The article discusses the possibility of improving the main characteristics (efficiency, specific thrust) of a gas turbine engine by using liquefied natural gas (LNG) as fuel. This possibility is considered on the example of using as fuel instead of aviation kerosene on PS-90A and NK-93 engines. The parameters of the engine were determined at various stages in the cruise flight mode when operating on kerosene and LNG. The parameters evaluating the fuel consumption of the engine are calculated and compared for both fuels. The performance characteristics for kerosene and LNG were evaluated in the system of the Tu-330 subsonic transport aircraft. Energy losses during storage of cryogenic fuel on board the aircraft are estimated.
This paper proposes the possibility of using a cryogenic power plant as part of a hybrid engine, which can be used in the system of urban transport infrastructure. The model of this cryogenic power plant consists of main contour and auxiliary contour of power plants. The parameters of a hybrid cryogenic power plant were evaluated and the characteristics of the main contour of a hybrid power plant driven by a piston expander and a turbo expander with heat input from both the ambient and the exhaust gases of a diesel engine were calculated. Liquid methane is used as the main fuel. The optimal operation cycle of the auxiliary contour of power plant itself has been determined. For this purpose the main parameters of Rankin and Brayton cycles have been analyzed - consumption, power, efficiency. Besides, the most suitable cryogenic fuels for efficient operation were determined and the schemes of the plants were proposed. The calculations were performed using calculation algorithms, examples of which are presented in this article.
A computational study of the parameters of a propulsion system of an unmanned aerial vehicle operating on a cryogenic working medium has been carried out. Liquid nitrogen was selected as the cryogenic working fluid. Two alternative configurations of a cryogenic propulsion system for an unmanned aerial vehicle are presented. The first one is a scheme of an air-heated cryogenic propulsion system of an unmanned aerial vehicle in which air acts as the heat source at an ambient temperature at an altitude of 2000 m. The second one is a scheme wherein the working fluid is heated due to solar energy, in this case solar energy acts as the source of heat. A computational study of a cryogenic propulsion system operating on the open Rankine cycle was carried out, as well as computational studies of possible cryogenic propulsion system configurations. As a result of the studies a comparative analysis of the data obtained was made and a suitable cryogenic propulsion system configuration for an unmanned aerial vehicle with the required parameters was selected.
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