Proposal was a systematic study of thermal heat recovery for rotorcrafts which aim at generating electrical power from heat losses. These systems decrease the electrical load input required from the engine and achieve an overall increase in thermal efficiency of the rotorcraft propulsion system. A second aim is to study how such systems contribute to the cooling of main drive trains by pumping out heat. More specifically the following project work tasks will be carried out;
- Exploitable thermal loss sources of rotocraft systems will be identified and quantified,
- Worldwide study of potential innovative and novel solutions will be reviewed. The specific power, specific power density outputs, specific volume and specific cost of such systems will be thoroughly evaluated. Risk assessments with regards to rotorcraft performance, magnetic and electrical interferences, flight safety and structural integrity will be carried out,
- Heat and power balance flow diagrams and exergy analysis of most promising candidates heat recovery electrical systems will be carried out. An energy flow behavioural model of each of the systems which take into account a representative helicopter power and thermal networks will be established,
- A detailed simulation and design of a robust rotorcraft power networks will be developed in SABER. High level behavioural model of the most promising heat recovery electrical generators will be included,
- The mock-up of the most representative heat recovery electrical generation device will be manufactured and the performance capability verified. A nominal power production around 1 KW will be chosen.
- The mock-up potential verification will first be carried out with a main heat input from a ground/laboratory based 200kW size helicopter turboshaft engine test bed. The mock-up will then be tested in a second aircraft installation application environment that will be determined later.
RECYCLE advanced technologies devoted to the development of waste heat recovery electrical generation systems dedicated to rotorcrafts, with specific objectives like weight optimisation and proof of feasibility in the helicopter thermal environment.