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Extra info for Gas Turbine Engineering: Applications, Cycles and Characteristics
1 ). 2. 6 is to reduce the useful output available from the turbine, which therefore also reduces the cycle efficiency relative to the given heat addition. 5). 3 shows the effects of varying the pressure ratio and over-all temperature ratio in a real engine. 1 to compensate. Three sample compression ratios were used: 4, 10 and 20 to 1. Five turbine entry temperatures were used: 800, 1000, 1200, 1400 and 1600 K, with no allowance for blade cooling. The air mass flow was 1 kg/s, the inlet pressure Po 1 was 1 bar and To 1 was 288 K.
To desorb into the high pressure ducting, heat is added at about 373 K from a solar or geothermal source. After regeneration, the high-pressure gas is further heated with high-grade energy from a source at about 973 K. The turbine then drives only the electrical load. It is anticipated that about 90 per cent of the high-grade energy is recovered as electricity, while about three times as much low-grade heat is also required. 6. 3 Cycle Calculations: Design Point Performance Engine performance can be calculated at a multitude of different levels.
9). Carbon dioxide is another relatively inert gas which is a viable working fluid, and might even be replenished from the combustion gases. Nitrogen is used in the regasification of LNG, which provides the cooling necessary before recompression: in this application, the regenerative cycle with external combustion also provides useful shaft power for electricity generation. 10. External combustion experience is expected to lead to the use of helium closed-cycle gas turbines as the means of extracting power from advanced, gascooled nuclear reactors.