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GE Gas Turbine Performance Characteristics this pressure ratio is also equal to the pressure at point 3 divided by the pressure at point 4. However, in an actual cycle there is some slight pressure loss in the combustion system and, hence, the pressure at point 3 is slightly less than at point 2. The other significant parameter, firing temper- ature, is thought to be the highest temperature reached in the cycle. GE defines firing temper- ature as the mass-flow mean total temperature sented as firing temperature by point 3 in Figure 4. Steam-cooled first stage nozzles do not reduce the temperature of the gas directly through mixing because the steam is in a closed loop. As shown in Figure 5, the firing temperature on a turbine with steam-cooled nozzles (GE’s cur- rent “H” design) has an increase of 200 degrees without increasing the combustion exit temperature. OPEN LOOP AIR-COOLED NOZZLE ADVANCED CLOSED LOOP STEAM-COOLED NOZZLE 200F More Firing Temp. at Same NOx Production Possible GT25134 Figure 5. Comparison of air-cooled vs. steam-cooled first stage nozzle at the stage 1 nozzle trailing edge plane. Currently all first stage nozzles are cooled to keep the temperatures within the operating lim- its of the materials being used. The two types of cooling currently employed by GE are air and steam. Air cooling has been used for more than 30 years and has been extensively developed in air- craft engine technology, as well as the latest fam- ily of large power generation machines. Air used for cooling the first stage nozzle enters the hot gas stream after cooling down the nozzle and reduces the total temperature immediately downstream. GE uses this temperature since it is more indicative of the cycle temperature repre- An alternate method of determining firing tem- perature is defined in ISO document 2314, “Gas Turbines – Acceptance Tests.” The firing tem- perature here is a reference turbine inlet tem- perature and is not generally a temperature that exists in a gas turbine cycle; it is calculated from a heat balance on the combustion system, using parameters obtained in a field test. This ISO reference temperature will always be less than the true firing temperature as defined by GE, in many cases by 100 F/38 C or more for machines using air extracted from the compressor for internal cooling, which bypasses the combustor. Figure 6 shows how these various temperatures are defined. GE Power Systems ■ GER-3567H ■ (10/00) 5PDF Image | GE Gas Turbine Performance Characteristics
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