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214 Gas Turbine Handbook: Principles and Practices • For gas turbines with an annular design it is sufficient to remove one fuel nozzle from each side of the gas turbine in order to view all of the first stage turbine nozzles and blades. Figure 13-8 is a boroscope view of the internal annular combustor liner and fuel nozzles. This photograph was taken by inserting a flexible boroscope through one of the boroscope ports provided in the combustor section. This procedure would have confirmed the increase in turbine temperature spread and the decrease in combustor efficiency associated with the events leading up to the complete disintegration of the combustor shown in Figure 13-9, the hole in the combustion liner shown in Figure 13-10, and the hole in the transition piece shown in Figure 13-11. Liquid carryover in the fuel gas was the primary cause of the problems depicted in Figures 13-9 and 13-10. Identifying the problem early is preferable to finding it after extensive damage has been done. The combustion process is often accompanied by a high frequency vibration, which can excite the combustor and transition ducts. High frequency movement of the mating metal parts, can and often does, result in fretting and subsequent failure. Detecting the initial fretting is difficult. Once a crack starts it grows rapidly. Therefore, monitoring the turbine temperature or exhaust temperature profile is the best indicator of an internal duct failure. Turbine temperature profile distortions are also caused by burnt, plugged or “coked-up” fuel nozzles as shown in Figures 13-12 and 13-13. Where boroscope ports are available, this condition (once highlighted by a temperature profile change) can be verified quickly and easily. Another alternative is to calculate the swirl effect and remove the suspected fuel nozzles. Frequent use of a boroscope will detect problems such as the small holes in a combustion liner (as shown in Figure 13-14) before the problem becomes serious enough to affect burner efficiency, temperature profile, or unit operation. Turbine Blades And Nozzles Boroscoping through the combustor boroscope ports or the fuel nozzle port, provides a broad view of the first stage turbine nozzles as shown in Figure 13-15. Moving the boroscope closer makes possible a good view of the turbine nozzle airfoil ID and OD platforms as shown in Figure 13-16 and 13-17. This view is sufficiently close to have detected the corrosion, erosion, and burning ( oxidation) shown in
Boroscope Inspection 215 Figure 13-8. Internal boroscope view of annular combustor liner and fuel nozzle after 1,000 hours operation. Figure 13-18 and 13-19, and foreign object damage and cracks shown in Figures 13-20 and 13-21, respectively. By performing periodic gas path analysis, the changes in exhaust gas temperature, fuel flow and rotor speed would have pointed to a diagnosis of an increase in turbine area. The material loss visible in Figures 13-18 and 13-19 is, in fact, an increase in turbine area. Even if the diagnosis was unclear, it would have prompted a visual inspection of the hardware. A flexible fiber-optic boroscope can be inserted through a first stage turbine nozzle for a good view of the first stage turbine blades. By rotating the turbine shaft, all of the first stage turbine blades can be inspected, including the blade tips and rub strips as shown in Figures 13-22, 13-23, and 13-24. With the above inspection techniques, blade surface condition as
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Gas Turbine Handbook: Principles an
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Dedication This book is dedicated t
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Contents PREFACE ..................
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Chapter 13—BOROSCOPE INSPECTION .
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Preface to the Third Edition The ne
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Acknowledgments I wish to thank the
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2 Gas Turbine Handbook: Principles
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100 Gas Turbine Handbook: Principle
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Chart 8-1 Gas Turbine Environments
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Appendix A-2 304 Gas Turbine Handbo
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5. Weather Hood Material __________
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Appendix C-6 Air/Oil Cooler Specifi
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9. Drive Requirements A. Hydraulic
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22. Packaging For Shipment Per Spec
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Parameters Units NH 3 CO H 2 CH 4 C
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.055 Parameters Units 1/0 .88/.12 .
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Koppers Foster Blue Coal Gas Winkle
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