Numerical Analysis of a Fuel Pump for an Aircraft Diesel Engine

Sochaczewski, R.; Szlachetka, Marcin

doi:10.1051/matecconf/201925201003

Cited by 9 publications

(6 citation statements)

References 14 publications

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“…The algorithm for calculating the fuel dose is shown in figure 3. This algorithm is based on the use of a common rail system in a diesel engine [20,21]. If the speed difference from the first function is greater than 300 rpm, the correction is calculated by the PC 1 controller.…”

Section: Research Objectmentioning

confidence: 99%

1D modelling and PID control of helicopter Diesel engine rotational speed in torque changes

Magryta

2021

J. Phys.: Conf. Ser.

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The article discusses the results of simulation tests concerning the operation of a diesel engine for a light helicopter. The tests were carried out in the AVL Boost software which is used to analyze dynamic phenomena in internal combustion engines. The research object was a newly designed diesel engine of a V8 structure and a power of 330 kW. This engine was designed to be used in the construction of a light class helicopter. The created one-dimensional simulation model included all the main engine components as well as the connection to the helicopter main transmission and the helicopter rotor. The tests consisted in selecting the P value in the PID controller used to control the amount of fuel injected into the engine. The change in the P value indirectly influenced the reaction of the engine to a change in power and torque during horizontal flight of a helicopter. These changes were introduced by changing thrust torque in the helicopter rotor. The fuel injection regulator was designed to maintain a constant engine rotational speed. The maximum speed deviations from the nominal speed of the engine operation due to both increasing and decreasing speed were analyzed. Additionally, the sum of the deviation values was analyzed until the rotational speed of the tested object stabilized. The results showed that the change of the P parameter affects all the analyzed parameters of the engine operation; however, the minimum deviation values for each parameter occur at non-equal PID settings, which makes it difficult to clearly indicate the appropriate value of the P element.

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Section: Research Objectmentioning

confidence: 99%

1D modelling and PID control of helicopter Diesel engine rotational speed in torque changes

Magryta

2021

J. Phys.: Conf. Ser.

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“…The exact description of the pump and injector submodel was presented in two articles by [21,22]. Therefore, this article focuses on the description of the construction of the fuel rail sub-model.…”

Section: Fuel Supply System Modelmentioning

confidence: 99%

“…However, higher pressure results in greater combustion efficiency and reduced fuel consumption. Considering the phenomena occurring in the flow of fuel through the fuel rail, this aspect of control is important, also due to the dynamic phenomena occurring in the injector, which was analyzed by [21], as well as in the fuel pump as studied by [22]. Sochaczewski [21] analyzed the mass of fuel per one fuel injection process and determined the effective flow field, which allowed the atomizer to be optimized.…”

Section: Introductionmentioning

confidence: 99%

“…Sochaczewski [21] analyzed the mass of fuel per one fuel injection process and determined the effective flow field, which allowed the atomizer to be optimized. In contrast, the publication by [22] focused on developing a model that enables the simulation of pump operation under various conditions defined by the shaft speed, discharge pressure, pump actuator settings as well as fuel properties. In both articles above, the AVL Hydsim simulation tool was used.…”

Section: Introductionmentioning

confidence: 99%

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Modelling of Dynamic Interactions in the Fuel Rail for the Aircraft Diesel Engine

Sochaczewski¹,

Magryta²

2020

Adv. Sci. Technol. Res. J.

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The paper reports a computer model for simulating dynamic responses in fuel rail of aircraft diesel engine. The fuel system was designed for use in a two-stroke compression-ignition engine with opposite pistons. The methodology of building a fuel system model in the AVL Hydsim program and the results of simulation studies were presented. Determination of dynamic phenomena in the fuel rail required the construction of a model of the entire supply system. It is a common rail system with a three-section positive displacement pump and electromagnetic fuel injectors. The system is also equipped with a PID regulator to maintain the present pressure in the fuel rail. For the purposes of the research, two structures of the fuel rail were developed. They differ in dimensions, spacing of the outlet ports and location of the high-pressure connection. The research allowed determining the interactions between the geometry of the fuel rail and the supply method with the fuel pressure and injector mass flow rate. This will optimise the design of the fuel rail for the three-cylinder engine power supply system.

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“…The use of a compression ignition engine in light aviation is also being considered and such aircraft are already in service [19]. Research is also underway to develop an aviation diesel engine with opposed pistons [7,20]. Other concepts to reduce emissions or aircraft power demand are related to interference with aircraft aerodynamics [2] or the use of modern construction materials [22] or even interference with an aircraft shape through the use of smart materials [1,3].…”

Section: Introductionmentioning

confidence: 99%

Analysis of propulsion units dedicated to test stands for aviation systems

Siadkowska¹,

Czajka²,

Ścisłowski³

et al. 2021

Combustion Engines

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This paper presents an analysis of selected propulsion units dedicated to test stands for unmanned aircraft systems. It focuses on engines suitable for aircraft with a maximum take-off mass up to 150 kg. The study includes an analysis of propulsion units that can be used to power systems on stationary test stands dedicated to advanced research and measurement of prototype aerospace technologies intended for use in rotorcraft. The analysis of propulsion units shows that electric units are a better choice for powering UAV rotorcraft test stands. Their main advantages include the possibility to simplify the construction of the device by eliminating gears and to mount the motor in a vertical position, simpler power supply, cooling and control systems and the lack of an exhaust system. Additional advantages are undoubtedly lower vibration generation, cheaper and easier operation as well as better comfort.

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Numerical Analysis of a Fuel Pump for an Aircraft Diesel Engine

Cited by 9 publications

References 14 publications

1D modelling and PID control of helicopter Diesel engine rotational speed in torque changes

1D modelling and PID control of helicopter Diesel engine rotational speed in torque changes

Modelling of Dynamic Interactions in the Fuel Rail for the Aircraft Diesel Engine

Analysis of propulsion units dedicated to test stands for aviation systems

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