Research Papers: Gas Turbines: Turbomachinery

Influence of Fouling on Compressor Dynamics: Experimental and Modeling Approach

[+] Author and Article Information
Gbanaibolou Jombo

Centre for Propulsion Engineering,
School of Aerospace, Transport
and Manufacturing,
Cranfield University,
Cranfield MK43 0AL, UK
e-mail: g.jombo@cranfield.ac.uk

Jiri Pecinka

Department of Air Force and Aircraft Technology,
University of Defence,
Brno 662 10, Czech Republic
e-mail: jiri.pecinka@unob.cz

Suresh Sampath

Centre for Propulsion Engineering,
School of Aerospace, Transport
and Manufacturing,
Cranfield University,
Cranfield MK43 0AL, UK

David Mba

Faculty of Technology,
De Montfort University,
Leicester LE1 9BH, UK

1Corresponding author.

Contributed by the Turbomachinery Committee of ASME for publication in the JOURNAL OF ENGINEERING FOR GAS TURBINES AND POWER. Manuscript received June 7, 2017; final manuscript received July 24, 2017; published online October 17, 2017. Assoc. Editor: Klaus Brun.

J. Eng. Gas Turbines Power 140(3), 032603 (Oct 17, 2017) (7 pages) Paper No: GTP-17-1202; doi: 10.1115/1.4037913 History: Received June 07, 2017; Revised July 24, 2017

The effect of compressor fouling on the performance of a gas turbine has been the subject of several papers; however, the goal of this paper is to address a more fundamental question of the effect of fouling, which is the onset of unstable operation of the compressor. Compressor fouling experiments have been carried out on a test rig refitted with TJ100 small jet engine with centrifugal compressor. Fouling on the compressor blade was simulated with texturized paint with average roughness value of 6 μm. Compressor characteristic was measured for both the clean (baseline) and fouled compressor blades at several rotational speeds by throttling the engine with variable exhaust nozzle. A Greitzer-type compression system model has been applied based on the geometric and performance parameters of the TJ100 small jet engine test rig. Frequency of plenum pressure fluctuation, the mean disturbance flow coefficient, and pressure-rise coefficient at the onset of plenum flow field disturbance predicted by the model was compared with the measurement for both the baseline and fouled engine. Model prediction of the flow field parameters at inception of unstable operation in the compressor showed good agreement with the experimental data. The results proved that used simple Greitzer model is suitable for prediction of the engine compressor unstable behavior and prediction of the mild surge inception point for both the clean and the fouled compressor.

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Fig. 1

Layout of small jet engine test rig showing measurement points

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Fig. 2

Simulated fouling pattern in test rig compressor

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Fig. 3

Texturized fouling paint layer

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Fig. 4

Baseline versus fouled compressor pressure map

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Fig. 5

Nondimensional map of clean and fouled compressor

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Fig. 6

Compressor discharge pressure oscillations in time and frequency domain for 90% RPM

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Fig. 7

Overview of a Greitzer compression system model

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Fig. 8

Geometric parameter of experimental test

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Fig. 9

Generalized pressure-rise characteristic for test rig based on experimental data

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Fig. 10

Plenum pressure disturbance frequency for baseline and fouled operations

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Fig. 11

Disturbance mean flow coefficient for baseline and fouled operations

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Fig. 12

Disturbance mean pressure-rise coefficient for baseline and fouled operations

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Fig. 13

Measured time waveform for the plenum pressure-rise coefficient at 0.85 of rated speed



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