HIT09 designs and develops small turbojet and turbo-shaft engines suitable for application to ultra-light aircrafts and helicopters, gliders, UAV and energy generation.
In particular, HIT09 has identified target customers in the subsector of Small Manned Aerial Vehicles (SMAV) and Unmanned Aerial Vehicles (UAV) and proposes high power-to-weight ratio propulsion systems.

Small gas turbines have intrinsic advantages over other propulsion systems when applied in SMAVs and UAVs. Advantages include higher power-to-weight ratio, fuel flexibility and small power de-rating, as well as a better vibration behaviour. Also, pollutant emissions are generally of lesser concern. On the other hand, some drawbacks are generally found in higher costs and higher specific fuel consumptions. Actually these drawbacks have generally led to either unsuccessful implementations or prevented the use of gas turbines on SMAVs and UAVs.

By means of a dedicated design we are capable of reducing costs by a factor of 2 with respect to conventional gas turbines. On the other hand, the design of a special recuperated cycle allows us to nearly halve the specific fuel consumption. Other advantages include fuel flexibility and limited power de-rating with flight altitude.
Our goal is to definitely implement technological solutions for making small gas turbines efficient and competitive. We can provide full engineering services and customized prototype production.

The following is a list of capabilities and references we can offer to this purpose:

  • Validated in-house engine deck simulation tool for design and analysis of gas turbines (success cases include Solar Titan T62 turbine and GE T700 engines [1-2]).
  • Engine test bench for thrust and performance measurement [3].
  • Qualified prototype construction workshop according to EN-ISO 9000 quality standards, including 5-axis CNC.
[1] E. Benini, A. Toffolo, A. Lazzaretto, Experimental and numerical analyses to enhance the performance of a microturbine diffuser, Experimental thermal and fluid science 30 (5), 427-440, 2006.
[2] G.A. Misté, E. Benini, Improvements in Off Design Aeroengine Performance Prediction Using Analytic Compressor Map Interpolation, Int. J. Turbo Jet-Engines 29 (2), 69-77, 2012.
[3] E. Benini, S. Giacometti, Design, manufacturing and operation of a small turbojet-engine for research purposes, Applied Energy 84 (11), 1102-1116, 2007.

Products currently under development are a turbojet in the size of 175 daN thrust and a turbo-shaft in the range of 120 kW.