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Preliminary research of microgasturbine injection ring

100%

Czarnecki M. , Orkisz M. , Wołoszyn T.

tom Vol. 17, No. 4

117-122

Fuel supply systems used in microgasturbines are designed in experimental way. In literature they exist as geometrically prescribed that is proper in general. In commercial aeroengines injection system is the most vulnerable part which failure generates high thermal loads and causes overheating of whole "hot section " or part of it. Microgasturbines are subjected to overheating due to relative short combustion section and uneven fuel distribution in injection points. Presented article contains preliminary research of fuel injector ring designed for microgasturbine turbojet. Tested fuel collector is supplied from the single source and feeds five vaporizers. Investigations are focused on mass flow measurement from each supply point. Research methodology is similar to supervisory tests carried out on commercial aeroengines. Injector was tested with two types of microfuelpumps: JetCAT A60I405 and FlightWorks 200C. As a working liquid the JET A l kerosene was used For each probe constant volume of liquid was pumped through the system. Pumps were tested infull operational range of voltage. Electric power characteristics were obtained for fuel pump and whole fuel system. The strong influence of throttling on stability of microfuelpumps was affirmed. As a conclusion there is a modernization proposal that aims on quality and quantity of fuel distribution.

The influence of operating conditions of the marine gas turbine engine on the level of emission of pollutants contained in the exhaust

63%

Wirkowski P. , Markowski J.

tom R. 58, nr 3

218--223

Pollution emission tests from turbine engines used for the main propulsion of vessels require measurement of the concentration of harmful compounds in the exhaust and assessment of the exhaust gases mass generated by the engine. The concentration of harmful compounds can be determined in a direct way by measuring it in the stream of exhaust gases. However, due to the large output of exhaust gases, the mass of exhaust gases must be determined indirectly. To do this it is necessary to carry out a series of tests and analyzes that will enable parameterization of operating conditions. The obtained parameters and functional relations between them can be used to assess the mass of generated exhaust gases. The article presents analyzes related to the methodology for assessing the mass of exhaust gases generated by the main propulsion turbine engine of the vessel, and the manner of their use in the assessment of emission of harmful exhaust gases.

Airflow analysis of the microgasturbine axial turbine stage

63%

Czarnecki M. , Orkisz M.

tom R. 48, SC1

242--246

Presented paper consists detailed analysis of the airflow in micro gasturbine. Calculations was made for axial turbine with given mass flow rate m=0,15 [kg/s] and total inlet temperature T3* = 950 [K]. Presented analysis is useful for gasturbines with mass flow rate smaller than 0.5 [kg/s]. As a major conclusions for designers of microgasturbines there is a considerations that require to be very careful and forewarn that typical correlations for commercial gasturbines couldn’t be take it as granted.

Prezentowana praca zawiera szczegółową analizę przepływu przez stopień osiowy turbiny mikroturbinowego silnika odrzutowego. Obliczenia wykonano dla osiowej turbiny o masowym natężeniu przepływu m=0,15 [kg/s] i temperaturze spalin przed turbiną 3*T = 950 [K]. Analiza jest przydatna dla silników o masowym natężeniu przepływu powietrza w kanale silnika mniejszym niż 0.5 [kg/s]. W wyniku przeprowadzonych obliczeń stwierdzono że w przypadku mikromaszyn przepływowych obliczenia należy wykonywać ze szczególną starannością gdyż przyjęcie założeń oraz uogólnień typowych dla całej rodziny maszyn przepływowych uniemożliwia uzyskanie poprawnego rozwiązania.