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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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degrees is applied to the cooling holes on the suction and pressure surfaces at each location. This will help to prevent the cooling jets from lift off or separation from the surface [100]. The blowing ratio (𝑀 = 𝜌𝑗𝑉𝑗 ) for the cooling jets is about 1. This blowing 𝜌∞𝑉∞ ratio has been chosen because it provides enough power for the jet to penetrate the main flow while preventing it from separating from the blade surface. Moreover, the mixing losses are minimum at this blowing ratio [100], [101]. V.5.2 Results and Discussion Figure 64 shows the midspan Mach number distribution and velocity vectors in configuration 1. As shown in this figure, the flow is closely following the blade metal angle and the incidence angle is minimized in stator and rotor. The maximum Mach number in the rotor throat does not exceed 0.85 which represents a subsonic flow along the entire passage. Moreover, the approaching flow Mach number is about 0.1 which provides a suitable environment to achieve a stable combustion process [60], [62]. The Mach number distribution and velocity vectors in configurations 2 to 4 are similar to configuration 1 with slight differences. Therefore, the figures have not been presented independently to avoid repetition. Moreover, it should be mentioned that the stage power calculated by the CFD simulation in configuration 1 (23.0 MW) only slightly differs from the results of meanline calculation (22.1 MW). Similar agreement is observed in other parameters such as velocity, pressure, temperature, etc. This further validates the results of both simulations, considering the two methods use completely different approaches and tools to solve the problem. 102

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