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Gas Turbine Handbook : Principles and Practices

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Detectable Problems 183<br />

Chapter 12<br />

Detectable Problems<br />

As with any piece of mechanical equipment, the gas turbine<br />

is susceptible to a wide variety of physical problems. These<br />

problems include such things as dirt build-up, fouling,<br />

erosion, oxidation, corrosion, foreign object damage, worn bearings,<br />

worn seals, excessive blade tip clearances, burned or warped turbine<br />

vanes or blades, partially or wholly missing blades or vanes, plugged<br />

fuel nozzles, cracked <strong>and</strong> warped combustors, or a cracked rotor disc<br />

or blade. <strong>Gas</strong> turbine problems may be detected by concentrating on<br />

four general areas: 1) the thermodynamic gas path, 2) vibration of<br />

bearings, rotors, etc., 3) lubrication, <strong>and</strong> 4) controls. The information<br />

gathered will often be the result of an interdependent parameter relationship<br />

<strong>and</strong> will assist in verifying a diagnosis <strong>and</strong> more precisely<br />

isolating a fault.<br />

Some of these problems will become evident as vibration increases,<br />

others will be detected by a change (increase or decrease) in<br />

lubrication oil temperature. However, some problems (often the most<br />

serious problems) can be detected only through gas path analysis.<br />

The gas path, in its simplest form, consists of the compressor(s),<br />

combustor, <strong>and</strong> turbine(s). The operation of each component follows<br />

predictable thermodynamic laws. Therefore, each component will<br />

behave in a predictable manner when operating under a given set of<br />

conditions.<br />

Detectable faults make themselves evident through changes in<br />

observed engine parameters. Actually these faults are the result of<br />

changes in component geometry. Therefore, it is necessary to identify<br />

the geometry changes in order to evaluate the severity of the problem.<br />

Lou Urban, in his book “<strong>Gas</strong> <strong>Turbine</strong> Parameter Interrelationships” 1 ,<br />

defined the measurable engine parameters (rotor speed, temperature,<br />

pressure, fuel flow, <strong>and</strong> power output) as dependent variables <strong>and</strong><br />

pumping capacity, efficiency, <strong>and</strong> effective nozzle areas as independent<br />

variables. To further simplify matters it is usually not necessary<br />

183

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