Coolant pump for compression-ignition aircraft engine

4/2019 (179) - CE-2019-408
Autorzy: Michał Jan GĘCA, Konrad PIETRYKOWSKI, Grzegorz BARAŃSKI
The article presents an analysis of  the design of cooling  liquid pumps  for a compression-ignition aircraft engine. A 100 kW  twin- charged, two-stroke, liquid-cooled engine has 3 cylinders and 6 opposed-pistons. In the first part of the study, the amount of heat needed to be removed by the cooling system was estimated to obtain the required volumetric flow rate. Then, the design of automotive cooling liquid pumps for compression-ignition engines with a Common Rail power supply system and power of about 100 kW was analyzed. The aim of the analysis was to select a suitable pump for applications in the aircraft compression-ignition engine. 5 constructions of different shape, diameter and width of the working rotor were selected. The pressure and volume flow rate were determined for a given rotational speed of the pump on a specially built stand. The operation maps of individual pumps were created to select the most efficient types of pumps. 
Słowa kluczowe: diesel engine, opposed piston engine, aircraft propulsion system, cooling system, water pump


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