Abstract
In this study, the on-going research into the improvement of micro-gas turbine propulsion system performance and the suitability for its application as propulsion systems for small tactical UAVs (<600 kg) is investigated. The study is focused around the concept of converting existing micro turbojet engines into turbofans with the use of a continuously variable gearbox, thus maintaining a single spool configuration and relative design simplicity. This is an effort to reduce the initial engine development cost, whilst improving the propulsive performance. The BMT 120 KS micro turbojet engine is selected for the performance evaluation of the conversion process using the gas turbine performance software GasTurb13. The preliminary design of a matched low-pressure compressor (LPC) for the proposed engine is then performed using meanline calculation methods. According to the analysis that is carried out, an improvement in the converted micro gas turbine engine performance, in terms of thrust and specific fuel consumption is achieved. Furthermore, with the introduction of a CVT gearbox, the fan speed operation may be adjusted independently of the core, allowing an increased thrust generation or better fuel consumption. This therefore enables a wider gamut of operating conditions and enhances the performance and scope of the tactical UAV.
Highlights
Many of today’s Unmanned Air Vehicles (UAVs) are still propeller driven, intended for low speed and low endurance applications
The use of advanced gas turbine propulsion systems enables faster flight speeds with an increased efficiency, but they are only found in larger military medium-altitude long endurance (MALE) and high-altitude long endurance (HALE) UAVs
As on-going operational requirements expand, there is a need for a smaller UAVs with increased mission profile capabilities in terms of speed and endurance
Summary
Many of today’s Unmanned Air Vehicles (UAVs) are still propeller driven, intended for low speed and low endurance applications. The turbojet is the most common configuration of MTE currently found, mostly due to the relative simplicity of manufacture for homebuilders and hobbyists. These systems provide the required thrust for high-speed UAV applications; like the larger architecture, the range is hindered by a relatively poor fuel consumption. This is noted in works by both [1] and [2] that propose the conversion of micro-turbojets into micro-turbofan engines, and whose on-going projects provide the foundation of this study
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