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38 Gas Turbine Handbook: Principles and Practices tribution of the fuel gas (or greater atomization of the liquid fuel particles) and more rapid and uniform burning and heat release (Figure 3-13). But the problems of equally distributing fuel to each fuel nozzle significantly limit the number of fuel nozzles employed. The second combustor concept is the annular or single combustor. The single combustor is a stand-alone combustor, generally outside the envelope of the compressor and turbine. The annular combustor is also a single combustor but within the envelope of the compressor and turbine (Figure 3-14). Two main distinctions exist between these designs. The single combustor is usually configured with a single fuel nozzle, while the annular combustor must be configured with multiple fuel nozzles. Secondly, the annular combustor incorporates an inner wall or liner and heat shield, which is necessary to protect the rotor. The heavy industrials use a longer combustion chamber, which makes it more suitable for burning poor quality fuel. However, the longer combustor also sacrifices combustor efficiency due to reverse flow pressure losses, a greater surface area to be cooled, and greater heat loss through convection and radiation. Typical materials used in the combustor are listed in Table 3-4. Figure 3-13. Courtesy of Solar Turbines Incorporated. Comparison of the low NO x and standard fuel injectors for the Centaur 50 gas turbine. SoLoNO x is Solar’s designation for it’s low NO x emission engine configuration.
Hardware 39 Figure 3-14. Courtesy of ABB STAL AB. The low NO x , double-coned, EV burner design is used in both the GT10 (25 megawatt) and the GT35 (17 megawatt) gas turbines. The EV burner reduces NO x to 25 ppm - dry. BEARING DESIGN The last major hardware difference between the aero-derivative and heavy and hybrid industrial gas turbines is in bearing design. The aero-derivatives use anti-friction roller and ball bearings while the heavy and hybrid industrials use hydrodynamic bearings. The use of anti-friction bearings in the aero-derivative gas turbines is a
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Page 6 and 7: Dedication This book is dedicated t
Page 8 and 9: Contents PREFACE ..................
Page 10 and 11: Chapter 13—BOROSCOPE INSPECTION .
Page 12 and 13: Preface to the Third Edition The ne
Page 14 and 15: Acknowledgments I wish to thank the
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Chart 8-1 Gas Turbine Environments
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Figure 15-4. Corinth Motor Oil Refi
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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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