Research Papers: Gas Turbines: Microturbines and Small Turbomachinery

Demonstration of Model-Based, Off-Line Performance Analysis on a Gas Turbine Air Compressor

[+] Author and Article Information
Ashley P. Wiese

e-mail: awiese@unimelb.edu.au

Chris Manzie

Department of Mechanical Engineering,
The University of Melbourne,
Parkville, Victoria,

Anthony Kitchener

SVW Pty. Ltd.,
Spotswood, Victoria,

Contributed by International Gas Turbine Institute (IGTI) of ASME for publication in the Journal of Engineering for Gas Turbines and Power. Manuscript received June 28, 2012; final manuscript received August 20, 2012; published online January 8, 2013. Editor: Dilip R. Ballal.

J. Eng. Gas Turbines Power 135(2), 022301 (Jan 08, 2013) (7 pages) Paper No: GTP-12-1238; doi: 10.1115/1.4007731 History: Received June 28, 2012; Revised August 20, 2012

This paper presents a model-based, off-line method for analyzing the performance of individual components in an operating gas turbine. This integrated model combines submodels of the combustor efficiency, the combustor pressure loss, the hot-end heat transfer, the turbine inlet temperature, and the turbine performance. As part of this, new physics-based models are proposed for both the combustor efficiency and the turbine. These new models accommodate operating points that feature the flame extending beyond the combustor and combustion occurring in the turbine. Systematic model reduction is undertaken using experimental data from a prototype, microgas turbine rig built by the group. This so called gas turbine air compressor (GTAC) prototype utilizes a single compressor to provide cycle air and a supply of compressed air as its sole output. The most general model results in sensible estimates of all system parameters, including those obtained from the new models that describe variations in both the combustor and turbine performance. As with other microgas turbines, heat losses are also found to be significant.

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Fig. 1

GTAC schematic and instrumentation

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Fig. 3

Turbine exit temperature compensation

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Fig. 4

GTAC performance measures: rp,c = 3(·), rp,c = 2.5(+), rp,c = 2(×) (a) efficiency, (b) equivalence ratio, (c) bled-mass fraction, (d) fuel flow rate

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Fig. 5

Results for variable ηt: (a) measured and modeled exit temperature, (b) error in overall energy balance, (c) fuel burnt in combustor, (d) combustor pressure ratio

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Fig. 7

Modeled ηt for curve fit optimization: rp,c = 3(·), rp,c = 2.5(+), rp,c = 2(×)

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Fig. 6

Modeled turbine inlet temperature for case A: rp,c = 3(·), rp,c = 2.5(+), rp,c = 2(×)

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Fig. 8

Error in overall energy balance without heat loss model



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