1

Distortion screens for direct-connect test setup (Ref.[18])

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Fig. 2

AJDG in a direct connect test setup (Ref. [18])

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Fig. 3

Outlook of the micro gas turbine test facility at Tehran Polytechnic

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Fig. 4

Engine performance test results without inlet distortion

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Fig. 5

Schematic view of the experimental setup used in the tests

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Fig. 6

Air jets and measuring probe's location in the duct cross section

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Fig. 7

Experimental apparatus used in this study

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Fig. 8

Distortion patterns inside the inlet simulator, measured during wind tunnel tests: (a) clean inlet, (b) 60 deg distorted zone, (c) 120 deg distorted zone, and (d) 180 deg distorted zone

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Fig. 9

Total pressure distribution measured at the inlet of the engine: (a) clean inlet, (b) 60 deg distorted zone, (c) 120 deg distorted zone, and (d) 180 deg distorted zone

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Fig. 10

Engine thrust deficit due to inlet distortion

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Fig. 11

Engine SFC increase due to inlet distortion

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Fig. 12

Reduction in compressor's isentropic efficiency due to inlet distortion

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