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Research Papers: Gas Turbines: Oil and Gas Applications

Degradation Effects on Industrial Gas Turbines

[+] Author and Article Information
Rainer Kurz

 Solar Turbines Incorporated, 9330 Skypark Court, San Diego, CA 92123kurz_rainer_x@solarturbines.com

Klaus Brun

 Southwest Research Institute, San Antonio, TX 78238klaus.brun@swri.org

Meron Wollie

EPT-Mechanical Engineering, BP Exploration and Production, 501 Westlake Park Boulevard, Houston, TX 77079meron.wollie@bp.com

J. Eng. Gas Turbines Power 131(6), 062401 (Jul 15, 2009) (7 pages) doi:10.1115/1.3097135 History: Received October 29, 2008; Revised November 06, 2008; Published July 15, 2009

This paper provides a discussion on how degradation develops and affects the performance of the gas turbine. Because the function of a gas turbine is the result of the fine-tuned cooperation of many different components, the emphasis of this paper is on the gas turbine and its components as a system. Therefore, the interaction of components is studied in detail. An engine model is subjected to various types of degradation, and the effect on operating parameters is studied. The focus is on three areas: How does component degradation impact the operating points of the engine compressor, how does component degradation impact full load and part load gas turbine performance characteristics, and how does component degradation impact measurable engine operating parameters. Experimental data are provided that supports the theoretical conclusion. Parameters that indicate levels of degradation are outlined, thus providing guidance for condition monitoring practice.

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Copyright © 2009 by American Society of Mechanical Engineers
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References

Figures

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Figure 1

Impact of inlet pressure loss on engine power and heat rate

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Figure 2

Schematic compressor map for a two shaft gas turbine (9)

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Figure 3

Compressor discharge pressure as a function of compressor flow for a new compressor and a compressor with 5% reduced efficiency

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Figure 4

Impact of reduced compressor efficiency (reduction of 5%) on the full load heat rate of a single shaft and a two shaft gas turbine for a range of ambient temperatures

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Figure 5

Impact of reduced compressor efficiency (reduction of 5%) on the full load power of a single shaft and a two shaft gas turbine for a range of ambient temperatures

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Figure 6

Impact of reduced compressor efficiency (at constant gas turbine power) on gas generator speed (NGG), firing temperature (turbine rotor inlet temperature (TRIT)), compressor discharge pressure (pcd), heat rate, and airflow for a two shaft engine

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Figure 7

Impact of reduced compressor flow capacity (reduction by 2%) on full load power for a single shaft and a two shaft gas turbine at varying ambient temperatures

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Figure 8

Impact of changed gas generator flow capacity (increased by 5% and decreased by 5%, respectively) on the operating lines of the compressor in a two shaft gas turbine

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Figure 9

Impact of reduced and increased gas generator flow capacities (by 5%, respectively) on full load power at varying ambient temperatures

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Figure 10

Impact of reduced gas generator turbine efficiency (by 2%) on full load power and heat rate for a two shaft gas turbine

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Figure 11

Impact of reduced gas generator turbine efficiency gas generator speed, firing temperature, compressor discharge pressure, heat rate, and air flow for a two shaft gas turbine at constant load

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Figure 12

Compressor operating line for a gas turbine after 40,000 actual operating hours

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