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Gas Turbine Handbook : Principles and Practices

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<strong>Gas</strong> <strong>Turbine</strong> Systems Theory 65<br />

As the (subsonic) velocity of the air decreases with the exp<strong>and</strong>ing<br />

shape of the divergent duct, its static pressure increases, although<br />

the total pressure remains the same. (Note that total pressure is the<br />

sum of the static pressure <strong>and</strong> the velocity pressure; where velocity<br />

pressure is the pressure created by the movement of the air.)<br />

The fraction of the velocity head that is converted to static pressure<br />

( diffuser efficiency) is a function of the area ratio <strong>and</strong> diffuser<br />

angle. Diffuser efficiency is defined as<br />

η D =<br />

1– P o<br />

P i<br />

σ<br />

1– T o<br />

T i<br />

(4-26)<br />

where subscripts i <strong>and</strong> o refer to the pressure <strong>and</strong> temperature entering<br />

<strong>and</strong> exiting the diffuser, respectively. 1 It must be noted that diffuser<br />

effectiveness is the designers problem <strong>and</strong> for most applications<br />

it can be considered part of the combustor efficiency.<br />

The fuel nozzles function is to introduce the fuel into the burner<br />

in a form suitable for rapid <strong>and</strong> complete mixing with air. There are<br />

several types of fuel nozzles: gaseous, liquid, dual gas/liquid, <strong>and</strong><br />

dual liquid/liquid. The liquid fuel nozzle must atomize the fuel into<br />

a fine, uniform spray. Furthermore, it must maintain this spray pattern<br />

throughout the range of operation from starting to maximum<br />

power output. To accomplish this, dual pressure features have been<br />

designed into the fuel nozzles. These are commonly referred to as duplex,<br />

dual orifice, multi-jet, <strong>and</strong> pintle fuel nozzles. The gaseous fuel<br />

nozzles do not share this problem, as the gas is already in a vapor<br />

form.<br />

The combustor itself may be either a series of combustor cans<br />

in an annular configuration, an annual combustor, or a single “st<strong>and</strong><br />

alone” design. Combustors typically have primary air holes at the<br />

dome for mixing with the fuel <strong>and</strong> providing the critical air ratio for<br />

ignition, <strong>and</strong> secondary air holes downstream for additional cooling<br />

(Figure 3-12). Combustor design continues to be an art <strong>and</strong>, although<br />

computer modeling of the air <strong>and</strong> fuel flow within the combustor is<br />

progressing, designs are developed <strong>and</strong> improved by trial <strong>and</strong> error<br />

testing.

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