DEVELOPMENT OF AN ULTRA-HIGH EFFICIENCY GAS TURBINE ENGINE (UHEGT

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DEVELOPMENT OF AN ULTRA-HIGH EFFICIENCY GAS TURBINE ENGINE (UHEGT ( development-an-ultra-high-efficiency-gas-turbine-engine-uheg )

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rate. On the bottom side of this figure, the turbine output power, compressor input power, and the total fuel energy are shown. The cycle thermal efficiency is calculated as, 𝑊−𝑊 𝜂𝑡h = 𝑡𝑢𝑟𝑏 𝑐𝑜𝑚𝑝 (5.3) 𝑄𝑓𝑢𝑒𝑙 The incoming air at atmospheric pressure and temperature (1 atm, 300 K) and mass flow rate of 150 kg/s passes through the compressor with the pressure ratio of 40:1. The high pressure air is injected with 2.3 kg/s of fuel flow in the first combustion stage. The high pressure and temperature gas then expands in the first turbine stage with the pressure ratio of 1.55:1. After that, the gas passes through the second combustor and the same combustion-expansion process takes place again. After the final combustion stage, the gas reaches its highest temperature (1500 K). At this point, it has expanded through the first two turbine stages and is at the pressure of 15.5 bar. The high pressure hot gas then expands through the last turbine set which consists of four turbine stages. At the exit point, the mixture is at atmospheric pressure and a relatively high temperature (869.1 K). The exit gas could be used in a following power cycle (combined system) to considerably increase efficiency. After the cycle design is finalized, all of the stage parameters are calculated as explained in the previous section. Table 3 shows the turbine stage parameters at mean section for the current design. The rotational speed is N=6000 rpm and the hub diameter is Dhub=0.5 m for all stages. The geometry of the turbine is discussed in the next section. 82

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