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76 7 Conclusion This paper provides an overview of turbo-electric/hydraulic, partial turbo-electric/hydraulic and distributed propulsion system. It mainly examined the decoupling of power generation device and thrust generation device. The quest to find the superior propulsion system model was fulfilled by creating and investigating the effectiveness of all the propulsion systems. The integration of novel propulsion systems into an existing commercial aircraft helped in under- standing the viability of the concepts. The advantages of these technologies were tested based on their direct operating costs, environmental impact and fuel burn. The tools that were re- quired to perform these examinations were developed by HAW Hamburg and modified ac- cording to the requirements of the thesis. A simple mass model for turbo-hydraulic/electric system was developed initially and a total of eight aircraft were compared. The performance of this propulsion system was investigated by enabling them with turboshaft and turboprop engines. It was found that turboshaft engines were preferred compared to turboprop due to their fuel efficiency. During the analysis, it was determined that turbo-hydraulic propulsion system is superior to electric propulsion. The overall performance of the A320 aircraft was slightly overpowered by a turbo-hydraulic air- craft with two engines. Since the gas turbine engine in this model does not produce any thrust among many disadvantages that were discovered, an advanced hybrid model was developed. In order to understand the performance of distributed propulsion, a specific aircraft was se- lected, and the number of engines were increased from 2 to 12 and investigated. During the study, the increase in number of engines demonstrated an increment in DOC. The fluctuations in propeller efficiency and disc loading were also examined. The partial turbo-electric/hydraulic propulsion system was analysed having a turbofan engine to power the fans using shaft off-take power and produce thrust simultaneously. Scholz and Turbomatch methods were used to determine the revised TSFC that will recalculate the DOC for that aircraft. Different thrust levels were set up to investigate the change in performance by using different combinations. A total of 16 models were analysed and compared. Partial turbo-hydraulic concept demotes the performances of A320 and completely turbo-hydraulic concepts. This model for propulsion leads back to jet fuel but it is an initiative towards green- er aircraft for the future. Future research can be carried out by implementing a detailed calculation by including the aerodynamics advantages that can be extracted from this concept. An advanced superconduct- ing material can be used for electric system and components to increase the efficiency to up to a 100%. The core engine of the turbofan engine can be sized accordingly in order to the max- imize the overall efficiency.PDF Image | Comparison of Concepts: Classic Jet Propulsion, Turbo-Electric Propulsion and Turbo-Hydraulic Propulsion
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