Performance estimation on micro gas turbine plant recuperator

In order to accomplish a thermodynamic analysis of a micro gas turbine plant, while satisfying conditions related to different configurations, different input data sets and a series of imposed thermodynamic parameters, assumptions are necessary regarding the individual performance of the components, for enabling the correlation of overall performance with the performance of the components. The use of a recuperator, even if it can improve a micro gas turbine cycle efficiency, by reducing the fuel consumption for an imposed turbine inlet temperature, will induce a pressure loss on the hot and cold sections, with possible negative influence on the cycle efficiency. In order to investigate this pressure loss, a numerical study was conducted on several cases, by modifying the geometry of a simplified recuperator, using as input a reference micro gas turbine thermodynamic cycle. The comparison between the different results led to the quantification of recuperator’s performance as a function of its geometry

Concept Study of Radio Frequency (RF) Plasma Thruster for Space Propulsion

Electric thrusters are capable of accelerating ions to speeds that are impossible to reach using chemical reaction. Recent advances in plasma-based concepts have led to the identification of electromagnetic (RF) generation and acceleration systems as able to provide not only continuous thrust, but also highly controllable and wide-range exhaust velocities. For Future Space Propulsion there is a pressing need for low pressure, high mass flow rate and controlled ion energies. This paper explores the potential of using RF heated plasmas for space propulsion in order to mitigate the electric propulsion problems caused by erosion and gain flexibility in plasma manipulation. The main key components of RF thruster architecture are: a feeding system able to provide the required neutral gas flow, plasma source chamber, antenna/electrodes wrapped around the discharge tube and optimized electromagnetic field coils for plasma confinement. A preliminary analysis of system performance (thrust, specific impulse, efficiency) is performed along with future plans of Space Propulsion based on this new concept of plasma mechanism