Autor: Orkisz, M. - Katalog OPAC zbiorów

Skocz do pozycji: 1.

Tytuł:: Flight characteristics of helicopter turboshaft engine with free turbine
Autorzy:: Czarnecki, M.
Orkisz, M.
Powiązania:: https://bibliotekanauki.pl/articles/243360.pdf
Data publikacji:: 2007
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: propulsion
engine
turboshaft
helicopte
performance
ceiling
Opis:: Numerical model for selected turboshaft engine is highly required by helicopter and aircraft designers. Presented paper includes key features for turboshaft numeric model builders. The study of the real performance and estimated results showed that presented method is exact for higher throttle levels. Presented method will be useful for preliminary design when is no need to acquire real test data. Numerical model was build for steady state operations, because maintenance manual for selected engine includes tests records only at its state. In that case helicopter turboshaft manuals are very similar, steady state was used widely for testing in TB3 and T700 family engines. Steady state reduced effect of rotor head positions which was influencing total engine performance. TB3-117 helicopter turboshaft engine, engine cutaway sections, first step - expansion ratios, second step - on the ground calculations for different throttle position, engine inlet mass flow ratio as a function of maximum allowable EGT, and throttle position, third step - on the ground calculations for different throttle position, second step - on the ground calculations for different throttle position, performance charts for RR-250 BJ turboshaft, and for TB3-117 M/MT - Mi-14/17, TB3-117 III-series Mi-24 are presented in the paper.
Źródło:: Journal of KONES; 2007, 14, 3; 149-151
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 2.

Tytuł:: Preliminary design of micro scale turbojet
Autorzy:: Czarnecki, M.
Orkisz, M.
Powiązania:: https://bibliotekanauki.pl/articles/248091.pdf
Data publikacji:: 2008
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: propulsion
micro gasturbines
preliminary micro gasturbine design
rc gasturbine
Opis:: During the development of the small gas turbine, the most important calculations comes from preliminary design process which gives a shape of airflow duct and limits available space for each component of the engine. Micro scale jet engines are not simply reduced-scale model of the full-size engines. The basic method of working is the same, but the are special considerations which demands a different approach to the main design. There are few similarities to the first generation of turbojets, for both critical dimensions comes from compressor and combustor. Micro gas turbine in the contrast to jet engines does not possess the mechanical coupling to the group of accessories. All accessories are electric driven. Small fuel pumps supply fuel line with pressure that hardly exceeds pressure that comes from compressor. The lubrication system is connected to the main fuel line. Bearings are lubricated with mixture of kerosene and turbine oil. Main difficulties in the process of preliminary design come from connecting of the each engine component. Narrow margin that consist limitations from rotational speed, overall dimensions, thermal and centrifugal loads ,overall efficiency and lack of knowledge about design process for small gasturbine makes up challenge for skilled designers.
Źródło:: Journal of KONES; 2008, 15, 3; 83-87
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 3.

Tytuł:: Multidisciplinary design and optimization of gas turbine engine low pressure turbine at preliminary design stage
Autorzy:: Bar, W.
Orkisz, M.
Moustapha, H.
Powiązania:: https://bibliotekanauki.pl/articles/246241.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: design and optimization
turbomachinery
turbines
Opis:: The gas turbine engine has evolved rapidly during past decades to provide a reliable and efficient business solution for global transportation. The engine design process is clearly a large contributor to this evolution. This process is highly iterative, multidisciplinary and complex in nature. The success of an engine depends on a carefully balanced design that best exploits the interactions between numerous traditional engineering disciplines such as aerodynamics and structures as well as lifecycle analysis of cost, manufacturability, serviceability and supportability. To take into account all of these disciplines and optimization should be used. Currently most of present state-of-art numerical modelling methods, which are used mainly at detailed design stage, are unsuitable for this task due to very high computational time. The solution to this problem can be found in multidisciplinary design and optimization at preliminary design stage with use of simple 1-2D models. This paper presents current aero engine design process and indicates possibilities of future improvements by utilization of proposed methodology, which take into account aerodynamic, thermodynamic and structures (blade, fixing and disc) calculations, connected in one multidisciplinary model, which is suited for optimization. All disciplinary models are presented and described in this paper as well as connection between them, with study over design variable, goal function and constrains that should be used. Moreover, a strategy of optimization is proposed as well as methods for acceleration of optimization process by use of surrogate. The presentation of methodology is followed by example optimization of low-pressure aero engine turbine.
Źródło:: Journal of KONES; 2014, 21, 3; 15-22
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 4.

Tytuł:: Preliminary analysis of two combustors turbofan engine
Autorzy:: Jakubowski, R.
Orkisz, M
Wygonik, P.
Powiązania:: https://bibliotekanauki.pl/articles/241925.pdf
Data publikacji:: 2013
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: jet engine
turbofan engine
Opis:: The problems of turbofan engines development is briefly discussed in the beginning. Next the conception of turbofan engine with two combustors is presented, and an engine thermodynamic cycle is analysed. The proposed engine it is a modification of the contemporary turbofan engine by addition of another combustor. First one is classical combustor located between high pressure compressor and turbine. Second one is located between high pressure turbine and low pressure turbine. This conception allows to lower the high pressure turbine inlet temperature. The second combustor increases energy of gasses inflow the low pressure turbine to the sufficient level for fan drive. The results of numerical analysis are used to show performance of the proposed engine and to present their advantages with compare to the classical turbofan engine construction. Then some other positive aspects of two combustors engine are discussed. It refers to possibilities of pollution emission reduction and overhauling period increasing and engine life time extension. On the other hand some aspects of engine hot elements (turbine) production simplification and cost reduction is analysed. In the next chapter the problems of the proposed engine technical realization are discussed. The summary and conclusions are presented in the last part of article.
Źródło:: Journal of KONES; 2013, 20, 2; 175-180
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 5.

Tytuł:: Preliminary research of microgasturbine injection ring
Autorzy:: Czarnecki, M.
Orkisz, M.
Wołoszyn, T.
Powiązania:: https://bibliotekanauki.pl/articles/247528.pdf
Data publikacji:: 2010
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: gasturbine
rc gasturbine
propulsion
fuel supply
Opis:: 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.
Źródło:: Journal of KONES; 2010, 17, 4; 117-122
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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Skocz do pozycji: 6.

Tytuł:: Prospective alternative propulsion systems for unmanned aerial vehicles
Autorzy:: Orkisz, M
Wołoszyn, T.
Wygonik, P
Powiązania:: https://bibliotekanauki.pl/articles/949507.pdf
Data publikacji:: 2014
Wydawca:: Instytut Techniczny Wojsk Lotniczych
Tematy:: alternative energy sources
hybrid-electric propulsion systems
fuel cells
solar cells
unmanned aerial
vehicles
Opis:: The paper presents selected issues concerning alternative power sources and propulsion systems meant for unmanned aerial vehicles (UAVs). The implementation of new propulsions in aviation is a laborious and long-term process, mostly due to safety and economical restrictions and requirements. Broadly, exploited solutions known from automotive industry may serve as a basis for development in aerospace technology, but cannot be applied without considering specific technical aspects (related to aircraft technology and flying objects physics). These aspects are mentioned in the text and some issues concerning suitability of types of aircraft are described. The paper presented contains a review of research on non-conventional propulsion systems for UAVs, conducted in Rzeszow University of Technology. Selected results of the research the fuel cell and the solar-cell UAVs and the aerial hybrid-electric drive test stand are shown in adequate pictures. The small-unmanned flying objects seem to be an accurate basis for such research. They allow reducing costs and improving safety in comparison to full-scale manned aircraft. They are also much quicker in manufacturing and easier to maintain and repair. Moreover, due to their various applications they may comprise the target market for this kind of propulsions. In particular, the issues of parallel hybrid-electric propulsions, fuel cell and solar-cell-assisted systems with appropriate examples are mentioned in the paper..
Źródło:: Journal of KONES; 2014, 21, 4; 369-374
1231-4005
2354-0133
Pojawia się w:: Journal of KONES
Dostawca treści:: Biblioteka Nauki

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