Our research group is involved in the development of aviation diesel engines for high altitude applications, and this paper describes the activity concerning the design of new experimental facilities for altitude testing. Two different solutions are evaluated: a hypobaric chamber reproducing altitude effects on the ground and an experimental airplane for testing in flight. The ground test facility should consist of a chamber, within which the engine, the turbo charging and the refrigerating systems are mounted, and in which the atmosphere is maintained at altitude conditions (low pressure and temperature). Different architectures and system designs are discussed and evaluated. The second solution concerns the installation of the test engine as aft engine of a Cessna 337, ‘push-pull’ twin engine aircraft, that provides the possibility to mount two propellers on the aircraft’s centreline. The rear test engine installation has been analyzed to provide all necessary modifications for cowling, cooling systems installation, engine controls, gearbox, fuel system, data acquisition system and test engineer console. A final discussion evaluates advantages and disadvantages of both solutions.
Bagassi S., Francia D., Persiani F. (2009). Design of Facilities for Altitude Testing of Aviation Diesel Engines. MANCHESTER : s.n.
Design of Facilities for Altitude Testing of Aviation Diesel Engines
BAGASSI, SARA;FRANCIA, DANIELA;PERSIANI, FRANCO
2009
Abstract
Our research group is involved in the development of aviation diesel engines for high altitude applications, and this paper describes the activity concerning the design of new experimental facilities for altitude testing. Two different solutions are evaluated: a hypobaric chamber reproducing altitude effects on the ground and an experimental airplane for testing in flight. The ground test facility should consist of a chamber, within which the engine, the turbo charging and the refrigerating systems are mounted, and in which the atmosphere is maintained at altitude conditions (low pressure and temperature). Different architectures and system designs are discussed and evaluated. The second solution concerns the installation of the test engine as aft engine of a Cessna 337, ‘push-pull’ twin engine aircraft, that provides the possibility to mount two propellers on the aircraft’s centreline. The rear test engine installation has been analyzed to provide all necessary modifications for cowling, cooling systems installation, engine controls, gearbox, fuel system, data acquisition system and test engineer console. A final discussion evaluates advantages and disadvantages of both solutions.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
