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Abstract

This paper presents the methodology and investigation of the sound power level produced by a radial piston aircraft engine operating at varied speeds. The research model aircraft engine of a maximum power of 5.5 kW with a two-bladed airscrew was placed on a test bend. Its sound power level was calculated from the sound pressure level measured at 9 measurement points distributed on a hemispherical surface in a confined space in line with PN-EN 3744. Mean sound power generated by the ASP FS400AR engine is 96 dB at idle (2,880 rpm) and 105 dB at a cruising speed (4,740 rpm). Accordingly, it can be concluded that a sound level meter registered a higher sound power level at the points in front of the model aircraft engine than at the points behind it, whereas the lowest sound power level was registered directly above the engine.

networks embedded in “more electrical aircraft” Proceedings of 2011 IEEE International Symposium on Industrial Electronics (ISIE), pp. 26-31. [10] Pietrykowski, K., 2011, “Research on the mixture formation process in a radial engine”, Combustion Engines, PTNSS–2011–SC–015. [11] Gęca, M., Wendeker, M., Litak, G., 2012, “Combustion variability and uniqueness in cylinder of a large power radial engine, Journal of Vibroengineering”, Vol. 14, Issue 2., pp. 582-591. [12] Grabowski, Ł., Tulwin, T., Geca, M. and Karpiński, P., 2016, “Validation Study of Radial Aircraft Engine

Imaging, Inc. 2009. [4] Kowalski M.: Maintenance of gas turbine engines with the phase mapping method applied. The Problems of Studying, Testing and Operating Aeronautical Systems. Vol. 8, Chapter 7, AFIT, Warszawa 2012 (in Polish). [5] Kowalski M., Szczepanik R.: Phase mapping and analysis of the performance of an aircraft engine with full-range microprocessor-based engine control unit FADEC type. The Problems of Studying, Testing and Operating Aeronautical Systems. Vol. 7, Chapter 10, AFIT, Warszawa 2010 (in Polish). [6] Kułaszka A., Błachnio J.: A non

Abstract

The article is focused on building the algorithm for identification the fatigue crack length in the first stage of compressor blade of the helicopter PZL-10W turbo-shaft engine. The fatigue wear of compressor blade is a process in which the fatigue crack begins at the structural notch of the working part. For compressor blade, the crack starts at the leading edge and progress along the blade chord. Due to working conditions, the compressor blades are referred to as critical components. The helicopter rotor downwash can easily lift particles form the ground that may cause damages in the compressor section. Aircraft engines are designed so that the rotational speed of impeller remains below the resonant frequency. However, the pulsation of working medium or mechanical vibrations may cause temporary increase of vibration frequency. The appearance of structural notch combined with temporary increase of vibrations may initiate the fatigue failure. The works undertaken at the Department of Aircraft and Aircraft Engines, Rzeszow University of Technology provided a wide spectrum of research data of amplitude-frequency (A-F) characteristics of 1st stage of compressor blade. For different crack lengths, the fatigue tests of resonant frequency and asymmetry of A-F characteristics were acquired. The crack lengths were measured by fluorescent or infrared mapping method. The aim of the article is to develop the numerical method for identification of crack length of compressor blade basing on A-F characteristics. The studies on A-F characteristics in order to find correlations between crack length, resonant frequency and characteristics asymmetry were performed. The next step was to build the algorithm for identification the crack length when only A-F characteristic is known. The article contains the description of researches background, A-F characteristics unique features, algorithm detailed methods of work and sample use of algorithm in identification the crack length.

5. References [1] Dzierżanowski P., Kordziński W., Łyżwiński M., Otyś J., Szczeciński A., Wiatrek R.: Turbinowe silniki odrzutowe [Turbine jet engines]. WKŁ, Warszawa 1983. [2] Kowalski M., Kozakiewicz A.: Unstable operation of the turbine aircraft engine. Journal of Theoretical and Applied Mechanics, Vol. 51, No. 3, pp. 719-727, 2013. [3] Kowalski M., Szczepanik R.: Analiza pracy silnika PZL-10WM z pełnozakresowym, mikroprocesorowym układem typu „FADEC”, a odwzorowanie fazowe [Analysis of the operation of the PZL-10WM engine with a full authority digital engine

] Jankowski, A., Reduction Emission Level of Harmful Components Exhaust Gases by Means of Control of Parameters Influencing on Spraying Process of Biofuel Components for Aircraft Engines, Journal of KONES, Vol. 18, No. 3, pp. 129-134, Warsaw 2011. [15] Kaźmierczak, U., Kulczycki, A., Dzięgielewski, W., Jankowski, A., Microemulsion Fuels for Piston Engines , Journal of KONBiN. Volume 21, Issue 1, pp. 131-140, 2012. [16] Kowalski, M., Unstable Operation of the Turbine Aircraft Engine, Journal of Theoretical and Applied Mechanics, Vol. 51, Issue 3, pp. 719-727, Warsaw

Abstract

The article presents the possibility of using a rotary piston engine, called the Wankel engine, to drive for unmanned aerial vehicles. It describes the principle of engine operation, its advantages and disadvantages. The article specifies the categories of drones to which these engines are dedicated. The author presents the modular Wankel engine of 5-120 hp for unmanned aerial vehicles, manufactured by Advanced Innovative Engeeniering.

Abstract

The main goal of the presented work is to determine the impact of the cyclic hardening model on the numerical results of the ε-N fatigue test. As an object of study, compressor blade (from PZL-10W helicopter engine) was used. The examined blade was made of EI-961 alloy. In numerical analysis, a geometrical model of the blade with a preliminary defect was created. Geometrical defect – V-notch was created on the leading edge. This defect was introduced in order to weaken the structure of the element and the possibility of observing the crack initiation process (in experimental tests). Material data to ε-N analysis, based on Manson-Coffin-Basquin equation, were estimated for Mitchell’s model. This model was built based on strength data provided by the steel producer. Based on three different models of cyclic hardening (Manson, Fatemi, and Xianxin), a number of load cycles were calculated. Load cycle during numerical analysis was represented as resonance bending with an amplitude of displacement equal to A = 1.8 mm. Obtained results were compared with experimental data. Additionally, the analytical model of ε-N fatigue (depending on the cyclic hardening) was prepared. All the work carried out has been summarized by a comprehensive comparative analysis of the results. Obtained results and dependencies can be used in the selection of an appropriate model of cyclic hardening in further fatigue tests of many aerospace elements.

Abstract

The paper presents how the parameters defining the state of the atmosphere: pressure, temperature, humidity, are affecting performance of the aircraft turbine engines and their durability. Also negative impact of dust pollution level is considered as an important source of engine deterioration. Article highlights limitation of the aircraft takeoff weight (TOW) and requirements for length of the runways depending on weather condition changes. These problems stem from the growing “demand” of gas turbine engines for an air. The highest thrust engines have air mass flow more than 1000 kg/s. Engine inlet ice formation is presented as a result of weather conditions and inlet duct design features.

Abstract

The research paper discusses the advantages of using compressor downstream air partial bleed and supplying it downstream of the turbine, which was applied in a prototype of a “bypass” turbojet engine. The impact of such a solution on the value of achieved basic operating parameters of the engine was described, i.e., unit thrust and unit power consumption. The presented attempt to compare these parameters with the parameters achieved for a turbojet, single flow engine is very important; in the first case without air bleed, and in the second, with air bleed to the environment and with the parameters of a turbojet, turbofan engine with a jet mixer.